CN112412660B - Space power system combining extrusion and electric pump auxiliary pressurization - Google Patents
Space power system combining extrusion and electric pump auxiliary pressurization Download PDFInfo
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- CN112412660B CN112412660B CN202011416273.6A CN202011416273A CN112412660B CN 112412660 B CN112412660 B CN 112412660B CN 202011416273 A CN202011416273 A CN 202011416273A CN 112412660 B CN112412660 B CN 112412660B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/50—Feeding propellants using pressurised fluid to pressurise the propellants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/46—Feeding propellants using pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/56—Control
- F02K9/563—Control of propellant feed pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/56—Control
- F02K9/58—Propellant feed valves
Abstract
The invention provides a space power system for extrusion and electric pump assisted pressurization, aiming at solving the technical problems that the existing extrusion system is low in power performance and heavy in weight and is difficult to meet the requirements of deep space exploration development and use. The invention can reduce the tank pressure of the rail-controlled oxidant storage tank and the rail-controlled fuel storage tank by a mode of extrusion and electric pump auxiliary pressurization, and realizes that the pressure of the rail-controlled thrust chamber reaches the set requirement by the pressurization of the electric pump, thereby achieving the effects of low tank pressure, high thrust chamber pressure and light storage tank weight.
Description
Technical Field
The invention belongs to the technical field of liquid rocket engines, and relates to a space power system combining extrusion and electric pump auxiliary pressurization.
Background
At present, a high-performance space variable thrust engine generally adopts an extrusion type power system as shown in fig. 1, and the principle is as follows: the working conditions of the first adjustable cavitation pipe 109 and the second adjustable cavitation pipe 110 are adjusted through the motor 108, so that the pressure of a propellant entering the rail control thrust chamber 111 is adjusted, and thrust adjustment is realized; this solution requires that the tank pressures of the oxidant tank 104 and the fuel tank 105 are sufficiently high, and therefore the tank wall thickness needs to be made very thick during design, resulting in a heavy overall weight, which cannot meet the requirements of future space missions for high-performance and light-weight space power systems. Particularly, when celestial bodies such as mars and the like are detected, the gravity of the celestial bodies is large, the working time of the orbiter is long, the consumption of the propellant is more, the requirements on the performance and the quality of a power system are higher, and the existing extrusion type system cannot meet the use requirements.
Disclosure of Invention
The invention provides a space power system for extrusion and electric pump assisted pressurization, aiming at solving the technical problems that the existing extrusion system is low in power performance and heavy in weight and is difficult to meet the requirements of deep space exploration development and use.
The technical scheme of the invention is as follows:
the space power system combining extrusion and electric pump auxiliary pressurization is characterized in that: comprises a gas cylinder, a first isolating valve, a first pressure reducer, a second pressure reducer, a rail-controlled oxidant storage box, a rail-controlled fuel storage box, a posture-controlled oxidant storage box, a posture-controlled fuel storage box, a rail-controlled thrust chamber and a posture-controlled thrust chamber;
at least one gas cylinder; when only one gas cylinder is provided, the gas outlet of the gas cylinder is communicated with the inlet ends of the first pressure reducer and the second pressure reducer through the first isolation valve; when a plurality of gas cylinders are arranged, the gas cylinders are arranged in parallel, and the gas outlets of the gas cylinders are communicated with the inlet ends of the first pressure reducer and the second pressure reducer through the first isolation valve; the gas cylinder is filled with inert gas and is used for pressurizing the propellant in the storage tank;
the medium flowing out of the outlet end of the first pressure reducer is divided into two paths, wherein one path enters the attitude control oxidant storage tank, and the other path enters the attitude control fuel storage tank; the attitude control oxidant storage tank and the attitude control fuel storage tank are used for providing a propellant for the attitude control thrust chamber;
the medium flowing out of the outlet end of the second pressure reducer is divided into two paths, wherein one path enters the rail-controlled oxidant storage tank, and the other path enters the rail-controlled fuel storage tank; the rail-controlled oxidant storage tank and the rail-controlled fuel storage tank are used for providing propellant for the rail-controlled thrust chamber;
a second isolation valve, a first booster pump and an oxidant main valve are sequentially arranged on an oxidant supply pipeline between the rail-controlled oxidant storage tank and the oxidant inlet end of the rail-controlled thrust chamber along the oxidant flow direction; a third isolating valve, a second booster pump and a fuel main valve are sequentially arranged on a fuel supply pipeline between the rail-controlled fuel storage tank and the fuel inlet end of the rail-controlled thrust chamber along the fuel flow direction;
the input end of the first booster pump is connected with the output end of the first motor, and the input end of the second booster pump is connected with the output end of the second motor; the first motor and the second motor are controlled by a controller; the controller is powered by a battery.
