RU2560645C1 - Thrust pulse output system - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: proposed system comprises control system, spherical tanks with deforming metal webs separating fuel and gas chambers, balloons, filling necks, low-thrust liquid-propellant control engine units, correction-braking engine, chokes, air-operated electrical valves, fluid-operated electrical valves and check valves, pressure indicators, fuel feed lines and supercharge lines. Additionally, this system is equipped with sealed resilient medium separators connecting the oxidizer and propellant and oxidizer tanks fuel chambers outlet pipes with those of gas chambers. Stiffness of these separators is smaller than that of deforming metal webs. Correction-braking engine is integrated with the three extra engines to make the unit fitted at spacecraft lengthwise axis. Note here that low-thrust liquid-propellant control engines are integrated into four units of three engines each. Two engines of each said unit are arranged so that their thrust vectors are diametrically opposite in the pane perpendicular to spacecraft lengthwise axis. Third engine thrust vector in the spacecraft lengthwise axis is directed opposite the flight direction. Said low-thrust liquid-propellant control engines are secured in pairs in diametrically opposite points. Lines of propellant feed to the main manifolds of said low-thrust liquid-propellant control engines and to manifolds of correction-braking are provided with four pairs of fluid-controlled electrical valves interconnected in parallel.

EFFECT: higher reliability at long-term operation, decreased weight, better controllability.

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Description

The claimed technical solution relates to the field of rocket and space technology, and in particular to the field of design and operation of propulsion systems (DU) of spacecraft (SC) and booster blocks, designed to provide impulse pulses of the spacecraft in six degrees of freedom necessary to bring the payload to calculated orbit, corrections of this orbit during the orbital flight, spacecraft orientation with respect to the Earth and stars, and also to give the spacecraft a braking impulse during descent from orbit.

Known liquid propulsion system DU-802 of the autonomous space tug “Krechet” (article by A. V. Dibrivny “Results of developing a system for ensuring synchronization of fuel generation from the tanks of a propulsion system DU-802 of a space tug” // Aerospace Engineering and Technology, 2008, No. 10. - p. 88, fig. 1;

http://www.nbuv.gov.ua/portal/natural/AkTT/2008_10/Dibrivn.pdf - analogue), containing fuel tanks of oxidizer, high pressure cylinders, liquid propellant engines (LRE) of low thrust (MT), automation units interconnected by hydraulic and pneumatic pipelines.

The disadvantage of the above liquid propulsion system is its low reliability due to the difficulty in performing a maneuver in the event of failure of at least one small thrust engine: lack of duplication of orientation engines and corrective-brake engine (KTD) (it is single-chamber); large mass: eight orientation engines, eight mounting points, eight sets of supply pipelines, the presence of a pneumatic pump unit for supplying fuel components, the need for an additional supply of compressed gas for the operation of the turbine of this unit.

A well-known compartment of a liquid-propellant rocket propulsion system of a spacecraft (patent RU No. 2059858 IPC F02K 9/00 is an analogue) containing fuel tanks with metal partitions, fuel supply lines, ball-balloon of the fuel displacement system, stabilization and orbit correction engines of the device.

Known integrated propulsion system for spacecraft type "Resource" (the book "Design of automatic spacecraft" edited by a member - Corresponding Member of the Russian Academy of Sciences DI Kozlova, Moscow, Engineering, 1996, p. 423, Fig. 9.3 - prototype), including fuel tanks, throttles in the fuel supply system, balloons, pressure alarms, check valves, electro-pneumatic valves (EPC) and electro-fluid valves (ELC), fuel fillers, corrective-brake engine, MT engine control units, piping system.

A disadvantage of the well-known complex propulsion system is the large mass resulting from the use of sixteen MT liquid propellant rocket engines (four engine mounts), a complex multi-unit pneumohydraulic system, with an intermediate fuel supply system through a hydraulic accumulator with an additional balloon for storing high-pressure gas. In this remote control, a fixed-chamber single-chamber KTD is used, which cannot be used to control the thrust vector, and, as a result, requires the use of high thrust control engines, which leads to an increase in fuel consumption through them, i.e., to an increase in fuel mass onboard the spacecraft.

