RU2414391C1 - Method of descending space rocket stage separation part and device to this end - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to space engineering, particularly, to liquid propellant rockets. Proposed method consists in stabilising discarded part in engine-forward position, orienting it and controlling its descent. Said separated from the rocket, maneuver is performed by power of gasified residual liquid fuel components fed into descent rocket gas engine plant. Control over motion of center of mass and around it is carried out by deflecting chambers of gas jet engine plant. Angular position of separation part in space, on cutting in gas jet engine, is set corresponding to minimum angle of attack on re-entry, and separation part is spinned about its lengthwise axis. Proposed separation part comprises control and navigation system, and gasification system. Fuel compartment bottom accommodates four chambers, each being provided with drive. Gasification system incorporates self-contained gas generator with membrane system to feed fuel components, acoustic vibration exciters arranged on unions feeding fuel in fuel tanks.

EFFECT: reduced area of rocket descent.

3 cl, 2 dwg

Description

The invention relates to rocket and space technology, in particular to rocket launchers for liquid fuel. Known methods of putting payload into outer space, for example, Prince. Yu.G. Sikharulidze. Ballistics of aircraft. - M .: Nauka, 1982.- 352 p. The movement of all stages, including their separating parts, is carried out in the launch plane, the programmed value of the roll and yaw angles is always zero, and the programmed value of the pitch angle is determined by the requirement of putting the maximum payload into orbit.

Given the fact that launch vehicles (LV) consist of several stages, in which, as a rule, liquid toxic residues of fuel and oxidizer are located, a problem arises of limiting the areas of incidence of separating parts (OC).

Closest to the proposed method is the invention "A method of launching an accelerator of a space rocket into the landing zone and a device for its implementation" according to patent RU 2043954, B64G 1/24, B64C 17/00, where the accelerator is launched, i.e. PF, in a limited area of incidence using stabilization, aiming and controlled descent using aerodynamic forces.

The application of this method causes a number of technical problems, including the difficulty of implementing aerodynamic rudders and their drives, the time and cost of working out the entire descent system. In addition, the application of this method does not solve the problem of reducing the impact of rocket fuel residues on the environment, which is especially important for toxic fuels, including kerosene.

In connection with the need to bring payloads to orbits with different inclinations i, there is a need for different azimuths of the launch planes A _r PH and, accordingly, additional areas of incidence.

In accordance with spherical geometry, the equality holds:

where i is the inclination of the orbit, φ _r is the latitude of the starting point PH, A _r is the azimuth of the starting direction PH.

The allocation of areas of decline for HF is associated with the removal of significant areas from the economic turnover, which, in addition to economic damage, is not always possible, for example, due to the presence of large settlements, territories of neighboring states, etc.

In this regard, the removal of the first (second) stage PH is carried out in the plane with the azimuth of the launch direction A _r , where there are fall areas, and the next stage maneuvers in the yaw plane to launch to a given orbit, which leads to significant energy costs, determined by the formula cosines:

where ΔV is the required value of the characteristic speed for the transfer maneuver from the launch path, where there are fall areas, to the path, the launch of which will provide a given inclination of the orbit i,

V ₃₁ , V ₃₂ - the velocity of the center of mass PH at the moment of the start of the maneuver from the launch path, for which there are areas of incidence on the launch path with a given orbital inclination angle i,

φ is the angle between the vectors V ₃₁ , V ₃₂ .

Figure 1 shows the scheme for the removal of PH with reference to the areas of fall of OCh.

The following notation is accepted:

A ₁ , A ₂ - azimuths of launch;

RPOCH11, RPOCH21 - available fall areas during launches in azimuth A ₁ ;

RPOCH12, RPOCH22 - fall areas, which must be distinguished during launches in azimuth A ₂ ;

a ₁₁ , a ₁₂ - active sections of the trajectory (AUT) of the first stage during starts, respectively, according to A ₁ and A ₂ ;

a ₂₁ , a ₂₂ - AUT of the second stage during starts, respectively, according to A ₁ and A ₂ ;

a ₃₁ , a ₃₂ - third-stage automatic control system at starts according to A ₁ and A ₂ , respectively;

P _11, P ₁₂ - passive sections of the trajectory (PUT) of the first stage OCh at starts according to A ₁ and A ₂ ;

P ₂₁ , P ₂₂ - PUT OCH of the second stage at starts according to A ₁ and A ₂ ;

P ₁₃ , P ₂₃ - the movement of OCH1 and OCH2 with the proposed method of descent to predetermined areas of incidence using a gas jet propulsion system;

V ₃₁ , V ₃₂ - the speed of the third stage when deriving respectively in azimuths A ₁ and A ₂ ;

- затраты на маневр для увода с траектории в плоскости пуска с A₁ на траекторию с плоскостью пуска A₂;

- the cost of maneuver to move away from the path in the launch plane from A ₁ to the path with the launch plane A ₂ ;

φ is the angle between the velocity vectors V ₃₁ and V ₃₂ .