Furthermore, a branch is divided from a pipeline between the first booster pump and the first main valve, and the branch is communicated with an oxidant supply pipeline between the attitude control oxidant storage tank and the attitude control thrust chamber through a first throttle valve and a first one-way valve; a branch is divided from a pipeline between the second booster pump and the second main valve, and the branch is communicated with a fuel supply pipeline between the attitude control fuel storage tank and the attitude control thrust chamber through a second throttle valve and a second one-way valve.
Further, at least one of the rail-controlled oxidant storage tank and the rail-controlled fuel storage tank is provided; when a plurality of rail-controlled oxidant storage tanks are arranged, the plurality of rail-controlled oxidant storage tanks are arranged in parallel, the inlet ends of the rail-controlled oxidant storage tanks are connected with the outlet end of the second pressure reducer through respective pipelines, and the outlet ends of the rail-controlled oxidant storage tanks are connected with the oxidant inlet ends of a plurality of rail-controlled thrust chambers arranged in parallel through respective pipelines; when the number of the rail-controlled fuel tanks is plural, the plural rail-controlled fuel tanks are arranged in parallel, the inlet ends thereof are all connected with the outlet end of the second pressure reducer through respective pipelines, and the outlet ends thereof are all connected with the fuel inlet ends of the plural rail-controlled thrust chambers arranged in parallel through respective pipelines.
Furthermore, at least one of the attitude control oxidant storage tank and the attitude control fuel storage tank is arranged; when a plurality of attitude control oxidant storage tanks are arranged, the plurality of attitude control oxidant storage tanks are arranged in parallel, the inlet ends of the attitude control oxidant storage tanks are connected with the outlet end of the first pressure reducer through respective pipelines, and the outlet ends of the attitude control oxidant storage tanks are connected with the oxidant inlet ends of a plurality of attitude control thrust chambers arranged in parallel through respective pipelines; when a plurality of attitude control fuel storage tanks are arranged, the plurality of attitude control fuel storage tanks are arranged in parallel, the inlet ends of the attitude control fuel storage tanks are connected with the outlet end of the first pressure reducer through respective pipelines, and the outlet ends of the attitude control fuel storage tanks are connected with the fuel inlet ends of a plurality of attitude control thrust chambers arranged in parallel through respective pipelines.
Furthermore, the first isolation valve, the second isolation valve and the third isolation valve are all electric control valves and are controlled by a controller.
Furthermore, the battery adopts a lithium ion battery which can be repeatedly charged and discharged.
The invention has the beneficial effects that:
1. by the mode of extrusion and auxiliary pressurization of the electric pump, the tank pressure of the rail-controlled oxidant storage tank and the rail-controlled fuel storage tank can be reduced (for example, the tank pressure is reduced to 0.5MPa from 3.4MPa of the existing pure extrusion type system), and the rail-controlled thrust chamber pressure can reach the design requirement (for example, 2MPa) by the pressurization of the electric pump, so that the effects of low tank pressure, high thrust chamber pressure and light storage tank weight are achieved.
2. The invention realizes the regulation of the flow and the pressure of the propellant entering the rail-controlled thrust chamber through the motor and the booster pump, has convenient thrust variation and can realize multiple starting.
3. The battery adopts the lithium ion battery which can be repeatedly charged and discharged, can be charged on the track, and saves energy.
4. The isolation valves in the invention are all electric control valves, and are controlled by the controller together with the motor and the booster pump, so that the intelligent management of the whole machine such as thrust, mixing ratio, residual propellant and the like can be carried out.
5. The invention integrates rail control and attitude control, adopts extrusion gas to supply base box pressure, further increases the pressure supplied to the thrust chamber by the electric pump, gives consideration to the advantages of the extrusion and pumping systems, and is suitable for a space power system for deep space exploration.
