RU2581894C1 - Method of descending separated space rocket stage and device therefor - Google Patents

Abstract

FIELD: astronautics.

SUBSTANCE: invention relates to aerospace engineering and can be used during a descent of a space rocket stage separation part (SRSSP). SRSSP comprises a control and navigation system, a fuel compartment, a system of gasification of liquid fuel residues, 2 opposite to each other discharge nozzles and piromembranes. SP is stabilized in statically stable position; use is made of energy based on gasification of liquid residues of unused components of rocket fuel and there is ensured an angular position in space corresponding to the minimum angle of attack during entrance in dense atmosphere; there is performed and aerodynamic maneuver, ensured control of movement of SP centre of mass and around the centre of mass separation by separate discharge of products of gasification (PG) from fuel and oxidizer tanks via adjustable nozzles of gas-reactive system (GS) and performed a non-momentary discharge of remaining gasification products from tanks through GS discharge nozzles.

EFFECT: invention allows to increase accuracy of SP stabilization at standard perturbations, reduce the weight and size of the system of PG utilization and SP oscillation frequency.

2 cl, 4 dwg, 2 tbl

Description

The present invention relates to rocket and space technology and can be used to reduce the areas of incidence of the separating parts (OCH) of the stages of space rockets (ILV).

One of the main problems associated with the reduction of the technogenic impact of ILV launches on the environment is the presence of PF, which leads to the need to allocate significant areas for areas of PF incidence, the use of energetically non-optimal removal schemes, and the presence of undeveloped residues of liquid fuel in PF tanks leads to explosions in orbits and in the atmospheric section of the descent trajectory, spills of fuel components in the areas of incidence, an increase in the dispersion of fragments of OCh, etc.

The well-known "Method of launching the separating part of the stage of a space rocket" (patent RU No. 2475429, IPC B64G 1/26, publ. 02.20.2013), according to which the program for controlling the operation of gas rocket engines and the movement of the high-frequency stages of space rockets is divided into extra-atmospheric and atmospheric sections, which are divided into a finite number of time intervals and determine the program of angular turn and movement of PF at each interval.

Closest to the claimed one is "A method of launching a separating part of a space rocket on liquid fuel components in a predetermined area of incidence and a device for its implementation" (patent RU No. 2414391, IPC B64G 1/26, B64C 15/14, publ. 03.20.2011) . The method is based on stabilization of the RP by the forward position of the propulsion system, orientation and controlled movement of the RP, after separation of the RP, the descent maneuver to the specified drop area is carried out due to the energy contained in the undeveloped residues of the liquid fuel components based on their gasification and supply to the gas rocket propulsion system (GzRDU ) descent, while controlling the movement of the center of mass and around the center of mass of the HF is carried out by the deviations of the GzRDU chambers, and the OH at the time of the shutdown of the GzRDU provide an angular position in a simple anstve corresponding to the minimum angle of attack as it enters into the atmosphere, and spin OCH around its longitudinal axis. The value of the undeveloped residual liquid fuel is formed taking into account the descent of the OCh to the specified drop region, and the completion of the active section of the maneuver of descent is carried out before entering the dense layers of the atmosphere and maintaining controllability of the OCh with the help of the GzRDU cameras.

The separating part of a space rocket on liquid fuel components includes a control and navigation system, a gasification system, and four chambers are installed on the upper bottom of the fuel compartment, each of which is equipped with a drive, and the gasification system has an autonomous gas generator with a membrane system for supplying fuel components, acoustic vibration pathogens located on the coolant inlet fittings in the fuel tanks.

The disadvantages of the known technical solutions include:

- the presence of gas turbine propulsion system, which requires the use of heavy combustion chambers, each of which is installed in a single-stage controlled drive, the mass of gas turbine propulsion system is many times greater than the mass of gas nozzles due to the high temperature of the combustion products;

- GzRDU is necessary when implementing pulses of descent from orbit, changes in the point of incidence (control of the center of mass), but is not effective in the stabilization mode (control of the center of mass) when flying in the atmospheric section of the descent trajectory (ATS), because drive design, pumping angles, lead to a significant weighting of the structure;

- during gasification of fuel in tanks, the composition of gasification products coming from tanks to the gas turbine engine is variable in time, which leads to the fact that the combustion process in the chamber is unstable with a variable flow rate and, accordingly, a variable draft;

- the possibility of aerodynamic maneuvering is not used, which, as shown by the estimates for this class of entry paths and the parameters of the displacement of the drop points of the PF, is more effective than imparting an impulse to the center of mass of the PF with the help of the gas turbine engine.

