JP2020084779A - Fluid type thrust direction control device - Google Patents

Abstract

[Object] To satisfy not only the condition (first condition) that "thrust is deflected when it should be deflected" but also the condition (second condition) that "thrust is not deflected when it should not be deflected". A thrust vector control system using a dual throat nozzle is provided. A thrust direction control device using a dual throat nozzle (10) having a first throttle portion (12), a widening portion (14), and a second throttle portion (15). By setting the cross-sectional area A2* of the second throat 16 to be larger than the cross-sectional area A1* of the first throat 13 formed at the downstream end of the first throttle portion 12, the secondary jet flows into the nozzle 10. During non-deflection control in which only the main flow FIN1 is flowed without injecting FIN2, a supersonic flow is generated in the diverging portion 14, and by preventing the flow from separating from the inner wall surface of the nozzle, unintended thrust deflection is prevented. I tried not to [Selection drawing] Fig. 6

Description

The present invention relates to a fluid thrust direction control device for controlling a thrust direction of a rocket engine, a jet engine or the like.

Most aircraft and various flying objects control their movements by aerodynamic steering, but aerodynamic steering may not work effectively under low dynamic pressure. For example, when the space around the airframe has a vacuum or low density, such as a space rocket operated in outer space or high altitude, or the speed of the airframe is very slow like various projectiles immediately after being launched from the ground. In this case, motion control using aerodynamic force (aerodynamic steering) becomes extremely difficult. Thrust direction control (TVC: Thrust Vector Control) is used to control the airframe under such conditions. Thrust direction control is a technique for controlling the direction of thrust by changing the direction of a jet flow discharged from a rocket engine or a jet engine by some method. As a result, even when the aerodynamic steering is not effective, it is possible to control the attitude and traveling direction of the airframe. In recent years, as a means for ensuring high maneuverability in an aircraft, there are cases where aerodynamic steering and TVC are used together.

The thrust direction control device can be roughly classified into a mechanical type and a fluid type. The mechanical thrust force direction control device (mechanical thrust force direction control device) mechanically changes the shape of the flow path of the jet flow. Mechanical thrust direction control devices include those that provide an inclined plate in the engine nozzle, those that change the nozzle shape, and those that change the direction of the engine itself. On the other hand, the fluid type thrust direction control device (fluid type thrust direction control device) changes the direction of the jet flow ejected from the nozzle outlet by using the action of the fluid itself flowing in the nozzle. A typical fluid-type thrust direction control device is one that injects a secondary jet into a main stream flowing in a nozzle to cause a change in the flow of the main stream and deflect the direction of the jet as a whole. .. The hydraulic thrust direction control is superior to the mechanical thrust direction control in that it is easy to reduce the weight and the response performance is improved.

As a fluid thrust direction control device using a secondary jet, a device using a dual throat nozzle has been proposed (for example, see Non-Patent Documents 1 and 2). Here, the "dual throat nozzle" is a nozzle having a shape in which a second throat is provided by narrowing the outlet of a Laval nozzle normally used as a nozzle for rocket engines and the like. FIG. 1 shows a conceptual diagram of a conventionally proposed dual throat nozzle 10. In the figure, reference numeral "10" indicates a dual throat nozzle, reference numeral "10a" indicates the center line of the nozzle, reference numeral "11" indicates the nozzle inlet, reference numeral "12" indicates the first throttle portion, and reference numeral "13" indicates The first throat, reference numeral “14” indicates a widened portion, reference numeral “15” indicates a second throttle portion, reference numeral “16” indicates a second throat, reference numeral “18” indicates a nozzle outlet, and reference numeral “19” indicates two. The secondary jet injection port, reference numeral “F _IN1 ”, is the main flow flowing from the engine combustion chamber to the nozzle inlet, reference numeral “F _IN2 ”is the secondary jet flow injected from the secondary jet injection port, and the reference numeral “F _OUT ” is the nozzle. The jets ejected from the outlet are represented by the reference numerals “F _a ”, “F _b ”, “F _c ”, and “F _d ”, which are typical streamlines, and the reference numeral “α ₁ ”is the separation region (hatched in FIG. Area) is shown.

As shown in FIG. 1, when the secondary jet F _IN2 is injected from the secondary jet injection port 19 provided in the lower nozzle wall near the first throat 13, the flow of the main flow F _{IN1 changes} its streamline F _a. , F _b , F _c , and F _d (particularly, the lower streamline F _d ), the dual throat nozzle 10 is separated from the inner wall surface on the lower side, and the secondary jet injection port 19 and the lower stream surface are separated. A separation area α ₁ is formed between the inner wall surface and the second throat 16. As a result, the main flow F _IN1 is largely pushed upward, and is pushed back in the opposite direction by the second throttle portion 15 immediately before the nozzle outlet 18. For this reason, the jet flow F _OUT ejected from the nozzle outlet 18 is deflected so as to be parallel to the nozzle center line 10a and directed to the lower right than the direction to the right, and the thrust generated as a reaction thereof is parallel to the nozzle center line 10a and directed to the left. Bias so that it faces the upper left of the direction of. In the dual throat nozzle 10 using the secondary jet, the thrust direction is controlled by the above mechanism (hereinafter, also referred to as “flow separation mechanism”).

Flamm, J.M. D. , Deere, K.; A. Mason, M.; L. Berrier, B.; L. , And Johnson, S.; K. , "Experimental Study of an Axisymmetric Dual Throat Fluid Thrust Vectoring Nozzle for Supersonic Application", 7, 50-200, AIA 200 Pa. Shin, C.I. S. Kim, H.; D. , Setoguchi, T.; and Matsuo, S., "A Computational Study of Throwing Vectoring Control Using Dual Throat Nozzle", J. Am. Thermal Science, 19, 6 (2010), pp. 486-490. Farn, R.; M. Mullin, T.; and Cliffe, K.; A. , "Nonlinear Flow Phenomena in a Symmetric Sudden Expansion", J. Am. Fluid Mech. , 211 (1990), pp. 595-608. Durst, F.F. Pereira, J.; C. F. and Tropea, C.I. , "The Plane Symmetric Sudden-Expansion Flow at Low Reynolds Numbers", J. Am. Fluid Mech. , 248 (1993), pp. 567-581. Nakanishi Sukeji, Sakurai Motoyasu, Oda Shingo, "Numerical Study on Asymmetric Flow in Two-Dimensional Symmetrical Expansion Channel", Hiroshima Institute of Technology Bulletin, 30 (1996), pp. 37-43. Leapman Roshko, Translated by Tamada Ko ("Kou" means "King" and "Light"), "Gas Mechanics", Yoshioka Shoten, 1960.

By the way, when considering the practicality of a thrust direction control device including a dual throat nozzle that uses a secondary jet, the condition that "the thrust is deflected when it should be deflected" (hereinafter referred to as "first condition"). And the condition that “the thrust is not deflected when it should not be deflected” (hereinafter, may be referred to as “second condition”). However, the establishment of the first condition has already been confirmed in Non-Patent Document 1 and Non-Patent Document 2, but the establishment of the second condition has not yet been confirmed. Therefore, the inventor performed a simulation to confirm whether the dual throat nozzle using the secondary jet satisfies the second condition. Specifically, in the dual throat nozzle 10 shown in FIG. 1, the flow field and the thrust deflection angle in the dual throat nozzle 10 when the secondary jet F _IN2 is not injected and only the main flow F _IN1 is flowed in are numerical values. Calculated by simulation.

As a simulation analysis method, a Monte Carlo direct simulation (DSMC: Direct Simulation Monte Carlo) method was used. The molecular model is a rigid sphere, and the rigid sphere is specularly reflected by the inner peripheral wall of the dual throat nozzle 10. The thrust (vector amount “f”) is calculated from the value of the total momentum (vector amount “Δp”) of the molecules ejected from the nozzle outlet 18 during a minute time (“Δt”). It was determined using the following formula 1. Further, the thrust deflection angle (referred to as “δ”) was obtained using the following equation 2.

Further, in this simulation, the dual throat nozzle 10 was defined as a two-dimensional nozzle in which the shape of an arbitrary cross section perpendicular to the y-axis direction was the same as that shown in FIG. The dimension of each part (dimension of each part with respect to the opening width D ₁ of the nozzle inlet 11) in the cross section perpendicular to the y-axis direction of the dual throat nozzle 10 was set to the value shown in FIG. 3. Hereinafter, the dual throat nozzle 10 having the dimensions shown in FIG. 3 may be referred to as “nozzle A”. The width (cross-sectional area) of the second throat 16 in the nozzle A is a thrust direction control device using a conventionally proposed dual throat nozzle (thrust direction using the dual throat nozzle of Non-Patent Document 1 and Non-Patent Document 2). Like the control device), the size is set to be the same as the width (cross-sectional area) of the first throat 13. The calculation was started from an initial state in which the entire area inside the dual throat nozzle 10 is a vacuum, and continued until at least the flow field inside the dual throat nozzle 10 was confirmed to be in a substantially steady state.