Drawings
Fig. 1 is a schematic diagram of a conventional spatial power system using a squeezing method.
FIG. 2 is a schematic diagram of the combined compression and electric pump assisted augmentation spatial power system of the present invention.
The reference numerals in fig. 1 illustrate:
101-a gas cylinder; 102-a first isolation valve; 103-a stress reducer; 104-an oxidant tank; 105-a fuel tank; 106-a second isolation valve; 107-third isolation valve; 108-a motor; 109-a first tunable cavitation tube; 110-a second tunable cavitation tube; 111-rail controlled thrust chamber; 112-attitude control thrust chamber.
The reference numbers in fig. 2 illustrate:
1-a gas cylinder; 2-a first isolation valve; 3-a first pressure reducer; 4-a second stress-reducer; 5-rail control oxidant storage tank; 6-rail controlled fuel storage; 7-a second isolation valve; 8-a third isolation valve; 9-attitude control oxidizer storage tank; 10-attitude control fuel storage tank; 11-a first booster pump; 12-a first electric machine; 13-a second booster pump; 14-a second electric machine; 15-a battery; 16-a controller; 17-an oxidizer main valve; 18-a second one-way valve; 19-a first one-way valve; 20-a first throttle valve; 21-a second throttle valve; 22-rail controlled thrust chamber; 23-attitude control thrust chamber; 24-fuel main valve.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
As shown in figure 1, the space power system combining extrusion and electric pump auxiliary pressurization mainly comprises a gas cylinder 1, a first isolation valve 2, a first pressure reducer 3, a second pressure reducer 4, a rail-controlled oxidant storage tank 5, a rail-controlled fuel storage tank 6, an attitude-controlled oxidant storage tank 9, an attitude-controlled fuel storage tank 10, a rail-controlled thrust chamber 22 and an attitude-controlled thrust chamber 23.
At least one gas cylinder 1; when only one gas cylinder 1 is provided, the gas outlet of the gas cylinder is communicated with the inlet ends of the first pressure reducer 3 and the second pressure reducer 4 through the first isolation valve 2; when a plurality of gas cylinders 1 are arranged, the gas cylinders 1 are arranged in parallel, and gas outlets of the gas cylinders are communicated with inlet ends of a first pressure reducer 3 and a second pressure reducer 4 through a first isolation valve 2; the gas cylinder 1 is filled with inert gas and is used for pressurizing propellant in the storage tank;
the medium flowing out of the outlet end of the first pressure reducer 3 is divided into two paths, one path enters an attitude control oxidant storage tank 9, and the other path enters an attitude control fuel storage tank 10; the attitude control oxidant storage tank 9 and the attitude control fuel storage tank 10 are used for providing a propellant for one or more attitude control thrust chambers 23 arranged in parallel; at least one attitude control oxidant storage tank 9 and at least one attitude control fuel storage tank 10 are arranged; when a plurality of attitude control oxidant storage tanks 9 are arranged, the attitude control oxidant storage tanks 9 are arranged in parallel, the inlet ends of the attitude control oxidant storage tanks are connected with the outlet end of the first pressure reducer 3 through respective pipelines, and the outlet ends of the attitude control oxidant storage tanks are connected with the oxidant inlet ends of a plurality of attitude control thrust chambers 23 arranged in parallel through respective pipelines; when a plurality of attitude control fuel storage tanks 10 are arranged, the attitude control fuel storage tanks 10 are arranged in parallel, the inlet ends of the attitude control fuel storage tanks are connected with the outlet end of the first pressure reducer 3 through respective pipelines, and the outlet ends of the attitude control fuel storage tanks are connected with the fuel inlet ends of a plurality of attitude control thrust chambers 23 arranged in parallel through respective pipelines;
the medium flowing out of the outlet end of the second pressure reducer 4 is divided into two paths, one path enters the rail-controlled oxidant storage tank 5, and the other path enters the rail-controlled fuel storage tank 6; a rail-controlled oxidant tank 5 and a rail-controlled fuel tank 6 for supplying propellant to one or more parallel rail-controlled thrust chambers 22; at least one of the rail-controlled oxidant storage tank 5 and the rail-controlled fuel storage tank 6 is provided; when there are a plurality of rail-controlled oxidant storage tanks 5, the plurality of rail-controlled oxidant storage tanks 5 are arranged in parallel, the inlet ends thereof are all connected with the outlet end of the second pressure reducer 4 through respective pipelines, and the outlet ends thereof are all connected with the oxidant inlet ends of a plurality of rail-controlled thrust chambers 22 arranged in parallel through respective pipelines; when there are a plurality of rail-controlled fuel tanks 6, the plurality of rail-controlled fuel tanks 6 are arranged in parallel, the inlet ends thereof are all connected with the outlet end of the second pressure reducer 4 through respective pipelines, and the outlet ends thereof are all connected with the fuel inlet ends of a plurality of rail-controlled thrust chambers 22 arranged in parallel through respective pipelines;