The technical result of the proposed technical solution is the elimination of these shortcomings, improving the accuracy of stabilization of PF under standard disturbances, reducing the weight and size of the GHG utilization system and the frequency of PF oscillations.

The specified technical result is achieved by the fact that in the method of lowering the separating part (OCh) of the launch vehicle stage (LV) on the liquid components of rocket fuel (SRT) to a predetermined area of incidence, based on the stabilization of the OCh in a statically stable position, the use of energy contained in unused the remnants of liquid CMT based on their gasification, providing an angular position in space corresponding to the minimum angle of attack when it enters the dense atmosphere, according to the claimed invention, after separation descent control to a predetermined area of fall is carried out on the atmospheric part of the path of descent of OCh due to aerodynamic maneuver, while the movement of the center of mass and around the center of mass of OCh is controlled by separate discharge of gasification products (GH) from the fuel and oxidizer tanks through adjustable nozzles of the gas reactive system (GDS) ), after the completion of the maneuver, they carry out an instantaneous discharge of the remaining GHGs from the tanks through the discharge nozzles of the GDS.

In the part of the device for implementing the method, the indicated technical result is achieved in that in the OCh rocket, which includes a control and navigation system, a fuel compartment, a gasification system for liquid fuel residues, according to the claimed invention, in the plane of stabilization of pitch (yaw), roll at maximum away from the center of mass, 2 discharge nozzles are installed opposite to each other, connected by GHG supply lines through pyromembranes, adjustable valves with corresponding tanks.

The essence of the technical solution is illustrated by the drawing, where

- in FIG. 1 illustrates the actions of the method;

- in FIG. 2 is a diagram of the operation of the GDS in the pitch channel by the example of the second stage IL of the Soyuz 2.1.v rocket launcher (block I);

- in FIG. 3 shows a diagram of the operation of the GDS in the roll channel;

- in FIG. Figure 4 shows the parameters of the descent trajectory by the example of the first stage IL of the Soyuz-2.1.v type.

Launching the ILV in the active section of the trajectory of the first stage 1 is carried out according to the optimal pitch program. After separation of the first stage OCh at the point of trajectory 2, in accordance with the prototype, the OCh maneuver is carried out with the help of the turbojet engine, which ensures further flight of the OCh along the ballistic descent trajectory, consisting of an extra-atmospheric section 3, entry into the atmosphere 4 and atmospheric section 5 with the fall of the OCh to the Earth set point 6. To ensure a stable flight of the PF at the entrance, the atmosphere in accordance with the prototype provide a twist of the PF around the longitudinal axis.

In the event that you do not maneuver the launch of the VL, then after separating the VL at point 2, it will descend along the nominal ballistic trajectory of 7.8 with a fall to point 9, which, as a rule, with the optimal program for launching an ILV, is outside the selected fall region to which the given aiming point 6 belongs.

In accordance with the proposed method, the maneuver of the launch of the OCh to a given aiming point 6 is carried out using GRS nozzles in the atmospheric section of the descent path 10 by using the normal component of the aerodynamic force.

Separate discharge of GHG gasification from O, G tanks through GDS nozzles is due to the following:

- minimization of the mass of the GHG supply lines, because GHG discharge nozzles are in close proximity to the O, G tanks;

- no chemical interaction of GHGs is provided for in the GRS nozzles;

- to solve the problem of stabilizing the VL during its controlled flight, the thrust values of the nozzles for the discharge of the GDS are sufficient;

- GHG discharge through the GDS nozzles begins after reaching the specified pressure in the O, G tanks when hot gases are supplied to the tank (the gasification system exits to the specified mode).