Prior to this simulation for confirming whether or not the above-mentioned "second condition" is satisfied (hereinafter, it may be referred to as "second condition confirmation simulation"), "Flow of Flow" explained in the section of "Background Technology" is explained. A simulation (hereinafter also referred to as “first condition confirmation simulation”) for confirming whether the thrust direction is actually deflected by the “separation mechanism” (whether or not the first condition is satisfied) is also performed. It was Specifically, in the two-dimensional nozzle (nozzle A) having the dimensions shown in FIG. 3, as shown in FIG. 1, the flow in the dual throat nozzle 10 when the main flow F _IN1 and the secondary jet F _IN2 are injected. The simulation was performed. The analysis method of the first condition confirmation simulation was the same as that of the second condition confirmation simulation described above. However, in the first condition confirmation simulation, as shown in FIG. 1, the secondary jet F _IN2 is injected. The flow rate of the secondary jet _{F IN2} is set to 5% for the total flow rate of the mainstream _{F IN1} and secondary jets _{F IN2.} The injection direction of the secondary jet F _IN2 was set to a direction rotated counterclockwise by 150° from the rightward direction (the positive side in the x-axis direction) parallel to the nozzle center line 10a in FIG. 1 toward the paper surface in FIG. Calculations in this case have confirmed that the thrust deflection angle δ in the steady state is approximately −19°. Here, since the thrust deflection angle δ calculated by the above equation 2 becomes a positive value when it is deflected counterclockwise in FIG. 3, the thrust is deflected in the upper left direction by the mechanism shown in FIG. The value of δ is negative.

FIG. 4 shows the result of the second condition confirmation simulation performed for the nozzle A. This FIG. 4 is a graph showing the change over time of the thrust deflection angle δ. In the figure, the values of the random number sequence used for the simulation are set to 10 and the results of the respective calculations are displayed in an overlapping manner. However, the conditions other than the random number sequence are the same. In the second condition confirmation simulation, a series of random numbers is used to set the velocity of each inflowing molecule, select molecules that collide with each other, and determine the scattering direction after collision. In addition, the time indicates a dimensionless value with D ₁ /(2RT ₁ ) ^1/2 as a reference value. Here, D ₁ is the opening width of the nozzle inlet 11, R is a physical quantity corresponding to the gas constant of the simulated molecule used in the calculation, and T ₁ is the absolute temperature in the inflow from the nozzle inlet 11. As is apparent from FIG. 4, the thrust deflection angle δ is approximately 0° for any random number sequence until time t=13, but within the range of t>13, the thrust deflection angle δ is positive due to the random number sequence. Or, it may take a negative value, and its absolute value reaches a maximum of about 4°. Even though the nozzle shape and inflow conditions are set vertically symmetrical, the direction of the thrust vector is deflected from the axis of symmetry, and the direction and magnitude of deflection are variously changed due to the random factor of the random number sequence. is doing.

In the case of the random number sequence 4 and the random number sequence 10 in which the large absolute value of the deflection angle is obtained, the flow lines in the nozzle at t=37.5 after a sufficient time has passed are shown in FIGS. ) Respectively. From FIGS. 5A and 5B, it can be clearly seen that a vertically asymmetric peeling region is generated in the dual throat nozzle 10. In both cases of the random number sequence 4 and the random number sequence 10, the subsonic velocity or the transonic velocity is set in the entire area of the dual throat nozzle 10.

In this way, statistical fluctuations are reflected in the simulation calculation process and calculation results. This fluctuation also exists in the actual flow field. However, the number of molecules in the simulation is about 10 6 and is much smaller than the actual Avogadro's number. For this reason, statistical fluctuations are reflected in the simulated flow field in a larger scale than in the actual flow field. On the other hand, in the actual flow field, there are macroscopic disturbances that are not considered in the simulation. Since this macroscopic turbulence can bring about the same effect as the fluctuation, the above-mentioned asymmetry can occur in the actual flow. Although the shape is different from this case, it has been confirmed experimentally that the incompressible flow passing through the sudden expansion part of the two-dimensional tube symmetrical with respect to the center line of the flow channel creates an asymmetric separation region. (See Non-Patent Document 3 and Non-Patent Document 4). Generally, in the widened portion, flow separation is likely to occur, and even if the boundary shape is symmetrical with respect to the center line of the flow path, the constraint condition that the separation region is also symmetrical is not imposed. In fact, if the Reynolds number is not too small, it is shown by numerical analysis that there is a solution having an asymmetric peeling region (see Non-Patent Document 3, Non-Patent Document 4, and Non-Patent Document 5). In general, the number of solutions increases with Reynolds number. Which solution each individual flow field faces is affected by minute turbulence and fluctuations existing in the flow field or slight irregularities on the wall surface.

Furthermore, in the case of a high-speed flow whose compressibility is not negligible, such as the flow field in a fluid thrust control device, even if a flow that does not separate at the widening part is realized, if the flow velocity is below the sonic velocity, The flow is decelerated at the spread portion of the fluid to cause a reverse pressure gradient state (a state in which the pressure increases as it goes downstream), and the volume of the fluid decreases as it moves downstream. In the situation where the expansion of the flow channel and the reduction of the fluid volume occur at the same time, it is difficult to continue the flow without separation, and it can be said that the transition to the separation flow is a natural consequence. At that time, if there exists a solution in which the separation region has an asymmetrical shape, it is not unnatural if the flow field may shift to that solution.

As described above, in the hydraulic thrust direction control device, in addition to the first condition that "the thrust is deflected when it should be deflected", the second condition that "the thrust is not deflected when it should not be deflected" Is also important. In this respect, the fluctuation in the thrust direction that appears in the second condition confirmation simulation (FIG. 4) when the thrust should not be deflected is due to the "secondary jet generated due to an accidental factor" even in the actual fluid thrust direction control device. It may appear as "thrust thrust deflection". This may be a serious problem regarding whether or not the fluid thrust control device using the dual throat nozzle is put to practical use. Therefore, this problem should be solved in advance for practical use of the fluid thrust direction control device using the dual throat nozzle.

The present invention has been made to solve the above-mentioned problems, and not only the condition (first condition) that "thrust is deflected when it should be deflected" but also "thrust is deflected when it should not be deflected". A thrust direction control device using a dual throat nozzle that can also satisfy the condition "not" (second condition).

The above problems are
By injecting the secondary jet from the secondary jet injection port provided in the middle of the nozzle to the main flow that flows in the nozzle from the nozzle inlet to the nozzle outlet, the flow of the main stream is changed, and from the nozzle outlet A fluid thrust direction control device for changing the direction of a jet flow,
The nozzle
The upstream end serves as a nozzle inlet, the cross-sectional area of the downstream end is formed to be smaller than the cross-sectional area of the upstream end, and the downstream end has a first throttle portion that is the first throat,
A widened portion which is connected to the downstream side of the first throttle portion and whose cross-sectional area of the downstream end portion is larger than that of the upstream end portion.
It has a second throttle portion which is connected to the downstream side of the widened portion and whose downstream end has a cross-sectional area smaller than that of its upstream end and whose downstream end serves as a second throat. With a dual throat nozzle,
By setting the cross-sectional area of the second throat (referred to as "A ₂ ^* ") to be larger than the cross-sectional area of the first throat (referred to as "A ₁ ^* "), the secondary jet flow is generated in the nozzle. During non-deflection control in which only the main flow is introduced without injecting, supersonic flow is generated in the expanded part and it is prevented from separating from the inner wall surface of the nozzle, so that unintentional thrust deflection does not occur. A solution is provided by providing a fluid thrust control apparatus.

Accordingly, the thrust direction control device using the dual throat nozzle can also satisfy the condition (second condition) of "not deflecting thrust when it should not be deflected". That is, by adopting the above configuration, when only the main flow is allowed to flow into the nozzle without injecting the secondary jet flow (during non-deflection control), the expansion part connected to the downstream side of the first throat The shock wave can be made to stand at a specific position in, and the flow can be made supersonic in the region between the place where the first throat is formed and the place where the shock wave is standing. For this reason, when the secondary jet is not injected into the nozzle, separation in the nozzle is suppressed, a flow field that is substantially symmetrical with respect to the nozzle center line is realized, and fluctuations in the thrust direction are suppressed. (The thrust deflection angle can be made substantially constant at 0°).

The reason why a shock wave is generated in the above-mentioned widened portion by making the cross-sectional area A ₂ ^* of the second throat larger than the cross-sectional area A ₁ ^* of the first throat is as follows, using the theory based on the one-dimensional flow approximation. Can be explained. That is, in both throat parts (first throat and second throat) of the dual throat nozzle, the Mach number is 1, that is, the flow velocity is equal to the speed of sound due to the property of the compressible fluid. In a continuous flow tube (tube without branching or injection from the middle), the cross-sectional area at which the flow becomes sonic is inversely proportional to the total pressure at each position. That is, when the Mach number is 1 at both throats, the following Expression 3 is established (see Non-Patent Document 6). In Formula 3 below, “p ₀₁ ”and “p ₀₂ ” are total pressures at the first throat and the second throat, respectively.

