JPH06300499A - Missile - Google Patents

Abstract

(57) [Summary] [Purpose] By providing a folding mechanism or a deployment mechanism on the stabilizing wings of a flying vehicle and controlling the static stability of the airframe when turning by thrust deflection during combustion of a propulsion device, Get a high-turning vehicle that can make good turns. [Structure] The stabilizer blade 3 having a folding mechanism and the expansion device 4 close the stabilizer blade when thrust is being deflected, and open the stabilizer blade when it is detected that combustion of the propulsion device is completed.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a flying body which makes a high turning motion by a thrust deflection system.

[0002]

2. Description of the Related Art FIG. 6 (a) is an outline of a flight trajectory of a flying body that turns by a thrust deflection method. In the figure, 13 is a flying body, 14 is a vector direction of thrust after deflection, and 15 is a vector direction.
Is a vector direction of thrust in a direction perpendicular to the machine axis, 16 is a velocity vector direction, and 17 is a flight trajectory. Figure 6
(B) A comparison of flight trajectories at the time of turning by the thrust deflection system and the aerodynamic steering system. In the figure, 18 shows the flight trajectories in the case of the thrust deflection system and 19 in the case of the aerodynamic steering system. . FIG. 7 shows a typical example of a conventional thrust deflector, in which 1 is a nozzle, 2 is a vane that deflects combustion gas, 20 is propellant, 21 is an actuator that drives the vane, and 22 is thrust. Deflection type autopilot device 23 is a stabilizing wing fixed to the rear part of the airframe.

Next, a conventional device will be described. The vane 2 deflects the combustion gas to generate a moment in the flying object. This moment causes the flying body to rotate, and the vector direction of the thrust of 14 is directed to the required turning direction, thereby causing the turning motion shown in 18.

FIG. 8 shows the directions in which the load generated by the thrust deflection generated in the flying vehicle during turning and the load aerodynamically generated in the stabilizing blades work. Reference numeral 15 in the figure indicates the direction perpendicular to the thrust axis. The component, 16 is the velocity vector of the flying object, 24 is the lift generated on the stable wing, 25 is the angle of attack, and 26 is the center of gravity of the flying object. As described above, in the flying vehicle which is turning by the thrust deflection method, the direction of the moment acting by the thrust deflection is opposite to the direction of the moment acting by the lift generated on the stabilizing blade. Further, FIG. 9 shows the relationship between the angle of attack of the flying body and the aerodynamic moment coefficient generated by the lift force generated on the stabilizer blade. The aerodynamic moment (static stability) of the stabilizer blade increases in proportion to the angle of attack. .

Further, FIG. 10 shows the relationship between the load generated after the launch of the flying object and the time. In the figure, 27 indicates the load generated by the aerodynamic force in the case of the thrust deflection angle system in the single thrust. In the thrust deflection method, the load generated is constant without depending on the velocity of the flying object, but in the case of aerodynamic load, the load generated depends on the velocity (dynamic pressure) of the flying object, so the flight after launch is It increases according to the accelerated speed of the body.

As can be seen from FIGS. 8 and 10, in the conventional thrust deflection type flying vehicle, in the case of the low acceleration type, the increase in the load due to aerodynamic force is small, so the thrust deflection largely contributes to the initial turning performance. In the case of a high acceleration type such as No. 28, the load (static stability) generated on the stabilizing blade has a great influence of the moment action (static stability) that is a reverse hand with respect to the load generated by the thrust deflection. There is a problem that the turning performance is hindered, or an additional thrust deflection angle is needed to offset this counter-dominant moment action.

[0007]

In a high-speed flying vehicle that turns by the conventional propulsion force deflection method, the effect of static stability during turning by the propulsion force deflection method is strong, and the turning performance by the propulsion force deflection method is reduced. However, there is a problem in that a large thrust deflection angle is required to offset the static stability.

In order to solve the above-mentioned problems, the present invention uses a propulsive force deflection system to adjust the deployment angle of the stabilizer blades of a flying vehicle during turning to optimally control the effect of static stability. The purpose is to realize high turning flight by the force deflection method.