Common disadvantages of the above devices (analogues) and the known installation (prototype) is low reliability due to the lack of protection of tanks against destruction when pressure increases as a result of temperature fluctuations during storage, transportation and operation, lack of duplication of the corrective-brake engine system and the inability to control the thrust vector corrective-brake engine without special drives, as well as gearbox pressurization of the gas cavities of the fuel tanks, which does not provide a high step the tightness of the boost gas, which leads to a constant increase in pressure in the gas cavities of the fuel tanks and the need to discharge these excess gas through special safety valves overboard the SC, which does not allow the use of such a scheme for long orbital flights.

The objective of the proposed technical solution is to increase the reliability of operation over a long period of operation, reducing the mass of the system for issuing thrust impulses (SVIT), as well as improving the flight control of the spacecraft.

The technical result is achieved by the fact that the SWIT, which includes a control system, spherical tanks with deformable metal partitions separating the fuel and gas cavities, balloons, filling necks, blocks of control liquid thrusters, corrective-brake engine, throttles, electro-pneumatic valves, electro-fluid and non-return valves, pressure alarms, fuel and boost lines, and the traction impulse output system is additionally equipped with tight elastic medium dividers connecting the outlet pipelines of the fuel cavities of the oxidizer and fuel tanks with pipelines combining the gas cavities of the tanks, and their rigidity is less than the stiffness of the deformable metal partitions of the tanks, and the corrective-braking engine together with three additional injected engines are assembled in a block mounted on the longitudinal axis of the space apparatus, while controlling liquid propellant small thrust engines are combined in four blocks of three pieces, with two engines in each block are mounted with a diametrically opposite direction of the thrust vector in the plane perpendicular to the longitudinal axis of the spacecraft, and the thrust vector of the third engine installed in the plane of the longitudinal axis of the spacecraft is directed in the direction opposite to the direction of flight, while the blocks of control liquid propellant thrusters are paired in diametrically opposite places of the spacecraft, and in the lines of supply of fuel components to the main collectors of the control liquid p four thrust engines and four corrective brake engine manifolds are fitted with four pairs of electro-fluid valves connected in parallel.

The proposed technical solution is illustrated by drawings, in which Fig. 1 shows a schematic pneumohydraulic circuit of the SVIT, Fig. 2 shows the control system of the liquid-propellant rocket engine MT and KTD SVIT;

The SVIT device (Fig. 1) contains a control system 1 (not shown conditionally in the figures), four spherical tanks 2 for storing liquid fuel components with deformable metal partitions 3, intended for separating the fuel 4 and gas 5 cavities, oxidizing nozzles 6 and fuel, test fittings 7, intended for testing the aggregates along the oxidizer line 8 and the fuel line 9, hermetic elastic medium dividers 10, for example, bellows hydraulic compensators, through which the fuel strips These 4 tanks 2 of oxidizer and fuel are connected by pipelines 11 to pipelines 12 connecting the gas cavities of 5 tanks 2, throttles 13 installed at the outlet of tanks 2 in the fuel component supply lines 8 and 9 to ensure equal costs consumed from both fuel tanks 2 or oxidizing agent necessary to maintain the alignment of the spacecraft, balloon 14 for storing boost gas, charging neck 15 of the boost gas, test neck 16 for checking the units along the line of the boost 17, pyro valves 18, electric solenoid valves 19, throttle devices 20, check valves 21 of the boost system, breakout membranes 22 installed in the lines 8 and 9, breakout membrane 23 installed in the line 17, signaling devices 24 and pressure sensors 25, filters 26 to ensure the purity of the liquid fuel and gas components pressurization, block 27 of four KTDs 28, 29, 30 and 31 mounted on the longitudinal axis 32 of the spacecraft, two pairs of blocks 33 and 34 of three control rocket engines MT 35, 36, 37 in each, fixed in pairs in two diametrically opposite places of the spacecraft ( figure 2), while in each block installed two motor 38 on the same axis with the diametrically opposite direction of the thrust vector in a plane perpendicular to the longitudinal axis 32 of the spacecraft 39 and the third motor axis lies in the plane of the longitudinal axis 32 of the spacecraft and its thrust vector directed in the direction opposite to the direction of flight of the spacecraft. Blocks 33 and 34 of the control MT rocket engines are duplicated: main collectors 40 of fuel and oxidizer are connected to one (main) pair of blocks 33, duplicate collectors 41 are connected to the other pair of blocks 34. In lines 8 and 9 of the fuel components supply to the main collectors 40 of control MT rocket engines 35, 36, 37 and collectors 42 KTD 28, 29, 30, 31 are installed four pairs of parallel-connected electro-fluid valves 43, and in the supply lines of the fuel components to the backup manifolds 41 of the control MTRE MT 35, 36, 37 are installed one ELC 44 . The composition of each exercise MT-governing LRE 35, 36, 37 and CT 28, 29, 30, 31 includes its own LSE 45 disposed immediately before the combustion chambers.