Further, when the total pressure ratio on the right side of the above Expression 3 (which becomes a value exceeding 1 due to the total pressure loss) is generated by one shock wave, the following Expression 4 is derived from the Rankine-Hugoniot relational expression. In Equation 4, “M ₁ ”is the shock wave upstream Mach number, and “γ” is the specific heat ratio.

When the total pressure ratio p ₀₁ /p ₀₂ obtained by substituting the ratio A ₂ ^* /A ₁ ^* of the cross-sectional areas of both throats into the above equation 3 is substituted into the left side of the above equation 4, the shock wave upstream Mach number M ₁ is obtained. You can The shock wave is located at a location in the nozzle where the shock wave upstream Mach number M ₁ is obtained (the cross-sectional area of the nozzle at the location is “A _S ”). Regarding the value of the cross-sectional area A _S, the value of the shock wave upstream Mach number M ₁ obtained from the above Expression 4 is substituted into the following Expression 5 under the approximation that it is an isentropic flow between the first throat and the shock wave. It can be calculated by When the cross-sectional area ratio A ₂ ^* /A ₁ ^* is larger than 1 (when the cross-sectional area A ₂ ^* of the second throat is larger than the cross-sectional area A ₁ ^* of the first throat), the disconnection in the following formula 5 is applied. The area ratio A _S /A ₁ ^* is greater than 1. From this, it is understood that a shock wave is generated in the above-mentioned widened portion by making the cross-sectional area A ₂ ^* of the second throat larger than the cross-sectional area A ₁ ^* of the first throat.

The reason why the flow becomes supersonic in the region between the formation position of the first throat and the standing position of the shock wave to suppress separation in the nozzle can be explained as follows. That is, in the supersonic flow, a forward pressure gradient (a phenomenon in which the pressure decreases toward the downstream side) is generated by acceleration in the spread portion, and the fluid expands as it moves downstream (hereinafter, this expansion mechanism will be referred to as " It may be referred to as "expansion mechanism of supersonic flow in the widened portion".) Therefore, even if the cross-sectional area of the flow channel expands, the fluid expands to fill the flow channel, and a flow without separation is likely to be realized. That is, the second condition that the thrust is not deflected when it should not be deflected (when the secondary jet is not injected into the nozzle) is likely to be satisfied.

In the fluid thrust direction control device of the present invention, there is no particular limitation on how much the cross-sectional area A ₂ ^* of the second throat is made larger than the cross-sectional area A ₁ ^* of the first throat. However, if the ratio A ₂ ^* /A ₁ ^* of the cross-sectional area A ₂ ^* of the second throat to the cross-sectional area A ₁ ^* of the first throat is too small (too close to 1), the above formula 3, the above formula 4, and the above The value of the cross-sectional area ratio A _S /A ₁ ^* calculated by Equation 5 becomes small (approaching 1), and the standing position of the shock wave approaches the formation point of the first throat. Since the supersonic region between them becomes narrower, the above-mentioned effect (the effect of suppressing fluctuation in the thrust direction when the secondary jet is not injected into the nozzle) becomes difficult to be achieved, and the significance of adopting the configuration of the present invention Is reduced. Therefore, the ratio A ₂ ^* /A ₁ ^* is preferably 1.2 or more. On the other hand, if the ratio A ₂ ^* /A ₁ ^* is made too large, the thrust deflection angle δ when the secondary jet is being injected into the nozzle becomes small, as will be described later. It becomes difficult to satisfy the condition of "deflecting" (first condition). Therefore, the ratio A ₂ ^* /A ₁ ^* is preferably 1.8 or less.

By the way, as described above, the area where the first throat is formed when the cross-sectional area A ₂ ^* of the second throat is made larger than the cross-sectional area A ₁ ^* of the first throat and the secondary jet is not injected. If the second condition "not deflect when thrust should not be deflected" is satisfied by ensuring that the flow becomes supersonic in the region between and where the shock wave is stationary, In order to deflect, even if a secondary jet is injected from the secondary jet inlet provided in the nozzle wall near the first throat to cause flow separation in the nozzle, the supersonic flow of the above-mentioned widened portion Due to the expansion mechanism, the fluid forming the main stream expands, so that there is a risk that the separation will be eliminated immediately (the separation will be eliminated at a location near the downstream side from the location where the separation has occurred). Therefore, it becomes difficult to satisfy the first condition that "the thrust is deflected when it should be deflected". Therefore, in the fluid thrust direction control device of the present invention, a thrust direction control device using a conventionally proposed dual throat nozzle (dual throat nozzle in which a secondary jet injection port is provided near the first throat) is used. In contrast, it is preferable to provide the secondary jet injection port in the widened portion.

Thus, the cross-sectional area A ₂ ^* of the second throat is made larger than the cross-sectional area A ₁ ^{* of} the first throat, and when the secondary jet is not injected, the place where the first throat is formed and the shock wave are generated. Even if the flow is made supersonic in the area between the fixed location and the secondary jet is being injected into the nozzle, the flow will be subsonic near the secondary jet injection port. It is also possible to For this reason, the main flow separated in the nozzle (the main flow pushed in the nozzle to the side opposite to the secondary jet injection port) does not return until the second throttle portion is reached (separation is not eliminated). Will be possible. Therefore, the first condition that "the thrust is deflected when it should be deflected" can be easily satisfied.

Here, in the dual throat nozzle in which the cross-sectional area A ₂ ^* of the second throat is larger than the cross-sectional area A ₁ ^* of the first throat, as in the dual throat nozzle in the fluid thrust direction control device of the present invention, the dual throat nozzle is installed in the nozzle. The position of the secondary jet inlet where the flow becomes subsonic near the secondary jet inlet while the secondary jet is being injected can be specified as follows.

First, consider the limit where the flow rate of the secondary jet is reduced. In this limit, the position of the shock wave in the nozzle converges on the position of the shock wave when the secondary jet is not injected. Therefore, assuming that the position where the shock wave front when the secondary jet is not injected intersects with the inner wall surface of the nozzle where the secondary jet injection port is to be provided is P ₀ , the secondary jet injection port is P ₀ or downstream of P _0. If it is provided on the side, the flow becomes subsonic near the inlet of the secondary jet in the limit where the flow rate of the secondary jet is small. Since the position of P ₀ is included in the shock wave front when the secondary jet is not injected, the nozzle cross-sectional area is approximately equal to the cross-sectional area A _S obtained by combining the above equations 3, 4, and 5. Matches at equal positions.

Next, when a secondary jet with a finite flow rate is injected from the diverging portion to deflect the thrust, the shock wave in the nozzle is generally the same as in the case described above (when the secondary jet flow rate is reduced. It becomes weaker than in the extreme case). That is, the shock wave upstream Mach number M ₁ becomes smaller, and the total pressure loss amount due to the shock wave becomes smaller. Alternatively, if the flow rate of the secondary jet is large enough, the shock wave disappears. The reason why the shock wave weakens or disappears is that the secondary jet injected into the spread portion does not pass through the first throat but is included in the flow passing through the second throat. Therefore, if the cross-sectional area A ₁ ^* and the cross-sectional area A ₂ ^* in the above equation 3 are replaced with cross-sectional areas that can be substantially occupied by the main flow in the first throat and the second throat, respectively, the ratio A due to the effect of the secondary jet flows. The value of ₂ ^* /A ₁ ^* is reduced. As a result, the total pressure loss caused by the shock wave is reduced or the shock wave becomes unnecessary. In any case, the supersonic region is reduced or disappears as compared with the limit case where the flow rate of the secondary jet is reduced. Therefore, if the secondary jet injection port is provided within the range described above, that is, P ₀ or on the downstream side of P ₀ , even if the flow rate of the secondary jet is finite, the flow rate of the secondary jet The flow becomes subsonic in the vicinity of the secondary jet injection port, as in the limit case where

However, since the above Equations 3, 4, and 5 are derived under the approximation of a one-dimensional flow, an isentropic flow, etc., some of them are compared with the actual flow in the nozzle. It may include an error. Therefore, the upstream limit of the inlet setting position for the flow to be subsonic in the vicinity of the secondary jet inlet is such that the cross-sectional area in the expanded portion is expressed by the above formula 3 in consideration of the influence of the above error. It is preferable to set the area to be 0.9 times the cross-sectional area A _S obtained from the above equations 4 and 5. On the other hand, regarding the downstream limit of the inlet setting position, there is no particular restriction due to the condition that the flow becomes subsonic near the inlet, but as a general tendency, the position of the secondary jet inlet is downstream. Since the peeling area becomes smaller as the distance goes to, and the thrust deflection effect becomes weaker, it is not preferable that the distance is too large in the downstream direction from P ₀ . Therefore, the downstream side limit of the setting position of the secondary jet injection port is a place where the cross-sectional area in the expanded portion is 1.1 times the cross-sectional area A _S obtained from the above Expression 3, Expression 4 and Expression 5. (cross-sectional area of the downstream end of the expansion portion if less than 1.1 times the cross-sectional area a _S, the downstream end of the expanded portion) is preferably set to.

