RU2406856C2 - Method of withdrawing rocket carrier separated section (rcss) from pay load orbit and power plant to this end - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: rocket carrier separated part (RCSS) is revolved about lengthwise axis to stabilise its angular position in space. Residual liquid fuel and oxidiser components are gasified to generate braking pulse by combusting them in gas rocket engine chamber and due to high-rate efflux of combustion products into space. Power plant (PP) comprises oxidiser and fuel tanks and tanks pressurisation system. PP additionally incorporates powder rocket engines to spin-up RCSS, at least, gas rocket engine with feed system and residual fuel-and-oxidiser gasification system. Said feed system comprise gas bleed devices incorporating pyro membranes connected to gas rocket engine manifold. Residual fuel-and-oxidiser gasification system comprises compressed gas cylinder, a ball, communicated via electropneumatic valve and reducing valve with fuel and oxidiser expansion tanks, and gas generator fed from said expansion tanks and communicated with devices to force gas into fuel tanks.

EFFECT: reduced contamination of outer space.

2 cl, 1 dwg

Description

The invention relates to rocket and space technology, mainly to launch vehicles (LV) with liquid propellant rocket propulsion systems (DU), and can be used to remove the separated part (OH) of the LV stage from the payload orbit to the disposal orbit.

There is a method of separating the payload from the launch vehicle and the removal of the last stage OFP due to the successive inclusion of brake engines (see, for example, US patent No. 3534686, CL 102-49.5). After rupture of the mechanical connection between the burned-out RL of the last stage of the launch vehicle and the payload using one of the engines, the RN PH is braked and simultaneously deployed, then, with a time delay of 0.8 s, they act on the RN PH by a brake pulse from the second braking engine and finally retract the RN RN from the flight path payload.

A device for implementing this method contains two solid fuel brake rocket engines (RD), located symmetrically relative to the center of mass of the RP, diametrically opposite.

The disadvantage of this method and device for its implementation is that during the initial non-simultaneous operation of the brake taxiways, an additional lateral dynamic load on the frequency response occurs, because the effective residual thrust of the OHP LV engine and the thrust of one brake taxiway create an unbalanced torque, which acts as a lateral force on the end of the RP, which leads to distortion of the specified trajectory of the further movement of the RP. In addition, this method and the device for its implementation does not ensure the transfer of the NF LV to the disposal orbit, which leads to an increase in the clogging of the orbital space.

Closest to the claimed invention in terms of the method is a method of withdrawing an aerospace unit from the upper stage of the launch vehicle, according to which, after breaking the mechanical connection between the burnt out last stage of the launch vehicle and the payload, the last stage of the launch vehicle is separated in the axial direction by applying a brake pulse to the last stage of the launch vehicle with given equal traction simultaneously from both brake taxiways located on the last stage of the launch vehicle, and then after the end of the working time of one of the brake taxiways act on and the OCh of the last stage of the launch vehicle by the brake pulse of the second taxiway, which continues to operate and ensures the removal of the OCh of the last stage of the launch vehicle from the payload flight path (RF patent RU No. 2252532 C2, IPC F02K 9/80, B64G 1/26).

The disadvantages of this method is that it can be implemented using solid propellant RD, having a large mass relative to the mass of the stage itself. In addition, this method also does not ensure the withdrawal of the NF LV into the orbit of disposal and therefore does not solve the problem of reducing the debris of outer space.

The closest in technical essence to the proposed invention in terms of the device (prototype) is the remote control given in the book "Fundamentals of the design of aircraft". Textbook for technical universities. / V.P. Mishin, V.K. Bezverby, et al. - M.: Mechanical Engineering, 1985. - Fig. 6.22, p. 220. The remote control contains fuel tanks and a system of pressurization of tanks, including a gas generator, devices for introducing gas into tanks and flow washers.

This device operates as follows.

In the process of completing the stage of its target task, components of rocket fuel (SRT) are supplied to the gas generator, where they react with the release of heat and form gas. This gas is supplied to pressurize the fuel tank, and for the oxidizer tank, the oxidizing agent vaporized by the gas of the pressurization of the fuel tank is used, and then the gases displace the SRT from the tanks to liquid (RD).

However, the specified remote control is designed only to bring the payload to the orbit of operation. Departure of the VHF LV into the orbit of disposal using this remote control is not possible, which ultimately leads to an increase in the clogging of outer space.