The work of the Suite is as follows.

During storage, transportation and operation, before the spacecraft enters the reference orbit, the breakthrough membranes 22 provide the amplification of tanks 2, in the fuel cavities 4 of which, as a result of temperature fluctuations during storage, the volumes of the liquid fuel components change, while the expansion of the mass of the liquid is compensated in the closed volume of the tanks 2 occurs by changing the volumes due to sealed elastic media dividers 10, the rigidity of which is less than the rigidity of the deformable metal partitions 3 of the fuel tank 2, for example by the movement of the bellows in the bellows lash.

After the spacecraft is launched by the launch vehicle into the reference orbit, the spacecraft control system 1 (or the upper stage) sends a command to actuate the pyro valves 18 and EPK 19, after which the boost gas from balloons 14 enters the boost line 17 and passes through throttle devices 20, which as a result of throttling, the charge gas flow rate is limited, providing a given rate of pressure increase in the gas cavities of 5 tanks 2. In the process of pressure increase behind the throttle devices 20, the charge gas breaks the breakthrough membrane 23 and fills the gas the cavity 5 of the tanks 2, acting by its pressure through the deformable metal partitions 3 on the liquid fuel components in the fuel cavities 4. The pressure in the fuel cavities 4 of the tanks 2 rises, resulting in a rupture of the breakthrough membranes 22 and the liquid fuel components fill the oxidizer line 8 and a fuel line 9, the pressure of which increases synchronously, which allows the installation of fuel pressure alarms 24 in one of the lines (in our case, in the fuel line 9). Upon reaching the highest fuel pressure in line 9, the pressure signaling device 24 issues a signal to the control system 1, from which a command is issued to close the electropneumatic valves 19, after which the SWIT is ready for operation.

After receiving a command from control system 1 to issue certain traction pulses to orient the spacecraft in orbit or to correct the orbit (increase or decrease its altitude), paired EJCs 43 of the main collectors 40 or collectors 42 are opened (each second of the parallel installed EJCs operates in “hot” mode reserve, that is, for the normal operation of the system it is enough to operate one of the two ELCs 43), - this ensures reliable fuel supply to the control engines of the MT 35, 36, 37 and KTD 28, 29, 30, 31, with the operation of their own ELC 45 to The fuel and oxidizer are injected into the combustion chambers, self-ignite and give traction pulses in the required direction due to the jet stream of combustion products flowing from the nozzles of the respective engines. The installation of paired ELCs 43 at the entrance to the main collectors 40 and collectors 42 increases the reliability of the MT 35, 36, 37 and KTD 28, 29, 30, 31 liquid-propellant chambers during long-term operation of the spacecraft in orbit, since they turn off the engines during the “drift” ELC 45 due to the effect of fuel pressure, which, if they are leaking, can lead to unauthorized leakage and freezing of fuel components in the combustion chambers and failure of the MT 35, 36, 37 or KTD 28, 29, 30, 31 liquid propellant engines.

With fuel consumption, the volume of the fuel cavities 4 decreases, under the influence of the boost gas pressure, the metal partitions 3 bend, the volume in the gas cavities 5 of the tanks 2 increases and the pressure in them decreases. When the specified pressure is reduced to the lowest permissible engine operating pressure, the pressure switch 24 is activated and a command is issued through the control system 1 to open the electropneumatic valves 19, after which the gas from the balloons 14 begins to flow into the gas cavities of 5 tanks 2, raising the pressure to the highest permissible engine operating pressure, that is, the cycle of maintaining the working pressure in the tanks 2 is repeated until the end of the work (fuel consumption) of engines that can operate in long-term modes (with correction and orbits of the spacecraft) or in pulsed modes (for the orientation of the spacecraft in orbit). After the spacecraft’s maneuver is completed, the control system 1 receives a command to stop the engines, EZhK45, close, stopping the supply of fuel to the engines, then close the EZhK 43, stopping the supply of fuel to the main manifolds 40 and collectors 42.