In the fluid thrust direction control device of the present invention, the nozzle is provided with each part in the order of the first throttle part, the first throat, the widening part, the second throttle part, and the second throat from the nozzle inlet to the nozzle outlet. The material is not particularly limited as long as it is a product. Examples of the nozzle include a nozzle having the same cross-sectional shape parallel to one plane including the center line (so-called two-dimensional nozzle), a nozzle having a shape of a rotating body having the center line as an axis, and the like.

As described above, according to the present invention, not only the condition that the thrust is deflected when it should be deflected (first condition) but also the condition that the thrust is not deflected when it should not be deflected (second condition) It is possible to provide a thrust direction control device using a dual throat nozzle that can also satisfy the above.

It is a conceptual diagram of the dual throat nozzle (nozzle A) proposed conventionally. It is a figure showing the two-dimensional nozzle used in the simulation. It is a figure explaining the simulation dimension of the dual throat nozzle (nozzle A) proposed conventionally. It is the graph which showed the result of the 2nd condition confirmation simulation which was done concerning the dual throat nozzle (nozzle A) which is proposed from the past, when only the main flow inflows without injecting the secondary jet into the nozzle (non 3 shows the time variation of the thrust deflection angle (during deflection control) for each random number sequence. It is the figure which showed the result of the 2nd condition confirmation simulation performed about the conventionally proposed dual throat nozzle (nozzle A), when only the main flow inflows without injecting a secondary jet into a nozzle (non- The flow lines in the nozzle during the deflection control) are shown for (a) the random number sequence 4 in FIG. 4 and (b) for the random number sequence 10 in FIG. It is a key map of a dual throat nozzle used with a fluid type thrust direction control device of the present invention. It is the perspective view which showed the example of the three-dimensional shape of the dual throat nozzle used with the fluid type thrust direction control apparatus of this invention. It is a figure explaining the simulation size of the dual throat nozzle (nozzle B) used with the fluid type thrust direction control device of the present invention. It is the graph which showed the result of the 2nd condition confirmation simulation performed about the dual throat nozzle (nozzle B) used with the fluid type thrust direction control apparatus of this invention, Comprising: Only a main flow is injected without injecting a secondary jet into a nozzle. The time change of the thrust deflection angle at the time of inflow (during non-deflection control) is shown for each random number sequence. It is a figure showing the result of the second condition confirmation simulation performed about the dual throat nozzle (nozzle B) used by the fluid type thrust direction control device of the present invention, and only the main flow is injected without injecting a secondary jet into the nozzle. FIG. 10 shows the flow lines in the nozzle when flowing in (during non-deflection control) for the case of the random number sequence 4 in FIG. It is a figure showing the result of the second condition confirmation simulation performed about the dual throat nozzle (nozzle B) used by the fluid type thrust direction control device of the present invention, and only the main flow is injected without injecting a secondary jet into the nozzle. 10 shows the Mach number distribution in the nozzle when flowing in (during non-deflection control) for the case of the random number sequence 4 in FIG. It is a figure explaining the simulation size of the dual throat nozzle (nozzle C) used with the fluid type thrust direction control device of the present invention. It is the graph which showed the result of the 2nd condition confirmation simulation performed about the dual throat nozzle (nozzle C) used with the fluid type thrust direction control apparatus of this invention, Comprising: Only the main flow is not inject|poured into a nozzle. The time change of the thrust deflection angle at the time of inflow (during non-deflection control) is shown for each random number sequence. It is a figure showing the result of the 2nd condition confirmation simulation performed about the dual throat nozzle (nozzle C) used by the fluid type thrust direction control device of the present invention. Only a main flow is injected without injecting a secondary jet into a nozzle. The flow lines in the nozzles when they flow in (during non-deflection control) are shown for the case of the random number sequence 4 in FIG. It is a figure showing the result of the 2nd condition confirmation simulation performed about the dual throat nozzle (nozzle C) used by the fluid type thrust direction control device of the present invention. Only a main flow is injected without injecting a secondary jet into a nozzle. FIG. 14 shows the Mach number distribution in the nozzle at the time of inflow (during non-deflection control) for the case of the random number sequence 4 in FIG. It is a figure explaining the setting position of the secondary jet injection port used by the first condition confirmation simulation performed about the dual throat nozzle (nozzle B) used with the fluid type thrust direction control device of the present invention. It is a figure explaining the setting position of the secondary jet injection port used by the first condition confirmation simulation performed about the dual throat nozzle (nozzle C) used with the fluid type thrust direction control device of the present invention. FIG. 17 is a graph showing the results of the first condition confirmation simulation performed for the dual throat nozzle (nozzle B) used in the fluid thrust direction control device of the present invention, in which the secondary jet is injected from the position of P ₁ in FIG. 16. The time variation of the thrust deflection angle during the deflection (during deflection control) is shown for each random number sequence. FIG. 17 is a diagram showing a result of a first condition confirmation simulation performed for a dual throat nozzle (nozzle B) used in the fluid thrust direction control device of the present invention, in which a secondary jet is injected from a position P ₁ in FIG. 16. FIG. 18 shows the streamlines in the nozzle during the deflection (during deflection control) for the case of the random number sequence 4 in FIG. FIG. 17 is a diagram showing a result of a first condition confirmation simulation performed for a dual throat nozzle (nozzle B) used in the fluid thrust direction control device of the present invention, in which a secondary jet is injected from a position P ₁ in FIG. 16. FIG. 19 shows the Mach number distribution in the nozzle when (during deflection control) for the case of the random number sequence 4 in FIG. A graph showing the results of the first condition confirmation simulation performed for the fluid type dual throat nozzle used in the thrust direction control device (nozzle C) of the present invention, by injecting the secondary jets from the position for Q ₁ in FIG. 17 The time variation of the thrust deflection angle during the deflection (during deflection control) is shown for each random number sequence. A graph showing the results of the first condition confirmation simulation performed for the dual throat nozzle (nozzle C) used in the hydraulic thrust direction control device of the present invention, by injecting the secondary jets from the position for Q ₁ in FIG. 17 FIG. 22 shows the streamlines in the nozzle during the deflection (during deflection control) for the case of the random number sequence 1 in FIG. A graph showing the results of the first condition confirmation simulation performed for the dual throat nozzle (nozzle C) used in the hydraulic thrust direction control device of the present invention, by injecting the secondary jets from the position for Q ₁ in FIG. 17 22 shows the Mach number distribution in the nozzle when the deflection is being performed (during deflection control) for the case of the random number sequence 1 in FIG. FIG. 17 is a graph showing a result of a first condition confirmation simulation performed for a dual throat nozzle (nozzle B) used in the fluid thrust direction control device of the present invention, in which a secondary jet is injected from a position P ₂ in FIG. 16. The time variation of the thrust deflection angle during the deflection (during deflection control) is shown for each random number sequence. A graph showing the results of the first condition confirmation simulation performed for the dual throat nozzle (nozzle B) used in the hydraulic thrust direction control device of the present invention, by injecting the secondary jets from the position of P ₂ in FIG. 16 3 shows the flow lines in the nozzle when the deflection is being performed (during deflection control). A graph showing the results of the first condition confirmation simulation performed for the dual throat nozzle (nozzle B) used in the hydraulic thrust direction control device of the present invention, by injecting the secondary jets from the position of P ₂ in FIG. 16 3 shows the Mach number distribution in the nozzle during the operation (during deflection control). FIG. 17 is a graph showing the results of the first condition confirmation simulation performed for the dual throat nozzle (nozzle B) used in the fluid thrust direction control device of the present invention, in which the secondary jet is injected from the position of P ₃ in FIG. 16. The time variation of the thrust deflection angle during the deflection (during deflection control) is shown for each random number sequence. FIG. 17 is a diagram showing a result of the first condition confirmation simulation performed for the dual throat nozzle (nozzle B) used in the fluid thrust direction control device of the present invention, in which the secondary jet is injected from the position of P ₃ in FIG. 16. 3 shows the flow lines in the nozzle when the deflection is being performed (during deflection control). FIG. 17 is a diagram showing a result of the first condition confirmation simulation performed for the dual throat nozzle (nozzle B) used in the fluid thrust direction control device of the present invention, in which the secondary jet is injected from the position of P ₃ in FIG. 16. 3 shows the Mach number distribution in the nozzle during the operation (during deflection control). A graph showing the results of the first condition confirmation simulation performed for the dual throat nozzle (nozzle C) used in the hydraulic thrust direction control device of the present invention, by injecting the secondary jets from the position Q ₂ 'in FIG. 17 The time variation of the thrust deflection angle during the deflection (during deflection control) is shown for each random number sequence. A graph showing the results of the first condition confirmation simulation performed for the dual throat nozzle (nozzle C) used in the hydraulic thrust direction control device of the present invention, by injecting the secondary jets from the position Q ₂ 'in FIG. 17 3 shows the flow lines in the nozzle when the deflection is being performed (during deflection control). A graph showing the results of the first condition confirmation simulation performed for the dual throat nozzle (nozzle C) used in the hydraulic thrust direction control device of the present invention, by injecting the secondary jets from the position Q ₂ 'in FIG. 17 3 shows the Mach number distribution in the nozzle during the operation (during deflection control). A graph showing the results of the first condition confirmation simulation performed for the dual throat nozzle (nozzle C) used in the hydraulic thrust direction control device of the present invention, by injecting the secondary jets from the position of Q ₃ in FIG. 17 The time variation of the thrust deflection angle during the deflection (during deflection control) is shown for each random number sequence. A graph showing the results of the first condition confirmation simulation performed for the dual throat nozzle (nozzle C) used in the hydraulic thrust direction control device of the present invention, by injecting the secondary jets from the position of Q ₃ in FIG. 17 3 shows the flow lines in the nozzle when the deflection is being performed (during deflection control). A graph showing the results of the first condition confirmation simulation performed for the dual throat nozzle (nozzle C) used in the hydraulic thrust direction control device of the present invention, by injecting the secondary jets from the position of Q ₃ in FIG. 17 3 shows the Mach number distribution in the nozzle during the operation (during deflection control).

