RU2475429C1 - Method of spacecraft stage separation part descent - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aerospace engineering and may be used for programmable displacement of coordinates of spacecraft separation stages fall points. Rocket gas engine and separation stages control program is divided into extra-atmospheric and atmospheric sections. Said sections are divided into finite number of time intervals to define the program of separation stage angular turn and motion at every said interval.

EFFECT: complete combustion of liquid propellant components, varying and lowering fall points.

2 cl, 2 dwg

Description

The invention relates to rocket and space technology and can be used to bring the spent accelerator - the separable part of the first (OCh) stage of a space rocket (ILV) to a limited area of impact to reduce the effect of the rocket on the environmental condition of the operating area.

There is a method of launching the ILV accelerator into the landing zone according to patent RU No. 2043954, B64G 1/24 according to the application No. 5035363/23 of 04/01/1992, where after-separation the stabilizer is stabilized by the forward motor, they are controlled by aerodynamic control wheels in pitch channels and yaw, install a radar on board the PF, a beacon at the point of incidence, etc.

The use of such a technical solution is fraught with technical and operational problems, which, ultimately, make this approach economically costly and impractical, at least at the current level of development of rocket and space technology.

Closest to the proposed technical solution is the method of returning to the cosmodrome the reusable first stage of the rocket according to patent RU No. 2309089, B64G 1/14 according to application No. 2006110150/11 of March 29, 2006, where the launch of the VL stage of the ILV to the cosmodrome area is carried out by multiple the inclusion of mid-flight and steering engines of the primary stage of the primary stage.

The use of this technical solution is associated with significant costs of liquid components of rocket fuel (CRT), problems of multiple launch of a marching rocket engine, etc.

The aim of the invention is to reduce the impact of ILV on the ecological state of the area of operation by increasing the efficiency of managing the release of PF to a given area of its fall and the full generation of MCT residues.

The object of the invention is achieved by the fact that in the known method of lowering the IF, based on the turn of the IF in a statically stable position after it is separated from the ILV, applying a pulse to the IF, aerodynamic drag during descent, the following actions are added, namely:

1.1. Program angular motion (pitch angle, yaw) OCH the shutter portion after the turn on pulse application direction is divided into areas outside the atmosphere and atmospheric flight, movement on exoatmospheric plot trajectory is divided into a finite number S _ext time intervals and angular rotation program OCH each the i-th time interval (i = 1, 2 ... S _ext ) is determined from the condition of the maximum change in the increment of the range of the point of fall of the VL in the passive flight from the end of the i-th current time interval according to the formula:

Where

ΔV _i is the velocity impulse applied at an angle ϑ _i on the i-th time interval by 4 steering chambers of a gas rocket engine (GRD), y ₀ , V _x0 , V _y0 , g ₀ are the coordinates, velocities of the center of mass of the PF and acceleration of the gravitational field Earth at the beginning of the i-th time interval.

1.2. The movement on the atmospheric portion of the flight path is divided into a finite number of time intervals S _at , and the program for the angular rotation of the optical frequency range at each j-th time interval (j = 1, 2 ... S _at ) is determined from the condition for creating an aerodynamic moment not exceeding, for example, the control the moment of the GRD steering chambers, strength conditions, etc., and providing the maximum change in the increment of the range of the drop point of the PF in passive flight from the end of the current j-th time interval to the point of drop of the PF, which is determined by the formula:

where y _jк , V _xj , V _yjк , g _jк are the coordinates of the velocities of the center of mass of the PF and the acceleration of the Earth's gravitational field at the end of the j-th time interval.

1.3. The total length of the control sections and the ratio of their durations:

- невыработанные остатки жидкого топлива в баках ОЧ, которые газифицируются и подаются в ГРД, каждая камера которого установлена в управляемый привод;

- массовый секундный расход газифицированного топлива через ГРД определяют из условия достижения максимальной дальности точки падения ОЧ.τ _I is the duration of the control sections;

- undeveloped residues of liquid fuel in the tanks of the HF, which are gasified and supplied to the main engine, each chamber of which is installed in a controlled drive;

- the mass second consumption of gasified fuel through the engine is determined from the condition of reaching the maximum range of the point of fall of the GP.

2. The essence of the proposed method actions is illustrated by the following materials.

2.1. The separation of the flight path of the PF to control sections is shown in figure 1:

- Turn OCh in the direction of acceleration (pos. 0-1),

- extra-atmospheric (pos. 1-2),

- atmospheric (pos. 2-3).

Figure 2 shows the placement of the GRD chambers for testing control actions, each of which is installed in a controlled single-stage drive.

To create control actions in the pitch channel (M _z1 ), cameras 8, 9 are deflected in planes parallel to the plane Y ₁ O ₁ X ₁ .

To create control actions in the yaw channel (M _y1 ), the chambers 10, 11 are deflected in planes parallel to the plane X ₁ O ₁ Z ₁ .

To create control actions in the roll channel (Mx ₁ ), all cameras 8-11 are used.

The value δL (1) for estimating the increment of the flight range (pos. 4, 5 in Fig. 1) of the reference point from the point with coordinates x ₀ , y ₀ , V _x0 , V _y0 in the acceleration section (pos. 1-2 in Fig. 1) obtained on the basis of an analytical solution of the system of equations describing the passive flight of the IF under the assumptions: g = g ₀ = const (the Earth is flat), there is no atmosphere (see book 1 Yu. G. Sikharulidze. Ballistics of aircraft. M: Science 1982, p. 69).

In accordance with the actions of the proposed method, the division of the path of the plot (pos. 1-2 in figure 1) is carried out on S _ext time intervals Δτ _i . At each time interval Δτ _i with the help of a hydraulic pulse impulse ΔV _{i is} applied.