The momentless GHG discharge from O, G tanks is carried out on the basis of the following conditions:

- ensuring the strength of the design of the tanks with increasing pressure;

- the need to expend toxic GHGs until the fall of OCh to the Earth's surface.

Table 1 shows a comparative analysis of two methods of descent: applying an impulse to the center of mass of the RP using the HGPR and aerodynamic maneuver for the first stage RP using the GDS on the automatic telephone exchange.

From the results of the comparative analysis shown in Table 1, it follows that for the first stage ILV, which performs most of the trajectory of motion in the atmosphere, the use of aerodynamic maneuver using the GDS is preferable in comparison with the use of GDDS.

At step 11, in the pitch plane X ₁ ОY ₁ , nozzles for dumping 12, 13 of gasification products from tank (G) and tank (O) 14, 15 are installed, providing control moments relative to the center of mass 16 to compensate for aerodynamic disturbing moments applied to the center of pressure 17 The thrust control of the nozzles for the discharge of gasification products from the tank (G), (O) is carried out by adjustable valves 18, 19. The nozzles for the discharge of gasification products 20, 21 from the tank (O) in the roll channel are connected through an adjustable valve 22, and the discharge nozzles 23, 24 gasification products from the tank (G) is connected s through an adjustable valve 25. The coolant is supplied to the tanks (G), (O) from gas generators 26, 27.

After separating OCH 11 at point 2 of the descent trajectory, gas generators 26, 27 of the gasification system are started. After reaching the specified pressure in the tanks (O), (G), pyromembranes 28, 29, respectively, are opened. Gasification products enter through adjustable valves 18, 19, 22, 25 from tanks (G), (O) to nozzles for discharging gasification products 12, 13, 14, 15, 20, 21, 23, 24.

перпендикулярно продольной оси OX₁.At OCH 11, at a distance L of _grcG from the center of mass 16, 2 nozzles for dumping SG 12, 13 from the tank (G) are installed opposite to each other relative to the longitudinal axis OX ₁ and create thrust

perpendicular to the longitudinal axis OX ₁ .

The control moments in the pitch channel from the nozzles of the GHG discharge from the tank (G) will be:

Similarly, nozzles for dumping the GHG from the tank (О) 14, 15 are installed, which create control moments in the pitch channel:

These control moments are formed simultaneously with the use of GH from tanks (O) and (G), so you can write:

The regulation of the values of the control moments is provided by changing the thrusts of the discharge nozzles of the GDS:

by changing the second GHG flow rate through nozzles 12, 13, 14, 15 by control valves 18, 19, as a result of which the thrust of each nozzle can vary in the interval [0, P _max ].

The nozzles for the discharge of PS from the tank (O) 20, 21 and the control valve 22 are installed opposite the nozzles for the discharge of PS from the tank (G) 23, 24 with the control valve 25 at distances R _GRS from the longitudinal axis OX ₁ . The most preferred location of the GDS along the roll from the point of view of minimizing the supply of gas lines between the tanks (O) and (G).

The control moments in the roll channel are formed by analogy with the control moments in the pitch channel M _z1 , namely, by dumping the steam generator from the tanks (О), (Г):

The nozzle thrust in the roll channel is regulated using adjustable valves 22, 25 in the range [0, P _max ].

The control in the yaw channel is carried out by the same composition of the GHG discharge nozzles, while the OCh is rotated around the longitudinal axis OX ₁ by 90 °. Given the low frequencies of the stabilization oscillation process (Fig. 4), it becomes possible to use roll maneuver and refuse to install additional 4 GHG reset nozzles for control in the yaw channel.

, коэффициентами настроек автомата стабилизации (см., например, кн. 1 Разоренов Г.Н., Бахрамов Э.А., Титов Ю.Ф. Системы управления летательными аппаратами (баллистическими ракетами и их головными частями). М.: Машиностроение, 2003. - 583 с.) при движении на атмосферном участке спуска).In the general case, it is possible to install GHG discharge nozzles in the yaw channel, as well as a specific decision on the composition of the gas distribution system, i.e. additional installation of discharge nozzles in the yaw channel is taken depending on the dynamic characteristics of the frequency response (frequencies and amplitudes of stabilization oscillations of the frequency response, which are determined by the efficiency of the governing bodies

, the coefficients of the settings of the stabilization automaton (see, for example, book 1 Razorenov GN, Bakhramov EA, Titov Yu.F. Control systems for aircraft (ballistic missiles and their warheads). M: Engineering, 2003 . - 583 p.) When driving in the atmospheric section of the descent).