1. Outline of Fluid Thrust Direction Control Device of the Present Invention A preferred embodiment of the fluid thrust direction control device of the present invention will be described more specifically with reference to the drawings. FIG. 6 is a conceptual diagram of the dual throat nozzle 10 used in the fluid thrust direction control device of the present invention. In the figure, reference numeral "10" indicates a nozzle, reference numeral "10a" indicates a center line of the nozzle, reference numeral "11" indicates a nozzle inlet, reference numeral "12" indicates a first throttle portion, and reference numeral "13" indicates a first. The throat, reference numeral "14" indicates the widening portion, reference numeral "15" indicates the second throttle portion, reference numeral "16" indicates the second throat, reference numeral "18" indicates the nozzle outlet, reference numeral "19" indicates the secondary jet. The injection port, reference numeral "D ₁ "indicates the opening width of the nozzle inlet, reference numeral "F _IN1 "injects the main flow from the engine combustion chamber into the nozzle inlet, and reference numeral "F _IN2 " injects it from the secondary jet injection port. The reference symbol “F _OUT ”indicates the next jet flow, and the jet flow ejected from the nozzle outlet.

The above-described FIG. 6 illustrates the nozzle 10 as a cross-sectional view taken along a plane including the center line 10a (a plane parallel to the xz plane). FIG. 7 is a perspective view showing an example of a three-dimensional shape of the dual throat nozzle 10 used in the fluid thrust direction control device of the present invention. As for the three-dimensional shape of the nozzle 10, as shown in FIG. 7(a), the shape of the arbitrary cross section perpendicular to the y-axis direction is the same (so-called two-dimensional nozzle), or as shown in FIG. 7(b). In addition, those having a shape of a rotating body with the center line 10a as an axis (so-called axisymmetric nozzle) and the like can be mentioned. A nozzle such as this axisymmetric nozzle in which the shapes of arbitrary cross sections perpendicular to the y-axis direction are not the same may be called a "three-dimensional nozzle" in contrast to the above-mentioned two-dimensional nozzle.

As shown in FIG. 6, the fluid thrust direction control device of the present invention has a main jet F _IN1 flowing from the nozzle inlet 11 to the nozzle outlet 18 in the nozzle 10 and a secondary jet F from the secondary jet inlet 19 to the main flow F _IN1. By injecting _IN2 , the flow of the main flow F _IN1 can be changed, and the direction of the jet flow F _OUT as a whole can be changed.

In the nozzle 10, a first throttle portion 12 is formed on the downstream side of the nozzle inlet 11. The first throttle portion 12 is a portion formed by narrowing from the upstream side (x-axis direction negative side) toward the downstream side (x-axis direction positive side), and the downstream side of the first throttle portion 12 The cross-sectional area (opening area) of the end portion is smaller than the cross-sectional area (opening area) of the upstream end portion of the first throttle portion 12. The downstream end of the first throttle portion 12 is a first throat 13.

A widened portion 14 is formed on the downstream side of the first throttle portion 12 in the nozzle 10. The expanded portion 14 is a portion formed by expanding from the upstream side to the downstream side, and the cross-sectional area (opening area) of the downstream end of the expanded portion 14 is the upstream end of the expanded portion 14. It is wider than the cross-sectional area (opening area) of the part.

Further, a second throttle portion 15 is formed on the downstream side of the expanded portion 14 in the nozzle 10. Like the first throttle portion 12, the second throttle portion 15 is a portion formed by narrowing from the upstream side to the downstream side, and the downstream end portion of the second throttle portion 15 is cut off. The area (opening area) is smaller than the cross-sectional area (opening area) of the upstream end of the second throttle portion 15. The downstream end of the second throttle portion 15 is the second throat 16. In the nozzle 10, the portion of the second throat 16 serves as the nozzle outlet 18.

By the way, in the conventionally proposed dual throat nozzle, the cross-sectional area of the second throat 16 is set equal to the cross-sectional area of the first throat 13. On the other hand, in the dual throat nozzle 10 used in the fluid thrust direction control apparatus of the present invention, as shown in FIG. 6, the cross-sectional area A 2 * of the second throat 16 is changed to the cross-sectional area A 1 * of the first throat 13 . It is set larger than. Therefore, during non-deflection control in which only the main flow F IN1 is flown into the nozzle 10 without injecting the secondary jet F IN2 , a supersonic flow is generated in the widening part 14, and the above-mentioned “in the widening part 14 The expansion mechanism of the supersonic flow makes it possible to prevent the flow from separating from the inner wall surface of the nozzle 10. Therefore, the second condition that the thrust should not be deflected when it should not be deflected (during non-deflection control) is satisfied. Sectional area A 2 * ratio A 2 * / A 1 * is the relative cross-sectional area A 1 *, the first condition that the reasons already mentioned ( "thrust is deflected when it should deflection", "thrust to deflection In order to suitably satisfy both the second condition of "not deflecting when it should not be performed"), the range of 1.2 to 1.8 is preferable.

Further, a secondary jet injection port 19 for injecting the secondary jet F _IN2 into the nozzle 10 is provided on the peripheral wall portion of the nozzle 10. In the example shown in FIG. 6, the secondary jet injection port 19 is provided in the vicinity of the first throat 13, but for the reason already described (the first condition that "the thrust is deflected when it should be deflected" is satisfied). In order to make it easier), it is preferable to provide it on the inner wall surface of the widened portion 14 in the vicinity of the position where the shock wave fronts intersect when the secondary jet F _IN2 is not injected.

The secondary jet injection port 19 is connected to a gas transfer unit (not shown), and a gas transfer path connecting the gas transfer unit and the secondary jet injection port 19 is opened/closed to open/close the gas transfer path. A valve is provided. _Assuming that the main flow F _IN1 is supplied from the engine combustion chamber, the gas transfer means connected to the secondary jet injection port 19 is a gas transfer passage for transferring the main flow F _IN1 from the engine combustion chamber. , The secondary jet flow F _IN2 may be transferred to the secondary jet flow transfer one.

The number of secondary jet injection ports 19 provided is not particularly limited. However, if the secondary jet injection port 19 is provided only in one place, the thrust can be deflected only to the same side. On the other hand, if the secondary jet injection ports 19 are provided at a plurality of locations, the thrust can be deflected to different sides by switching the secondary jet injection ports 19 for injecting the secondary jet F _IN2 . For example, in the case of the two-dimensional nozzle shown in FIG. 7A, as shown in FIG. 6, the secondary jet injection port 19 has a lower secondary jet injection port 19a and an upper secondary jet injection port 19a. 19 b may be provided, and the secondary jet F _IN2 may be injected from one of the secondary jet injection ports 19 depending on the direction in which the thrust is to be deflected. This makes it possible to change the thrust direction not only on the positive side in the z-axis direction but also on the negative side in the z-axis direction. The angle by which the thrust is deflected can be adjusted by adjusting the opening degree of the on-off valve of the gas transfer passage to adjust the flow rate of the secondary jet F _IN2 .