With initial conditions:

the range is determined in the passive flight of the VL and, accordingly, the range increment (2) obtained by imparting a pulse ΔV _i with the orientation ϑ _i . Solving the trigonometric equation (1) numerically, the optimal value ϑ _{iopt is determined} . Next, the transition to the next time interval Δτ _{2 is made} , and the determination procedure ϑ _{iopt is} repeated until the end of the acceleration section. Equation (1) is not disclosed due to its bulkiness.

The condition for the maximum increment of the range of the point of incidence of the PF is used to assess the possibility of the maximum shift of the range of the point of incidence of the PF at full fuel generation (5).

2.2. The determination of angular motion in the atmospheric portion of the flight is determined according to a principle similar to the determination of angular motion in the extra-atmospheric portion with the following differences:

- determination of the angular orientation of the PF at each time interval Δτ _j in the atmospheric portion of the flight PF is carried out in accordance with the formula:

where α is the value of the optimal angle of attack (slip), which varies when determining the orientation of the OF (6), for example, by sequential enumeration in the interval:

in this case, the condition should be satisfied on the entire interval Δτ _j in terms of strength, thermal loading, controllability of the OF:

- the beginning of the atmospheric control section (position 2 in figure 1) is selected from the condition of maximum range increment due to aerodynamic maneuver;

- with the selected current value of the angle of attack from (7) and pitch (6) integrate the complete equation of motion of the PF (book 1, p. 100) on the time interval Δτ _j ;

- after the end of integration at coordinates and velocities at the end of the interval Δτ _j with different angles of attack, the change in the range increment is estimated based on the analytical solution (3).

The use of this solution for comparative evaluations of various controls at small time intervals Δτ _j (up to 10 sec) is quite acceptable (pos.6, 7 in Fig. 1).

2.3. The determination of the durations of sections (4) and their optimal ratio is carried out on the basis of an iterative procedure when determining pitch (yaw) programs while optimizing criteria, for example, range increment by simple enumeration of ζ values, for example, in the range: 0.1 <ζ <1.

Condition (4) corresponds to the total production of residual liquid SRT, the reserves of which can reach up to 3% of the initial volume of refueling fuel, and is one of the main environmental requirements for the program for managing the release of spent fuel to the fall area.

The implementation of the process of generating liquid residues of SRT is ensured by their gasification followed by the development of an impulse with the help of hydraulic propulsion, which is quite fully described in the literature, for example:

- A method for cleaning the separated part of a rocket from toxic liquid residues of rocket fuel components and a device for its implementation / patent RU No. 2359876. Publ. 06/27/2009. Bull. No. 18,

- The method of removal of the separated part of the launch vehicle from the orbit of the payload and the propulsion system for its implementation / patent RU No. 2406856. Publ. 12/20/2010. Bull. Number 35.

Additional advantages of the proposed descent control method are:

- the ability to change the coordinates of the point of incidence of PF due to the use of energy, contained in the undeveloped residues of liquid fuel in the tanks;

- a decrease in the scatter of the drop points of the VL due to the controlled descent of the VL stage of the ILV even in dense atmospheric layers;

- the full production of liquid residues of SRT in the fuel tanks of the OCh by the time of arrival in the area of fall.

The mass of structural elements, ensuring the implementation of this method, does not exceed 0.5% of the mass of the dry structure of OCh.

Figure 1, 2 shows a diagram explaining the operation of the method.

Claims (2)

1. The method of launching the separating part of the stage of a space rocket with a liquid rocket engine, based on the rotation of the separating part after it is separated from the space rocket in a statically stable position, applying a pulse, using aerodynamic quality during descent, characterized in that the program for controlling the movement of the separating part the steps in the descent section are divided into extra-atmospheric and atmospheric flight, the movement in the non-atmospheric section of the flight path is divided into final the number S _{int of} time intervals and the angular rotation program of the separating part at each i-th time interval (i = 1, 2 ... S _ext ) is determined from the condition of the maximum change in the increment of the range of the point of incidence of the separating part in passive flight from the end of the i-th current time interval according to the formula:

Where

ΔV _i - velocity impulse applied at an angle ϑ _i , on the i-th time interval by 4 steering chambers of a gas rocket engine, y ₀ , V _x0 , V _y0 , g ₀ - values of the coordinate, velocities of the center of mass of the separating part and acceleration of the Earth's gravitational field at the beginning of the i-th time interval, the motion of the separating part on the atmospheric portion of the flight path is divided into a finite S _at number of time intervals and the angular movement program of the separating part at each j-th time interval (j = 1, 2 ... S _at ) is determined from the condition creating an aerodynamic moment, not pr Witzlaus, for example, the control torque of steering gas chambers of rocket engine conditions and provides maximum strength change increment distance separating the point of incidence portion in the passive flight from the end of the j-th time interval to the point of incidence separable parts, which is determined by the formula:

where y _jк , V _xj , V _yjк , g _jк are the coordinates, the velocities of the center of mass of the separating part and the acceleration of the Earth's gravitational field at the end of the j-th time interval. 2. The method according to claim 1, characterized in that the total length of the control sections on which the gas rocket engine operates, and their ratio is determined by the formula:

where τ _i is the duration of the control sections;

- undeveloped residual liquid fuel in the tanks of the separating part, which are gasified and fed into the chambers of a gas rocket engine, each chamber of which is installed in a controlled drive;

- mass second consumption of gasified fuel through the chambers of a gas rocket engine, is determined from the condition of reaching the maximum range of the point of incidence of the separating part.

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