The essence of the proposed method lies in the fact that the launch of the OCh in a predetermined and reduced area of the fall area is carried out on the basis of the use of a special gas jet propulsion system (DU) descent and energy resources of the components of rocket fuel remaining in the fuel tanks of the OCh. See figure 1: the movement of the first stage along the paths P ₃₁ , and the second stage along the path P ₃₂ .

Thus, the following sequence of actions of the descent method is proposed after separation of the IF from the rocket, taking into account the presence of a prototype (stabilization, aiming, guided descent):

- maneuver of descent to a predetermined area of incidence is carried out at the expense of energy, contained in the undeveloped residues of the components of liquid fuel based on their gasification and supply to a special gas reactive remote control;

- energy costs for the implementation of the maneuver of launching the OC in a given area of incidence from the current trajectory to the falling one are determined from the condition of ensuring the corresponding increment of the center of mass velocity of the OC determined by formula (2), with the difference that instead of V ₃₁ , V ₃₂ , respectively, the speeds will be used centers of mass of the first and second steps PH;

- 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 chambers of the gas reactive remote control based on the solution of the problem of navigation and control, as in the prototype method;

- at the time of shutdown of the gas reactive remote control provide the angular position of the OF in space, corresponding to the minimum angle of attack at the entrance to the dense layers of the atmosphere,

- twist OCh around its longitudinal axis;

- 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 OC using the cameras of a gas reactive remote control.

As an analogue of the device, the device according to the invention is proposed ("A method for launching a payload into outer space and a multi-stage space-rocket system for its launch" patent RU 2092384 В64С 1/16), and as a prototype - a device according to the invention "Method for launching a space rocket accelerator destination in the landing zone and device for its implementation "set forth in patent RU 2043954 B64G 1/24, B64C 17/00.

The proposed device is an OCh part of a space rocket on liquid fuel components, which includes a control and navigation system, a gasification system, characterized in that on the upper bottom of the fuel compartment there are 4 chambers in controlled drives, and the gasification system has an autonomous gas generator with a membrane a system for supplying fuel components, pathogens of acoustic vibrations located on the fittings for entering the coolant into the fuel tanks.

Figure 2 shows a device for implementing this method.

Let us explain the sequence of actions of the claimed method of launching the NF PH into a given area of incidence.

1. The maneuver of descent to a predetermined area of incidence is carried out at the expense of energy, contained in the undeveloped residues of the components of liquid fuel based on their gasification and supply to the gas remote control.

In OCh missiles, the remainder of the undeveloped fuel remains up to 3% of the initial fill. Undeveloped fuel reserves are: oversupply residues, warranty refueling, fuel lines and engine filling, and there may also be fuel residues provided for the task of lowering the first (second) stage of high-speed fuel to a specified drop area. These residues are gasified (see, for example, “A method for removing payload into outer space and a multi-stage space-rocket system for its removal” patent RU 2092384 В64С 1/16).

In accordance with the Tsiolkovsky formula, the available reserves of the characteristic speed on board the OCh are determined

where P _beats - specific thrust, s; for LRE in vacuum reaches 300 ÷ 460 s;

m _{o =} m _k + m _fuel , m _k is the mass of the structure, including the mass of the gasification system;

m _fuel - the mass of fuel residues in the tanks that are subject to gasification.

For example, for a stage with m _kks = 1500 kg, m _fuel = 100 kg, 200 kg and P _beats = 300 s, the available energy in accordance with (3) will be 189 m / s and 368 m / s.

Obviously, the solution of the problems of lowering the OCh to a given area of incidence requires additional mass costs, and for each launch it is necessary to decide on the feasibility of its solution.

2. The value of the undeveloped residues is formed taking into account the descent of the OCh in the specified area of the fall,

The energy costs for the implementation of the maneuver of launching the OC in a given area of incidence from the current path to the falling one are determined from the condition of ensuring the corresponding increment of the center of mass velocity of the OC determined by formula (2), with the difference that, instead of V ₃₁ , V ₃₂ , corresponding speeds will be used the centers of mass of the first and second steps.