The principle of deflection of thrust by the fluid thrust control device including the nozzle 10 is as follows. That is, in the fluid thrust direction control device of the present invention, the combustion gas _delivered from the engine combustion chamber (combustion chamber such as rocket engine or jet engine) (not shown) _flows from the nozzle inlet 11 into the nozzle 10 as the main flow F _IN1. It is designed to flow in and jet from the nozzle outlet 18 as a jet F _OUT . By the reaction of the jets F _OUT, the power of the total momentum and opposite with the jet flow F _OUT engine receives a thrust is generated.

Here, when the thrust is not deflected (during non-deflection control), the secondary jet F _IN2 is not injected into the nozzle 10 and only the main flow F _IN1 flows. In the non-deflection control, the nozzle 10 used in the fluid thrust direction control device of the present invention has a momentum that the entire jet flow F _OUT has at the center of the nozzle 10 like the jet flow F _OUT indicated by the broken line arrow in FIG. It is designed to face one side in the direction parallel to the line 10a (the positive side in the x-axis direction). Therefore, thrust is generated in the engine, which is directed to the opposite side (negative side in the x-axis direction).

On the other hand, when it is desired to incline the thrust direction to the positive side in the z-axis direction (when trying to deflect to the upper left direction on the paper surface of FIG. 6 ), the nozzle is discharged from the secondary jet injection port 19 a on the lower side in FIG. A secondary jet F _IN2 is injected into the inside 10. Then, as in the case shown in FIG. 1, the main flow F _IN1 is pushed to the upper side (the positive side in the z-axis direction) in the nozzle 10, but the lower side (toward the lower right direction by the second throttle portion 15). It is bent to the z-axis direction negative side). Therefore, the momentum of the entire jet flow F _OUT ejected from the nozzle outlet 18 has a downward component like the jet flow F _OUT shown by the black arrow in FIG. As a result, the thrust of the engine is deflected in the upper left direction on the paper surface of FIG.

On the other hand, when it is desired to incline the thrust direction to the negative side in the z-axis direction (when attempting to deflect to the lower left direction on the paper surface of FIG. 6 ), the secondary jet injection port 19 b on the upper side in FIG. A secondary jet F _IN2 (not shown) is injected. As a result, the thrust is deflected to the lower left direction on the paper surface of FIG. 6 according to the same principle as in the case where the secondary jet F _IN2 is injected from the lower secondary jet injection port 19a.

Although the case where the nozzle 10 is the two-dimensional nozzle of FIG. 7A has been described above, the same is true when the nozzle 10 is the axisymmetric nozzle of FIG. 7B. However, when the nozzle 10 is an axisymmetric nozzle, it is preferable to provide the secondary jet injection ports 19 at at least three places in a range exceeding 180° around the center line 10a of the nozzle 10. Thus, by adjusting the flow rate of the secondary jet F _IN2 injected from each secondary jet inlet 19, it is possible to change the thrust direction to the y-axis direction positive side or the y-axis direction negative side. become.

2. Second condition confirmation simulation In order to confirm whether or not the dual throat nozzle 10 according to the fluid thrust direction control device of the present invention satisfies the second condition of "not deflecting when it should not deflect", a simulation (first Two-condition confirmation simulation) was performed. Specifically, in the nozzle 10 (FIG. 6) according to the fluid thrust direction control device of the present invention, when only the main flow F _IN1 is flown in without injecting the secondary jet F _IN2 (during non-deflection control) The flow field in the dual throat nozzle 10 and the thrust deflection angle were calculated by numerical simulation.

Regarding the analysis method and conditions of the second condition confirmation simulation performed for the dual throat nozzle 10 relating to the fluid thrust direction control device of the present invention, except for the dimensions of the nozzle 10, in the "Problems to be solved by the invention" column. This is the same as the second condition confirmation simulation performed for the previously proposed dual throat nozzle (nozzle A) described above. That is, regarding the conventionally proposed dual throat nozzle 10, the nozzle 10 is set to the dimensions shown in FIG. 3 (the cross-sectional area of the first throat 13 and the cross-sectional area of the second throat 16 are set to be equal) A condition confirmation simulation was performed. On the other hand, for the dual throat nozzle 10 according to the fluid thrust direction control device of the present invention, the second condition confirmation simulation was performed by setting the nozzle 10 to two sizes shown in FIGS. 8 and 12. In the following, the dual throat nozzle 10 having the dimensions shown in FIG. 8 may be referred to as “nozzle B”, and the dual throat nozzle 10 having the dimensions shown in FIG. 12 may be referred to as “nozzle C”. In each of the "nozzle B" and the "nozzle C" according to the fluid thrust direction control device of the present invention, the cross-sectional area of the second throat 16 is set larger than the cross-sectional area of the first throat 13. .. In the nozzle B, the ratio A ₂ ^* /A ₁ ^* of the cross-sectional area A ₂ ^* of the second throat 16 to the cross-sectional area A ₁ ^* of the first throat 13 is about 1.7. A ₂ ^* /A ₁ ^* is about 1.3.

2.1 Case of "Nozzle B" FIGS. 9, 10 and 11 show the results of the second condition confirmation simulation performed for the "nozzle B" (see FIG. 8) according to the fluid thrust direction control device of the present invention. Indicates. The graph of FIG. 9 shows the time variation of the thrust deflection angle δ during non-deflection control for each random number sequence. FIG. 10 shows the streamlines in the nozzle during non-deflection control for the case of the random number sequence 4 in FIG. FIG. 11 shows the Mach number distribution in the nozzle during non-deflection control for the case of the random number sequence 4 of FIG.

In the conventionally proposed “nozzle A” related to the dual throat nozzle, as shown in FIG. 4, the thrust deflection angle δ greatly varies depending on the random number sequence, and the absolute value thereof is about 4° at maximum. Had also reached. On the other hand, in the "nozzle B" according to the fluid thrust direction control device of the present invention, as shown in FIG. 9, there is no large variation in the thrust deflection angle δ due to the random number sequence, and the thrust deflection angle δ is all In the random number sequence of, the steady state is reached at a value close to 0°.

Further, in the conventionally proposed “nozzle A” related to the dual throat nozzle, as shown in FIG. 5, the nozzle inner streamline (t) in the random number sequence 4 and the random number sequence 10 (random number sequence largely deflected in FIG. 4) is shown. =37.5 in-nozzle) was formed asymmetrically in the vertical direction, and a large separation region was formed despite the non-deflection control in which the secondary jet F _IN2 was not injected. On the other hand, in the “nozzle B” according to the fluid thrust direction control device of the present invention, as shown in FIG. 10, the nozzle inner stream line in the random number sequence 4 (the nozzle inner stream line at t=37.5) is The upper and lower sides are formed substantially symmetrically, and no peeling region is formed.

Furthermore, in the conventionally proposed “nozzle A” related to the dual throat nozzle, the subsonic velocity or the transonic velocity is present in the entire area of the dual throat nozzle 10 in any of the random number sequence 4 and the random number sequence 10. .. On the other hand, in the "nozzle B" according to the fluid thrust direction control device of the present invention, as shown in FIG. 11, the downstream side of the center of the widened portion 14 (a portion near the downstream end of the widened portion 14). A shock wave was formed on the surface, and the supersonic velocity was in a wide range in the widened portion 14 (a wide range from the first throat 13 to the shock wave).

From the above results, it was found that the "nozzle B" according to the fluid thrust direction control device of the present invention satisfies the second condition of "not deflecting when not deflecting".

2.2 Case of "Nozzle C" FIGS. 13, 14 and 15 show the results of the second condition confirmation simulation performed for the "nozzle C" (see FIG. 12) according to the fluid thrust direction control device of the present invention. Indicates. The graph of FIG. 13 shows the time variation of the thrust deflection angle δ during non-deflection control for each random number sequence. FIG. 14 shows the streamlines in the nozzle during non-deflection control for the case of the random number sequence 4 in FIG. FIG. 15 shows the Mach number distribution in the nozzle during non-deflection control for the case of the random number sequence 4 in FIG.

As described above, in the “nozzle C”, the ratio A ₂ ^* /A ₁ ^* of the sectional area A ₂ ^* of the second throat 16 to the sectional area A ₁ ^* of the first throat 13 is about 1.3. Therefore, although the ratio A ₂ ^* /A ₁ ^* is smaller than that of the “nozzle B” having a ratio A ₂ ^* /A ₁ ^* of about 1.7, it is related to the conventionally proposed dual throat nozzle. It is larger than “nozzle A” (ratio A ₂ ^* /A ₁ ^* is 1). As shown in FIG. 13, also in the “nozzle C”, as in the case of the “nozzle B”, the thrust deflection angle δ is in a steady state with a value close to 0° in all the random number sequences. However, in the “nozzle C”, the variation width of the random number sequences 1 to 10 is slightly larger than that in the “nozzle B”.