If necessary, the supply or termination of the fuel supply to the backup manifolds 41 is carried out by ELC 44.

In contrast to the prototype (Fig. 3), where traction pulses to ensure the orientation of the spacecraft (roll, pitch or yaw) are created using eight (main) rocket engines MT, mounted at four mutually opposite points of the spacecraft, in the proposed SVIT device (Fig. 2) the same operations are carried out by means of six (main) control liquid propellant rocket engines, placed in three pieces each in blocks fixed at two mutually opposite points of the spacecraft or by the turbine engine itself.

For the prototype (figure 3): 46, 47, 48, 49, 50, 51, 52, 53 - control LRE; 54 KTD.

The spacecraft is controlled by the inclusion of control rocket engines:

- pitch control: 50, (up); 46, (down);

- yaw control: 52 (to the right); 48 (to the left);

- roll control: 49 and 53 (clockwise); 47 and 51 (counterclockwise).

For the SWIT (figure 2): 35, 36, 37, 55, 56, 57 - control MTL MT; 28, 29, 30 and 31 - KTD.

The spacecraft control is carried out by turning on the control rocket engine MT:

- pitch control: 57 (up); 37 (down);

- yaw control: 36 and 56 (to the right); 35 and 55 (to the left);

- roll control: 35 and 56 (clockwise); 36 and 55 (counterclockwise).

Also, the pitch and yaw control can be carried out in pairs by turning on the KTD:

- pitch control: 30 and 31 (up); 28 and 29 (down);

- yaw control: 28 and 31 (to the right); 29 and 30 (to the left).

At the same time, the use of four KTDs 28, 29, 30, 31 (on the SWIT) instead of one larger one (on the prototype) increases the reliability of the SWIT, since when one KTD fails, the prototype leads to the shutdown of the spacecraft, and when it fails one of the four CTDs in the proposed technical solution will not lead to the shutdown of the spacecraft, since by disabling the CTD, which is diametrically opposite to the emergency one, the spacecraft can continue to operate on the two remaining CTDs.

To ensure reliable operation during storage, transportation and operation, the SVIT is equipped with sealed elastic medium dividers, which make it possible to remove additional increases (decreases) in pressure in the tanks 2 and thereby prevent the destruction of the walls of the tanks as a result of temperature fluctuations.

To ensure a reliable long-term orbital flight, during which multiple triggers of the MT 35, 36, 37 liquid propellant rocket engines occur, duplication of the ELC 43 is used in the fuel supply system, and two pairs of blocks 33, 34, three three MT 35, 36, 37 rocket engines, are installed, in this case, each pair is mounted on its bracket - two diametrically opposite mounting points, which leads to a decrease in the mass of the system.

Thus, the claimed design makes it possible to increase the reliability of operation with a long service life, reduce the weight of the SVIT, as well as improve the flight control of the spacecraft.

Claims (1)

Traction impulse delivery system comprising a control system, spherical tanks with deformable metal partitions separating fuel and gas cavities, balloons, fuel nozzles, control engines for small thrust reactive engines, corrective and braking engines, throttles, electropneumatic valves, electro-fluid and reverse valves, pressure alarms, fuel and boost lines, characterized in that the system is additionally equipped with sealed elastic medium dividers, with connecting the output pipelines of the fuel cavities of the oxidizer and fuel tanks with pipelines combining the gas cavities of the tanks and their stiffness less than the stiffness of the deformable metal partitions of the tanks, and the corrective-braking engine, together with three additional injected engines, are assembled in a block mounted on the longitudinal axis of the spacecraft, control liquid propellant small thrust engines are combined in four blocks of three pieces, and in each block two engines are installed with diametrically prot in the opposite direction of the thrust vector in the plane perpendicular to the longitudinal axis of the spacecraft, and the thrust vector of the third engine installed in the plane of the longitudinal axis of the spacecraft is directed in the direction opposite to the direction of flight, while the blocks of control liquid thrusters of small thrust are pairwise fixed in diametrically opposite places spacecraft, and in the lines for supplying fuel components to the main manifolds of the control liquid propellant small thrust engines and four pairs of electro-fluid valves connected in parallel to the collectors of corrective-brake engines.

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