a second isolation valve 7, a first booster pump 11 and an oxidant main valve 17 are sequentially arranged on an oxidant supply pipeline between the rail-controlled oxidant storage tank 5 and the oxidant inlet end of the rail-controlled thrust chamber 22 along the oxidant flow direction; a third isolating valve 8, a second booster pump 13 and a fuel main valve 24 are sequentially arranged on a fuel supply pipeline between the rail-controlled fuel storage tank 6 and the fuel inlet end of the rail-controlled thrust chamber 22 along the fuel flow direction;
the input end of the first booster pump 11 is connected with the output end of the first motor 12, and the input end of the second booster pump 13 is connected with the output end of the second motor 14; the first motor 12 and the second motor 14 are controlled by a controller 16; the controller 16 is powered by a battery 15;
a branch is branched from a pipeline between the first booster pump 11 and the first main valve 17, and the branch is communicated with an oxidant supply pipeline between the attitude control oxidant storage tank 9 and the attitude control thrust chamber 23 through a first throttle valve 20 and a first one-way valve 19; when the first throttle valve 20 is closed, the bypass is not opened; when the attitude control oxidant storage tank 9 needs to be reversely filled, the first throttling valve 20 is opened, and the first one-way valve 19 can ensure that the oxidant in the rail control oxidant storage tank 5 can only be filled into the attitude control oxidant storage tank 9 without backflow;
a branch is branched from a pipeline between the second booster pump 13 and the second main valve 24, and the branch is communicated with a fuel supply pipeline between the attitude control fuel storage tank 10 and the attitude control thrust chamber 23 through a second throttle valve 21 and a second one-way valve 18; when the second throttle valve 21 is closed, the bypass is not opened; when reverse filling of the attitude control fuel tank 10 is required, the second throttle valve 21 is opened, and the second check valve 18 can ensure that the fuel in the rail control fuel tank 6 can only be filled into the attitude control fuel tank 10 without backflow.
The first isolation valve 2, the second isolation valve 7 and the third isolation valve 8 are all electrically controlled valves and are controlled by a controller 16.
The working process and principle of the invention are as follows:
a rail-controlled oxidant storage box 5 and a rail-controlled fuel storage box 6 are used for providing propellant for a rail-controlled thrust chamber 22, and an attitude-controlled oxidant storage box 9 and an attitude-controlled fuel storage box 10 are used for providing propellant for an attitude-controlled thrust chamber 23;
initial tank pressures of the rail-controlled oxidant storage tank 5, the rail-controlled fuel storage tank 6, the attitude-controlled oxidant storage tank 9 and the attitude-controlled fuel storage tank 10 are provided through the extrusion of the gas cylinder 1, the controller 16 controls the first motor 12 to drive the first booster pump 11 and the second motor 14 to drive the second booster pump 13 to adjust the pressure of a propellant (oxidant and fuel) entering the rail-controlled thrust chamber 22, so that the propellant is further pressurized, and compared with a traditional extrusion type space power system, the tank pressure requirements of the rail-controlled oxidant storage tank 5 and the rail-controlled fuel storage tank 6 are reduced, so that the wall thicknesses of the rail-controlled oxidant storage tank 5 and the rail-controlled fuel storage tank 6 can be reduced, the weights of the rail-controlled oxidant storage tank 5 and the rail-controlled fuel storage tank 6 are reduced, and the weight of the whole space power system is further reduced; in addition, because the pressure in the rail-controlled oxidant storage tank 5 and the rail-controlled fuel storage tank 6 is reduced, the volume of the required gas cylinder 1 can be further reduced, and the weight of the whole space power system can be further reduced;
when the propellants in the attitude control oxidant storage tank 9 and the attitude control fuel storage tank 10 are insufficient, the propellants in the rail control oxidant storage tank 5 and the rail control fuel storage tank 6 can be input into the attitude control oxidant storage tank 9 and the attitude control fuel storage tank 10 by opening the first throttle valve 20 and the second throttle valve 21.