Further, as shown in FIG. 14, in the “nozzle C” as well, in the same manner as the “nozzle B”, the nozzle inner streamlines (nozzle inner streamlines at t=37.5) are formed substantially vertically, and the peeling region It can be seen that the formation of Further, as shown in FIG. 15, in the “nozzle C” as well, as in the case of the “nozzle B”, a shock wave is formed in the widened portion 14, and a region of supersonic velocity is formed in the widened portion 14. However, in the "nozzle B", the shock wave was formed in the downstream side of the center of the expanded portion 14, whereas in the "nozzle C", the shock wave was formed slightly upstream of the center of the expanded portion 14. It was

From the above results, it was found that the "nozzle C" according to the fluid thrust direction control device of the present invention also satisfies the second condition of "not deflecting when it should not be deflected". However, the "nozzle C" is slightly disadvantageous in the satisfaction of the second condition, such as the variation in the thrust deflection angle δ is slightly larger than that of the "nozzle B". Therefore, if the ratio A ₂ ^* /A ₁ ^* is made too small (too close to 1), it is expected that the second condition will be difficult to be satisfied. From this, it was found that the ratio A ₂ ^* /A ₁ ^* is preferably 1.2 or more.

2.3 Summary of Second Condition Confirmation Simulation In order for the dual throat nozzle to satisfy the second condition "not deflect when thrust should not be deflected" by the above second condition confirmation simulation, It was confirmed that it is effective to make the cross-sectional area A ₂ ^* of the second throat 16 larger than the cross-sectional area A ₁ ^* of the first throat 13. Further, since the second condition both in the case where the cross-sectional area _A ^{1 *} cross section for _A ^{2 *} of the ratio _A ² * _{/ A} ^{1 *} to about 1.3 to about 1.7 is satisfied, the ratio A It was also found that the second condition can be satisfied if ₂ ^* /A ₁ ^* is set to about 1.2 to 1.8.

3. First Condition Confirmation Simulation Subsequently, in order to confirm whether or not the dual throat nozzle 10 according to the fluid thrust direction control device of the present invention satisfies the first condition of “deflect when it should be deflected”, A simulation (first condition confirmation simulation) was performed for the “nozzle B” and the “nozzle C”. Specifically, in the nozzle 10 (FIG. 6) according to the fluid thrust direction control device of the present invention, the flow in the dual throat nozzle 10 when the main flow F _IN1 and the secondary jet F _IN2 are injected (during deflection control). The field and thrust deflection angle were calculated by numerical simulation. Flow rate of the secondary jet _{F IN2} is set to 5% for the total flow rate of the mainstream _{F IN1} and secondary jets _{F IN2.} The injection direction of the secondary jet F _IN2 was set to a direction rotated counterclockwise by 150° from the rightward direction (the positive side in the x-axis direction) parallel to the nozzle center line 10a.

In the simulation for confirming the first condition, the injection positions of the secondary jet F _IN2 (positions of the secondary jet injection port 19) were tested at three positions for each of the “nozzle B” and the “nozzle C”. Specifically, for the nozzle B, the position at which the secondary jet F _IN2 is injected is changed at three positions P ₁ , P ₂ and P ₃ in FIG. 16, and for the nozzle C the secondary jet F ₂ is injected. The position of injecting F _IN2 was changed at _three positions of position Q ₁ , position Q ₂ and position Q _{3 in} FIG. 16 and 17 respectively show the Mach number distributions when only the main flow F _IN1 is flown into the nozzle without injecting the secondary jet F _IN2 . The position P ₁ of the “nozzle B” and the position Q ₁ of the “nozzle C” are both near the first throat 13, and the position P ₂ of the “nozzle B” and the position Q ₂ of the “nozzle C” are both. In the widened portion 14, slightly upstream of the place where the shock wave is formed when the secondary jet F _IN2 is not injected into the nozzle 10 (during non-deflection control), the position P ₃ of the “nozzle B” is The position Q ₃ of the “nozzle C” is located slightly downstream of the place where the shock wave is formed in the expanded portion 14 when the secondary jet F _IN2 is not injected into the nozzle 10 (during non-deflection control). Is becoming In addition, the analysis method and conditions of the simulation are the same as those of the above second condition confirmation simulation.

3.1 Injecting Secondary Jet F _IN2 from P _{1 by} “Nozzle B” FIGS. 18, 19 and 20 show “Nozzle B” (see FIG. 8) according to the fluid thrust direction control device of the present invention. 16) shows the result of the first condition confirmation simulation when the secondary jet F _IN2 is injected from P ₁ in FIG. The graph of FIG. 18 shows the time variation of the thrust deflection angle δ during deflection control for each random number sequence. FIG. 19 shows the streamline in the nozzle during deflection control for the case of the random number sequence 4 in FIG. FIG. 20 shows the Mach number distribution in the nozzle during deflection control for the case of the random number sequence 4 in FIG.

As shown in FIG. 18, the thrust deflection angle δ takes a value close to 0° in all the random number sequences, even during deflection control in which the secondary jet F _IN2 is being injected. It can be seen that the thrust direction is hardly deflected. From this, it was found that the first condition is difficult to be satisfied in the "nozzle B" when the configuration in which the secondary jet F _IN2 is injected from the vicinity of the first throat 13 is adopted.

The cause can be understood from FIGS. 19 and 20. That is, when looking at FIG. 19, the injection of the secondary jet F _IN2, the flow in the nozzle although once peeled from the nozzle inner wall surface, the peeling accidentally eliminated at a point close to the injection point of the secondary jet F _IN2 ing. When the secondary jet F _IN2 is not injected in the “nozzle B”, as shown in FIG. 11 above, a shock wave is formed near the downstream end of the widened portion 14, and most of the widened portion 14 is supersonic. It is considered that the secondary jet F _IN2 was injected from a location far away from the position of this shock wave on the upstream side in the region where the separation of the flow is easy to be eliminated. In fact, looking at FIG. 20, it can be seen that, although the secondary jet F _IN2 is injected, most of the widened portion 14 is in the supersonic region.

3.2 When the secondary jet F _IN2 is injected from Q _{1 by the} “nozzle C” FIGS. 21, 22 and 23 show the “nozzle C” (see FIG. 12) according to the fluid thrust direction control device of the present invention. 17) shows the result of the first condition confirmation simulation when the secondary jet F _IN2 is injected from Q ₁ in FIG. The graph of FIG. 21 shows the time variation of the thrust deflection angle δ during deflection control for each random number sequence. FIG. 22 shows the streamlines in the nozzle during deflection control for the case of the random number sequence 4 in FIG. FIG. 23 shows the Mach number distribution in the nozzle during deflection control for the case of the random number sequence 4 of FIG.

It can be seen from FIG. 22 that the separation of the flow generated near the injection position of the secondary jet F _IN2 is maintained up to the nozzle outlet 18. Furthermore, it can be seen from FIG. 23 that the flow becomes subsonic near the injection point of the secondary jet F _IN2 . As a result, the thrust deflection angle δ is in a steady state with a value close to −12° in all the random number sequences, as shown in FIG. From this, when the cross-sectional area A ₂ ^* of the second throat 16 is made larger than the cross-sectional area A ₁ ^* of the first throat 13 as in the dual throat nozzle according to the fluid thrust direction control device of the present invention (compared to Even when A ₂ ^* /A ₁ ^* is set to be larger than 1) and the secondary jet F _IN2 is injected from the vicinity of the first throat 13, the ratio A ₂ ^* /A ₁ ^{* is obtained.} It was confirmed that the first condition was satisfied when the value was set to be smaller than "nozzle B".

3.3 When the secondary jet F _IN2 is injected from P _{2 by the} “nozzle B” FIGS. 24, 25 and 26 show the “nozzle B” according to the fluid thrust direction control device of the present invention (see FIG. 8). 16) shows the result of the first condition confirmation simulation when the secondary jet F _IN2 is injected from P ₂ in FIG. The graph of FIG. 24 shows the time variation of the thrust deflection angle δ during deflection control for each random number sequence. FIG. 25 shows streamlines in the nozzle during deflection control. FIG. 26 shows the Mach number distribution in the nozzle during deflection control.

It can be seen from FIG. 25 that the separation of the flow generated near the injection position of the secondary jet F _IN2 is maintained up to the nozzle outlet 18. Further, it can be seen from FIG. 26 that the flow is subsonic near the injection point of the secondary jet F _IN2 . As a result, as shown in FIG. 24, the thrust deflection angle δ is a value close to −12° in all random number sequences (a value equivalent to the case where the secondary jet F _IN2 is injected from Q _{1 by the} “nozzle C”). ) Indicates a steady state. However, when the secondary jet F _IN2 was injected from Q ₁ by the “nozzle C”, the time during which the thrust deflection angle δ was in the steady state was around t=25 (see FIG. 21). When the secondary jet F _IN2 is injected from P _{2 by the} “nozzle B”, the thrust deflection angle δ is in a steady state at t<10. Shockwave Therefore, even in the case of using the "nozzle B", the position to inject secondary jet F _IN2, when the nozzle 10 in the not injected secondary jet F _IN2 (undeflected control) In the vicinity of the place where the turbulence is formed (slightly upstream of the shock wave), the first condition may be satisfied with better response performance than in the case where the secondary jet F _IN2 is injected from Q ₁ by the “nozzle C”. It could be confirmed.