The objective of the invention is to ensure the removal of HF LV from the orbit of the payload to the orbit of disposal in order to reduce the clogging of outer space.

The problem is achieved in that in the method of removing the payload from the orbit of the OHF LV, according to which, after breaking the mechanical connection of the payload with the OHL, the brake impulse is applied to it, according to the claimed invention, the magnitude of the brake impulse required to remove the OHL LV with initial payload orbit to a given recycling orbit, according to the formula

,

,

where H _α is the height of the apogee of the disposal orbit equal to the height of the circular orbit of the payload;

H _π is the perigee height of the disposal orbit, which is determined by the disposal time;

R ₃ = 6371 km - spherical radius of the Earth;

µ ₀ = 3.986 · 10 ⁵ km ³ · s ² - gravitational constant of the Earth's gravitational field,

Then, the design parameters of the gas taxiway are selected, which ensure the calculated value of the brake pulse for transfer to the disposal orbit, and until the calculated brake pulse is applied to the HF PH, the HF PH is rotated around the longitudinal axis until the stabilization of its angular position in space, then the residual liquid MCTs in the oxidizer and fuel tanks create a braking impulse due to their combustion in the gas RD chamber and the high-velocity outflow of combustion products into space some space.

In terms of the device, the task is achieved in that the remote control, including the fuel tanks of the oxidizer and fuel, and the pressurization system of the tanks containing the gas generator, the device for introducing gas into the tanks, equipped with flow washers, according to the claimed invention, the remote control is additionally equipped with gunpowder RD spin-offs, gas RD with a system power supply and gasification system for residues of SRT, and the power supply system contains gas extraction devices equipped with pyromembranes that are connected to the collector of the gas taxiway КРТ contains a ballon-cylinder with compressed gas, connected through an electro-pneumatic valve and a reducer with fuel and oxidizer displacement containers, a gas generator equipped with flow washers, powered from the displacement containers and connected to gas input devices into the fuel tanks equipped with pyro membranes.

The invention is illustrated in the drawing, which shows a schematic diagram of the claimed remote control pH.

The remote control contains:

- fuel tanks of oxidizer 1 and fuel 2 of a liquid taxiway with a system of pressurization of tanks (not shown in the drawing);

- a gasification system for the SRT residues, which consists of a balloon cylinder with compressed gas 3 connected through an electro-pneumatic valve 4 and a reducer 5 with fuel displacement containers 6 and an oxidizer 7, a gas generator 8 equipped with flow washers 9, 10, fed from the displacement containers 6, 7 and connected to devices for introducing gas into the tanks 11, 12, equipped with pyromembranes 13, 14 and flow washers 15, 16;

- a power system, which consists of gas sampling devices 17, 18, equipped with pyromembranes 19, 20, which are connected to the manifold 21 of the gas taxiway 22;

- gunpowder RD 23 promotion OCh.

Withdrawal from orbit of the payload of the VL PH to the disposal orbit is as follows.

After giving the command to turn off the liquid taxiway, a command is issued to separate the spacecraft. After separation of the spacecraft, the VF RH is rotated with the help of gunpowder RD spins 23 around the VH longitudinal axis to stabilize it in the direction of the velocity vector, which simultaneously leads to the distribution of undeveloped liquid fuel residues over the inner tank surfaces and facilitates the process of gasification.

The stabilizing moment M _st around the longitudinal axis of the oculus will be determined by the value of the product

,

,

where J _x10 is the initial moment of inertia of the OCh around the longitudinal axis, taking into account the presence of distributed fuel residues along the walls of the tank;

ω _x10 is the initial angular velocity imparted by the OC to stabilize its angular position in space at the time of separation of the spacecraft, is realized due to the operation of the powder propulsion RD 23.

After stabilization of the VL PH, the electro-pneumatic valve 4 is opened and pressurization gas 5 is supplied from the balloon 3 to the displacement containers with fuel and oxidizer 6 and 7, respectively, through the reducer 5. From the displacement containers with fuel and oxidizer 6 and 7, through the flow washers 9, 10, the SRT is supplied to the gas generator 8.

From the gas generator 8 by opening the pyromembranes 13 and 14 through the gas input devices into the tanks 11, 12, equipped with flow washers 15, 16, hot boost gas is supplied to the tanks 1, 2 with the remains of the SRT, where the remains of the SRT are gasified with the conservation of chemical energy by heating them .