[0009]

A high-turning vehicle according to the present invention comprises a stabilizing blade having a folding mechanism and a deploying device which outputs a deploying command for the stabilizing blade after combustion of a propulsion device.

Further, the high-turning vehicle according to the present invention has a stabilizing blade having a mechanism capable of being deployed at an arbitrary angle, a drive unit for deploying the stabilizing blade, and an optimal deployment angle of the stabilizing blade during combustion of the propulsion device. Is provided with a control device for calculating and outputting.

[0011]

The high-turning projectile according to the present invention has a thrust-deflecting device for turning the projectile by deflecting the thrust, a stabilizing wing having a deploying mechanism, and a control system for controlling the deploying angle of the projecting thrust. It is possible to control the static stability generated by the stabilizing blade during the turning by, and to realize an efficient high turning.

[0012]

【Example】

Example 1. An embodiment of the present invention will be described below with reference to the drawings. FIG. 1 shows an example in which a stabilizer having a folding mechanism is attached to a flying body having a thrust deflecting device. Reference numeral 1 is a propulsion device nozzle, 2 is a vane, 3 is a stabilizing blade, and 4 is a deploying device.

FIG. 2 shows an example in which a stabilizer having an arbitrary expansion angle is attached to a flying body also having a thrust deflector. Reference numeral 5 is a stabilizer blade, 6 is a drive section, and 7 is a control section.

Further, FIG. 3 shows the structure of the control section, in which 8 is a flight speed and angle of attack detection device, 9 is a vane deflection angle detection device, 10 is a required aerodynamic moment calculation device, and 11 is a device.
Is a stable blade required expansion angle calculation device, and 12 is an expansion angle command to be output.

FIG. 4 shows the relationship between thrust force and time.
Fig. 5 shows an example, and Fig. 5 shows the relationship between the angle of attack of the flying object and the aerodynamic moment with the expansion angle of the stabilizing blade as a parameter, where a is the expansion blade and c is the expansion. The case where the blade is fully closed, and b shows the case where the expansion angle is in the middle. The relationship between the angle of attack and the aerodynamic moment coefficient in FIG. 5 is measured by a normal wind tunnel test using the deployment angle and the velocity as parameters and stored in a database.

Next, the operation of the embodiment will be described. The flying body is launched with the stabilizing wings 3 closed, and in the course of turning by the deflection of the thrust by the vanes 2, it prevents the generation of a counter-dominant moment due to the static stability of the stabilizing wings. Further, the thrust pattern shown in FIG. 4 is pre-stored in the deploying device 4, and the combustion time and the flight time shown in FIG. 4 are compared at any time and drastically reduced when the combustion of the propulsion device is actually finished. By detecting the acceleration of the flying body in the machine axis direction, when it is determined that combustion has ended, the stabilizing blade that had been closed until then is deployed.

On the other hand, the control unit 7 uses the flying velocity and attack angle detection device 8 to calculate the angle of attack calculated by each velocity component in the machine axis direction of the flying object and in the direction perpendicular to the machine axis, and the tangent component of each of these velocity components. Detect and. Further, the vane deflection angle detection device 9 calculates the vane deflection angle, that is, the moment (MT) to be generated by thrust deflection, which is calculated by "Equation 1", while the turning rate is calculated by a general control loop. Calculate the total thrust deflection and aerodynamic moment that optimizes. The required aerodynamic moment calculation device 10 compares the optimum total moment calculated here with the moment (MT) obtained by the aforementioned thrust deflection, and calculates the required aerodynamic moment amount given by the difference. Furthermore, the required stable blade deployment angle calculation device 11 stores the relationship between the attack angle and the aerodynamic moment coefficient with the deployment angle of the stable blade as a parameter corresponding to the flight velocity as shown in FIG. From the velocity detected by the angle-of-attack detecting device 8, the angle of attack, and the required aerodynamic moment amount calculated by the required aerodynamic moment calculation device 10, the aerodynamic moment coefficient (Cm) calculated by "Equation 2" is calculated. From the value and the angle of attack at this time, the required deployment angle of the stabilizing blade is calculated from the relationship shown in FIG. Then, in the expansion angle command 12, the required expansion angle command of the drive unit 6 is output.