The design capacity of the attitude control oxidant storage tank 9 and the attitude control fuel storage tank 10 can be the propellant amount of single work (such as 900s), and although the propellant amount is still supplied by air bottle extrusion, the propellant amount is small and the weight is light. When the single-time operation is finished, the first throttle valve 20 and the second throttle valve 21 are closed, each storage tank respectively supplies a corresponding thrust chamber, after the single-time operation is finished, the propellant in the attitude control oxidant storage tank 9 and the propellant in the attitude control fuel storage tank 10 are consumed, the first throttle valve 20 and the second throttle valve 21 are opened, the attitude control oxidant storage tank 9 and the attitude control fuel storage tank 10 are respectively and reversely filled by the rail control oxidant storage tank 5 and the rail control fuel storage tank 6, and the propellant is supplemented, so that the multiple-time operation is realized.
The technical effect comparison shows that:
1. with reference to the schematic diagram of the existing extrusion type space power system shown in fig. 1, a mars detection space power system with 7500N thrust, single working time 900s, and accumulated working time 4500s is taken as an example:
two gas cylinders 101 with the density of 1300kg/m3The composite material gas cylinder is pressurized by helium, the pressure of the gas cylinder is 35MPa, and the mass of the gas cylinder is 65.8 kg;
two rail-controlled oxidant storage tanks 104 are provided, the pressure of the storage tanks is 3.4MPa, and the total mass is 68 kg;
two rail-controlled fuel storage tanks 105 are provided, the pressure of the storage tanks is 3.4MPa, and the total mass is 27.3 kg;
one motor 108 with a mass of 2 kg;
one each of the first adjustable cavitation pipe 109 and the second adjustable cavitation pipe 110, the total mass being 0.2 kg;
the total mass of the first isolation valve 102, the second isolation valve 106 and the third isolation valve 107 is 0.9 kg;
two rail-controlled thrust chambers 111 are provided, the chamber pressure is 2MPa, and the mass is 26 kg;
the attitude control thrust chambers are 112 sixteen, and the total mass is 8 kg;
the total space power system weight is about 198.2 kg.
2. With reference to the schematic diagram of the extrusion and electric pump assisted pressurization combined space power system shown in fig. 2, a mars detection space power system with 7500N thrust, single working time 900s and accumulated working time 4500s is taken as an example:
two gas cylinders 1 with the density of 1300kg/m3The composite material gas cylinder is pressurized by helium, the pressure of the gas cylinder is 35MPa, and as the pressure of the storage tank is reduced, the gas supply amount is reduced, the volume of the gas cylinder is reduced, and the total mass is 11.3 kg;
two rail-controlled oxidant storage tanks 5 are provided, the pressure of the storage tanks is 0.5MPa, and the total mass is 28 kg;
two rail-controlled fuel storage tanks 6 are provided, the pressure of the storage tanks is 0.5MPa, and the total mass is 10 kg;
the mass of the attitude control oxidant storage tank is 9kg, and the mass of the attitude control oxidant storage tank is 2.5 kg;
the attitude control fuel storage tank has 10 and the mass is 1 kg;
two groups of motor pumps (11, 12, 13 and 14) with the total mass of 12 kg;
15 lithium ion batteries with the mass of 6.8 kg;
one controller 16 with a mass of 4 kg;
a first isolation valve 2, a second isolation valve 7 and a third isolation valve 8, the total mass being 0.9 kg;
two rail-controlled thrust chambers 22 are provided, the chamber pressure is 2MPa, and the mass is 26 kg;
the attitude control thrust chambers are 23 sixteen, and the total mass is 8 kg;
the combined space power system weight of the present embodiment of compression and electric pump assisted boost amounts to about 110.5 kg.