The gasified residues of SRT through the gas sampling devices 17, 18 are supplied to the manifold 21, and then to the gas RD 22 by opening the pyromembranes 19 and 20. The SRT is burned in the combustion chamber of the gas RD 22 with the application of a traction brake impulse due to the high-speed discharge of combustion products into outer space.

Assuming the existence of time t _n in orbit utilization, we can determine the amount of brake pulse to transfer OCH last stage rocket payload from orbit to orbit disposal. In accordance with the recommendations of the Inter-Agency Space Debris Coordination Committee, this period should not be more than 25-50 years.

Based on the formulas given in the book "Engineering Reference for Space Technology", ed. 2nd, edited by A.V. Solodov. M .: Voenizdat, 1977, p.93-97, formula (2) was derived to determine the braking momentum of the coplanar transition of the VH PH from the payload orbit to the disposal orbit. Thanks to the following formula, it became possible, by the values of the apogee and perigee of the disposal orbit, to determine the braking impulse necessary for such a transition.

For example, in order to transfer the NF of the LV from a circular payload orbit with a height of N _cr = 950 km to a disposal orbit with parameters H _α = 950 km and H _π = 950 km, where t _exist ≈25 years, it is necessary to apply a braking impulse ΔV _τ determined in the following way:

,

,

where H _α and H _π are the apogee heights of the initial orbit of the payload and the perigee are shaved for disposal, respectively;

R ₅ = 6371 km is the spherical radius of the Earth;

µ ₀ = 3.986 · 10 ⁵ km ³ · s ² - gravitational constant of the Earth's gravitational field.

When choosing the design parameters of a gas taxiway, the type of SRT and the calculated value of the braking impulse, which must be implemented, are taken into account.

Depending on the calculated value of the brake impulse, the gasification of the SRT residues is set up by selecting flowmeter washers 9, 10, 15, 16 to adjust the gas generator 8 and gas input devices into the tanks 11, 12, respectively.

The implementation of the proposed method and the remote control for its implementation allows us to solve one of the most important tasks facing the developers of launch vehicles - reducing man-caused clogging of the orbital space due to the removal of the VHF LV to the orbit of disposal. The problem is solved by using the remaining undeveloped residues of liquid fuel remaining in the marching control unit, which are enough to work out the brake pulse (2).

This method and device for its implementation can be implemented on any LV using liquid SRT, in addition, this method can be used to transfer into orbit the disposal of upper stages and spacecraft using RD on liquid SRT.

The practical implementation of the proposed method and propulsion system does not go beyond the technological capabilities of enterprises developing and manufacturing launch vehicles with liquid taxiways.

In addition, the application of this method allows in some cases to exclude additional areas of incidence, for example, the area of incidence of the 3rd stage of the Proton launch vehicle, which was introduced on the basis of environmental conditions - ensuring the cleanliness of the orbital space from clogging with space debris. Similar Proton launch vehicles can also eliminate space debris, however, they make it necessary to create a fall area on the territory or water surface of the Earth, reduce the mass of the payload and, compared with the claimed invention, require significantly greater financial investments.

Claims (2)

1. A method of withdrawing a separating part of a launch vehicle (OCR) from the payload orbit, according to which, after breaking the mechanical connection between the OCR and the payload, a braking impulse is applied to the OCR, characterized in that before the application of the braking impulse to the OCR, the OCR are rotated around the longitudinal axis to achieve stabilization of its angular position in space, then the residual liquid undeveloped components of rocket fuel are gasified in the oxidizer and fuel tanks and create a braking impulse due to their combustion in the gas chamber a rocket engine and high expiration of the combustion products in the space. 2. A propulsion system including oxidizer and fuel tanks and a tank pressurization system comprising a gas generator, devices for introducing gas into tanks equipped with flow washers, characterized in that the propulsion system is additionally equipped with powder rocket engines for spinning the separating part, at least one gas rocket an engine with a power system and a gasification system for residual rocket fuel components, the power system comprising gas sampling devices equipped with pyromembranes, which are connected to the manifold of a gas rocket engine, and the gasification system for the residual components of rocket fuel contains a balloon with a compressed gas connected through an electro-pneumatic valve and a reducer with displacement containers with fuel and oxidizer, a gas generator equipped with flow washers, powered by displacement containers and connected to devices introducing gas into fuel tanks equipped with pyromembranes.