[0018]

[Equation 1]

[0019]

[Equation 2]

During the turning by the above thrust deflection, the stabilizing blade 3 having the folding mechanism or the stabilizing blade 5 having the deploying mechanism with an arbitrary amount is controlled by the deploying device 4 and the controller 7 to open and close and deploy the blade. Therefore, compared to the conventional method, the action of the asymmetrical moment of aerodynamics in high turning due to thrust deflection can be reduced, efficient turning can be performed, and as a result the required maximum thrust deflection angle can be made smaller than the conventional method. is there.

[0021]

As described above, according to the present invention, the influence of the averse moment (static stability) due to aerodynamics, which has been a problem when the vehicle makes a high turn by thrust deflection at a high speed in the related art, is reduced and the efficiency is improved. There is an effect that the turning can be performed and the maximum thrust deflection angle can be reduced by the deflection angle required to cancel the aerodynamic moment.

[Brief description of drawings]

FIG. 1 is a view showing an example in which a stabilizer according to the present invention is equipped with stabilizing wings having a folding mechanism.

FIG. 2 is a diagram showing an example in which a stabilizing wing having a deployment mechanism is attached to the flying object of the present invention.

FIG. 3 is a schematic diagram of a configuration of a control unit of the present invention.

FIG. 4 is a diagram showing an example of a relationship between a combustion time of a propulsion device and a propulsive force.

FIG. 5 is a diagram showing an example of the relationship between the angle of attack of the flying object and the aerodynamic moment coefficient, with the deployment angle of the stabilizing wings as a parameter.

FIG. 6 is an explanatory diagram of flight trajectories by a thrust deflection system and an aerodynamic steering system.

FIG. 7 is a diagram showing an outline of a conventional thrust deflector.

FIG. 8 is a diagram showing a relationship between a direction of force due to thrust deflection acting on a flying vehicle during turning and a direction of force due to aerodynamic force generated on a stabilizing blade.

FIG. 9 is a diagram showing an example of the relationship between the angle of attack of a flying object and the aerodynamic moment coefficient.

FIG. 10 is a diagram comparing the dynamic pressure of a flying object and the generated turning load between a thrust deflection method and an aerodynamic steering method.

[Explanation of symbols]

 1 Nozzle 2 Vane 3 Stabilizing Blade 4 Deploying Device 5 Stabilizing Blade 6 Drive Unit 7 Control Unit 8 Flying Velocity and Angle of Attack Detection Device 9 Vane Deflection Angle Detection Device 10 Required Aerodynamic Moment Calculation Device 11 Stabilized Blade Required Deployment Angle Calculation Device 12 Deployment Angle command 13 Flying body 14 Thrust vector direction 15 Thrust vector direction perpendicular to machine axis 16 Velocity vector direction 17 Flying locus 18 Flying locus in case of thrust deflection system 19 Flying in case of aerodynamic steering system Trajectory 20 Propellant 21 Actuator 22 Autopilot device 23 Stabilizer wing 24 Lifting force generated on the stabilizer wing 25 Angle of attack 26 Center of gravity of flying body 27 Turning acceleration in the case of thrust deflection method 28 Turning acceleration in the case of aerodynamic steering method

Claims (2)

[Claims] 1. In a high-turning projectile, a thrust deflector that deflects thrust during combustion by a propulsion device, a stabilizing wing with a folding mechanism attached to the fuselage, and the end of combustion of the propulsion device. A flying object comprising: a deployment device that detects the acceleration of the body and outputs a deployment command for the stabilizing wing. 2. A high-turning projectile, a thrust deflecting device for deflecting thrust during combustion by a propulsion device, a stabilizer wing attached to the fuselage, having a mechanism with an arbitrary expansion angle, and the above-mentioned stabilizer wing. It is equipped with a drive unit that opens and closes the vehicle, and a control unit that detects the velocity, attack angle, and thrust deflection angle of the flying object, calculates the optimal expansion angle of the stable blade based on the detected information, and outputs a command to the drive unit. A flying object characterized by what you have done.