With the proposed method of descent (using aerodynamic action to offset the point of fall of the PF), the GDS serves to form a control moment M _y , which balances the aerodynamic moment M _a when the PF moves with a balanced angle of attack α, determined from the condition of the PF to point 6.

The angular stabilization system solves the problem of working out the required angle of attack α _P and generates a control moment M _y , which is calculated by the formula:

где:

Where:

- коэффициент нормальной составляющей аэродинамической силы,

is the coefficient of the normal component of the aerodynamic force,

q, S - velocity head and midship midship area, respectively,

x _D , x _C - coordinates of the centers of mass and pressure of the OF,

k _ω , k _α are the gains of the stabilization system for the mismatch of the angular velocity (ω-ω _П ) and the deviation angle (α-α _П ) from the program path.

The first term provides the program value of the angle of attack α _P , the second and third form feedback on the speed and the mismatch from the program path, ensuring the quality of the transition process of the angular stabilization system. This takes into account the limitation:

To ensure the software value of the angle of attack α _{P, the} value of the control moment of the GDS is determined in accordance with (6), (7). Due to the constraint on the control moment (7), the actual angle of attack α can be less than the required α _P.

In FIG. Figure 4 shows the parameters of the descent trajectory using the example of the Soyuz-2.1.v type LV first-stage launcher, the dotted line shows program values, the solid one shows the actual ones: trajectory angle θ (t), pitch angle ϑ (t), angular velocity ω (t) , the actual α (t) and the required angle of attack α _P (t), the transverse aerodynamic force Y ₁ (t) with the initial data given in table. 2

From the above results it follows that the proposed method of descent and a device for its implementation are efficient and effective for lowering the first stage of the ILV to the automatic telephone exchange:

- provide high accuracy of the stabilization of the IF under standard disturbances and, accordingly, small deviations of the point of incidence from the calculated point (0.18 km);

- they allow providing a shift in the point of incidence of the OC (up to 30 km, which corresponds to 5% of the initial range), this value can be significantly increased (up to 20%), for this it is necessary to increase the permissible angle of attack, the thrust of the nozzles of the gas distribution system;

- the frequencies of the OCh are small, which makes it possible to use the installation of GDS nozzles in only one channel (pitch or yaw);

- a reduction in the mass of the GHG utilization system is achieved by more than 20% compared with the prototype due to the absence of a fuel supply line to the gas turbine propulsion system, the gas turbine propulsion chamber and drives, the mounting frame of the gas turbine propulsion system and drives.

Claims (2)

1. The method of lowering the separating part (OCh) of the space rocket stage on the liquid components of rocket fuel to a predetermined area of incidence, based on the stabilization of the OCh in a statically stable position, the use of energy, contained in the undeveloped residues of the liquid components of rocket fuel based on their gasification, providing an angular position in space corresponding to the minimum angle of attack when it enters the dense layers of the atmosphere, characterized in that after separation of the OCh, the descent control to a given paradise he falls are carried out on the atmospheric part of the path of descent of the HF due to aerodynamic maneuver, while the movement of the center of mass and around the center of mass of the HF is controlled by separately discharging the gasification products from the fuel and oxidizer tanks through the adjustable nozzles of the gas-reactive system, after the completion of the maneuver, they carry out the instantaneous discharge of the remaining products gasification from tanks through nozzles discharge gas-reactive system. 2. The detachable part of a space rocket, including a control and navigation system, a fuel compartment, a system of gasification of liquid fuel residues, characterized in that in the planes of stabilization of pitch, yaw, and roll at a maximum distance from the center of mass, 2 discharge nozzles are installed opposite to each other, connected by highways supplying gasification products through pyromembranes, adjustable valves with corresponding tanks.

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