3.4 When the secondary jet F _IN2 is injected from P _{3 by the} “nozzle B” FIGS. 27, 28 and 29 show the “nozzle B” according to the fluid thrust direction control device of the present invention (see FIG. 8). 16) shows the result of the first condition confirmation simulation when the secondary jet F _IN2 is injected from P ₃ in FIG. The graph of FIG. 27 shows the time variation of the thrust deflection angle δ during deflection control for each random number sequence. FIG. 28 shows streamlines in the nozzle during deflection control. FIG. 26 shows the Mach number distribution in the nozzle during deflection control.

28, it can be seen that the separation of the flow generated near the injection position of the secondary jet F _IN2 is maintained up to the nozzle outlet 18. Further, referring to FIG. 29, it can be seen that the flow becomes subsonic near the injection point of the secondary jet F _IN2 . As a result, the thrust deflection angle δ is in a steady state with a value close to −7° in all random number sequences, as shown in FIG. Further, the time required for the thrust deflection angle δ to reach a steady state is also short at t<10. Shockwave Therefore, even in the case of using the "nozzle B", the position to inject secondary jet F _IN2, when the nozzle 10 in the not injected secondary jet F _IN2 (undeflected control) It was confirmed that the first condition was satisfied even on the slightly downstream side of the place where the was formed. However, the thrust deflection angle δ becomes smaller than that when the secondary jet F _IN2 is injected from P ₂ by the “nozzle B”.

3.5 Injecting Secondary Jet F _IN2 from Q ₂ with “Nozzle C” FIGS. 30, 31 and 32 show “nozzle C” (see FIG. 12) according to the fluid thrust direction control device of the present invention. 17) shows the result of the first condition confirmation simulation when the secondary jet F _IN2 is injected from Q ₂ in FIG. The graph of FIG. 30 shows the time variation of the thrust deflection angle δ during deflection control for each random number sequence. FIG. 31 shows streamlines in the nozzle during deflection control. FIG. 32 shows the Mach number distribution in the nozzle during deflection control.

It can be seen from FIG. 31 that the separation of the flow generated near the injection position of the secondary jet F _IN2 is maintained up to the nozzle outlet 18. Further, referring to FIG. 32, it can be seen that the flow becomes subsonic near the injection point of the secondary jet F _IN2 . As a result, the thrust deflection angle δ is in a steady state with a value close to −17° in all random number sequences, as shown in FIG. The value "-17°" is close to the value "-19°" of the "nozzle A" described in the "Problems to be solved by the invention" section. From this, it was confirmed that when the secondary nozzle F _IN2 is injected from Q ₂ by the “nozzle C”, the deflection performance equivalent to that of the “nozzle A” may be obtained. Further, even with the same "nozzle C", when the secondary jet F _IN2 was injected from Q ₁ , the thrust deflection angle δ was in a steady state around t=25 (see FIG. 21). It was also confirmed that when the secondary jet F _IN2 was injected from Q ₂ , the thrust deflection angle δ was in a steady state in a short time of t<10.

3.6 Injecting Secondary Jet F _IN2 from Q ₃ with “Nozzle C” FIGS. 33, 34 and 35 show the “nozzle C” (see FIG. 12) according to the fluid thrust direction control device of the present invention. 17) shows the result of the first condition confirmation simulation when the secondary jet F _IN2 is injected from Q ₃ in FIG. The graph of FIG. 33 shows the time variation of the thrust deflection angle δ during deflection control for each random number sequence. FIG. 34 shows streamlines in the nozzle during deflection control. FIG. 35 shows the Mach number distribution in the nozzle during deflection control.

It can be seen from FIG. 34 that the separation of the flow generated near the injection position of the secondary jet F _IN2 is maintained up to the nozzle outlet 18. Furthermore, referring to FIG. 35, it can be seen that the flow becomes subsonic near the injection point of the secondary jet F _IN2 . As a result, as shown in FIG. 33, the thrust deflection angle δ is in a steady state with a value close to −17° in all random number sequences. From this, it was confirmed that even when the secondary nozzle F _IN2 is injected from Q ₃ by the “nozzle C”, the deflection performance equivalent to that of the “nozzle A” may be obtained. However, when the secondary jet F _IN2 was injected from Q ₂ with the “nozzle C”, the thrust deflection angle δ was in a steady state at t<10, while the secondary jet flow _{FIN 2} from the Q ₃ with the “nozzle C” was secondary. It was also confirmed that when the jet F _IN2 was injected, the time required for the thrust deflection angle δ to reach a steady state was slightly longer.

3.7 Summary of First Condition Confirmation Simulation By the above first condition confirmation simulation, in the dual throat nozzle, the sectional area A ₂ ^* of the second throat 16 is made larger than the sectional area A ₁ ^* of the first throat 13, It was confirmed that the first condition can be satisfied even when the second condition is satisfied. In particular, and when the cross-sectional area to the cross-sectional area _A ^{1 *} _A ^{2 *} ratio _A ^{2 *} _{/ A} ¹ * 1.3 before and after (about 1.2 to 1.4), the secondary jet F at the nozzle 10 in when injecting the secondary jet flow F _IN2 from near the position of the shock wave formed in the nozzle 10 in the case that _IN2 only mainstream F _IN1 not injected is flowing, it has also been found that the first condition is easily met.

10 Dual Throat Nozzle 10a Nozzle Center Line 11 Nozzle Inlet 12 First Throttling Section 13 First Throat 14 Spreading Section 15 Second Throttling Section 16 Second Throat 18 Nozzle Outlet 19 Secondary Jet Injection Port A ₁ ^* Cross-sectional Area of First Throat A ₂ ^* Cross sectional area of second throat D ₁ Nozzle inlet opening width F _a Representative streamline F _b Representative streamline F _c Representative streamline F _d Representative streamline F _{IN1 From} engine combustion chamber _Main stream flowing into nozzle inlet F _IN2 Secondary jet stream F _OUT Jet stream jetting from nozzle outlet α ₁ Separation area

Claims (6)

By injecting the secondary jet from the secondary jet injection port provided in the middle of the nozzle to the main flow that flows in the nozzle from the nozzle inlet to the nozzle outlet, the flow of the main stream is changed, and from the nozzle outlet A fluid thrust direction control device for changing the direction of a jet flow,
The nozzle
The upstream end serves as a nozzle inlet, the cross-sectional area of the downstream end is formed to be smaller than the cross-sectional area of the upstream end, and the downstream end has a first throttle portion that is the first throat,
A widened portion which is connected to the downstream side of the first throttle portion and whose cross-sectional area of the downstream end portion is larger than that of the upstream end portion.
It has a second throttle portion which is connected to the downstream side of the widened portion and whose downstream end has a cross-sectional area smaller than that of its upstream end and whose downstream end serves as a second throat. With a dual throat nozzle,
By setting the cross-sectional area of the second throat (referred to as "A ₂ ^* ") to be larger than the cross-sectional area of the first throat (referred to as "A ₁ ^* "), the secondary jet flow is generated in the nozzle. During non-deflection control in which only the main flow is introduced without injecting, supersonic flow is generated in the expanded part and it is prevented from separating from the inner wall surface of the nozzle, so that unintentional thrust deflection does not occur. A hydraulic thrust direction control device characterized by the above.
The fluid thrust direction control according to claim 1, wherein the ratio A ₂ ^* /A ₁ ^* of the cross-sectional area A ₂ ^* of the second throat to the cross-sectional area A ₁ ^* of the first throat is set to 1.2 to 1.8. apparatus.
The fluid thrust direction control device according to claim 1, wherein the secondary jet injection port is provided in the widened portion.
When the cross-sectional areas of the first throat and the second throat are respectively A ₁ ^* and A ₂ ^* , the shock wave upstream Mach number is M ₁ , and the specific heat ratio is γ,
Substituting the value of the ratio A ₂ ^* /A ₁ ^* into the left side of Equation 6 below, and the cross-sectional area A _S obtained by simultaneous equations 6 and 7 below,
Secondary jet inlets, the expanded portion, the hydrodynamic thrust direction control device according to claim 3, wherein provided in the portion which becomes 0.9 to 1.1 times the cross-sectional area of the cross-sectional area A _S.


The fluid thrust direction control device according to any one of claims 1 to 4, wherein the nozzle has the same cross-sectional shape parallel to one plane including the center line.
The fluid thrust direction control device according to any one of claims 1 to 4, wherein a nozzle having a shape of a rotary body having a center line as an axis is used as the nozzle.