The descent maneuver involves the application of a velocity impulse ΔV to the center of mass of the ocher to ensure the descent of the ocher from the trajectory of removal by a given inclination onto the trajectory in the existing fall region. In accordance with the formula (2) for the first stage OF, the magnitude of this pulse is determined by the formula:

where V ₁₁ , V ₁₂ , are the velocities of the center of mass of the first stage OHP at the time of separation when moving along the azimuth of launch A ₁ , with an existing fall region, which ensures the fall of the OH in this region, and the speed of the OCh of the same stage along the azimuth of launch A ₂ at a given orbit along an energetically optimal trajectory, but without the presence of a region of incidence;

χ is the angle between the velocity vectors V ₁₁ , V ₁₂ .

The momentum value for the separating part of the second stage is calculated similarly.

Residues of non-depleted fuel reserves in HF are caused, as a rule, by imperfection of on-board systems: fuel compartment structures (under-intake residues), warranty reserves (variation in the operation of bot systems), filling lines, etc. and make up to 3% of the initial working fuel reserves.

Depending on the tasks, in accordance with the proposed method, the amount of undeveloped reserves can be increased to solve the problems of lowering the reserve in the given area using the formula (4).

3. When you turn off the gas remote control provide an angular position in space corresponding to the minimum angle of attack at the entrance to the dense layers of the atmosphere

In the first (second) stage withdrawal area, pitch angles during separation of stages for different missiles and launch programs can be 80 ° -70 ° for the first stage and 50 ° -30 ° for the second stage, and the angle of attack is small and does not exceed 0-5 ° for the first steps and up to 10 ° for the second. Upon entering the dense layers of the atmosphere (where the pressure head takes on the maximum value), the angles of attack can reach different values, up to 90 °, which is determined by the magnitude of the perturbations of the angular velocities of the PF during separation, the length of the passive section of the trajectory from the separation of steps to the atmosphere, and the initial values pitch angle, attack, etc. As a rule, large angles of attack in the dense layers of the atmosphere lead to the destruction of the OC, an increase in the area of the areas of incidence.

The completion of the active section of the descent maneuver is carried out before entering the dense layers of the atmosphere and maintaining the controllability of the PF using gas reactive remote control chambers.

Let us explain the operation of the device for implementing this method.

After separating the OCh from the rocket, the gasification system is launched by supplying gas from the balloon 3 through the electro-pneumatic valve 4 and gear 5 to the displacement containers of the oxidizer 6 and fuel 7 through the consumables 9, 11 into the gas generator 8. The fuel components are self-igniting, for example, asymmetric dimethylhydrazine - fuel and nitric acid - an oxidizing agent.

In the gas generator 8, a chemical reaction occurs with the release of heat. Depending on the second consumption of fuel and oxidizer, the composition of the gas products of combustion, temperature, and pressure at the outlet of the gas generator are regulated 8. The pyromembranes 14, 17 are opened under the pressure of the products of combustion. The washers 13, 16 regulate the mass second flow rate of the coolant through the pipelines 19, 20 to the fuel tanks of the oxidizer 1 and fuel 2.

To increase the efficiency of the gasification process, acoustic vibrations are introduced into the coolant introduced into the fuel tanks 1, 2 by installing swirling devices (21, 22) on pipelines 19, 20 of the “whistle” type. See, for example, the patent "Method for preparing liquid fuel for combustion" RU 2132020 F23K 5/02.

Under the influence of the coolant, with acoustic vibrations devices 21, 22 superimposed on it, gasification of the fuel and oxidant residues in the tanks takes place. Upon reaching the specified pressure in the tanks, pyromembranes 15, 18 are opened and the gaseous components of the fuel enter the gas manifold 23, and from there into the combustion chambers 24 of the gas reactive remote control, where they interact and create traction. The thrust vector control gas reactive remote control is carried out by the actuators 25.

Claims (3)

1. The method of launching a separating part of a space rocket on liquid fuel components to a predetermined area of incidence, based on the stabilization of the separating part by the position of the propulsion system forward, the orientation and controlled movement of the separating part, characterized in that after separation of the separating part, a descent maneuver is carried out in a predetermined area of incidence due to the energy contained in the undeveloped residues of liquid fuel components based on their gasification and supply to a gas rocket propulsion system descent, while controlling the movement of the center of mass and around the center of mass of the separating part is carried out by the deviations of the chambers of the gas jet propulsion system, and the separating part at the time of shutdown of the gas jet propulsion system provides an angular position in space corresponding to the minimum angle of attack when it enters the dense layers of the atmosphere, and twist the detachable part around its longitudinal axis. 2. The method according to claim 1, characterized in that the value of the undeveloped residual liquid fuel is formed taking into account the descent of the separating part to a predetermined area of incidence, 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 the controllability of the separating part using gas chambers jet propulsion system. 3. The detachable part of a space rocket on liquid fuel components, including a control and navigation system, a gasification system, characterized in that 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 to the fuel tanks.

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