Through the comparison, the space power system combining extrusion and electric pump auxiliary pressurization achieves the same thrust, and compared with the existing constant-pressure extrusion power system, the weight of the space power system is reduced by 87.7 kg.
Claims (5)
1. Space driving system that extrusion and electric pump assist pressure boost combine, its characterized in that: comprises a gas cylinder (1), a first isolating valve (2), a first pressure reducer (3), a second pressure reducer (4), a rail-controlled oxidant storage box (5), a rail-controlled fuel storage box (6), a posture-controlled oxidant storage box (9), a posture-controlled fuel storage box (10), a rail-controlled thrust chamber (22) and a posture-controlled thrust chamber (23);
at least one gas cylinder (1); when only one gas cylinder (1) is provided, the gas outlet of the gas cylinder is communicated with the inlet ends of the first pressure reducer (3) and the second pressure reducer (4) through the first isolation valve (2); when a plurality of gas cylinders (1) are arranged, the gas cylinders (1) are arranged in parallel, and gas outlets of the gas cylinders are communicated with inlet ends of a first pressure reducer (3) and a second pressure reducer (4) through a first isolation valve (2); the gas cylinder (1) is filled with inert gas and is used for pressurizing propellant in the storage tank;
the medium flowing out of the outlet end of the first pressure reducer (3) is divided into two paths, one path enters an attitude control oxidant storage tank (9), and the other path enters an attitude control fuel storage tank (10); the attitude control oxidant storage tank (9) and the attitude control fuel storage tank (10) are used for providing a propellant for the attitude control thrust chamber (23);
the medium flowing out of the outlet end of the second pressure reducer (4) is divided into two paths, one path enters the rail-controlled oxidant storage tank (5), and the other path enters the rail-controlled fuel storage tank (6); the rail-controlled oxidant storage tank (5) and the rail-controlled fuel storage tank (6) are used for supplying propellant to the rail-controlled thrust chamber (22);
a second isolation valve (7), a first booster pump (11) and an oxidant main valve (17) are sequentially arranged on an oxidant supply pipeline between the rail-controlled oxidant storage tank (5) and the oxidant inlet end of the rail-controlled thrust chamber (22) along the oxidant flow direction; a third isolating valve (8), a second booster pump (13) and a fuel main valve (24) are sequentially arranged on a fuel supply pipeline between the rail-controlled fuel storage tank (6) and the fuel inlet end of the rail-controlled thrust chamber (22) along the fuel flow direction;
the input end of the first booster pump (11) is connected with the output end of a first motor (12), and the input end of the second booster pump (13) is connected with the output end of a second motor (14); the first motor (12) and the second motor (14) are controlled by a controller (16); the controller (16) is powered by the battery (15);
at least one attitude control oxidant storage tank (9) and at least one attitude control fuel storage tank (10) are arranged; when a plurality of attitude control oxidant storage tanks (9) are arranged, the attitude control oxidant storage tanks (9) are arranged in parallel, the inlet ends of the attitude control oxidant storage tanks are connected with the outlet end of the first pressure reducer (3) through respective pipelines, and the outlet ends of the attitude control oxidant storage tanks are simultaneously connected with the oxidant inlet ends of a plurality of attitude control thrust chambers (23) which are arranged in parallel through respective pipelines; when a plurality of attitude control fuel storage tanks (10) are arranged, the attitude control fuel storage tanks (10) are arranged in parallel, the inlet ends of the attitude control fuel storage tanks are connected with the outlet end of the first pressure reducer (3) through respective pipelines, and the outlet ends of the attitude control fuel storage tanks are simultaneously connected with the fuel inlet ends of a plurality of attitude control thrust chambers (23) which are arranged in parallel through respective pipelines.
2. The combination squeeze and motor-pump assisted boost space power system according to claim 1, wherein: a branch is divided from a pipeline between the first booster pump (11) and the oxidant main valve (17), and the branch is communicated with an oxidant supply pipeline between the attitude control oxidant storage tank (9) and the attitude control thrust chamber (23) through a first throttle valve (20) and a first one-way valve (19); a branch is branched from a pipeline between the second booster pump (13) and the fuel main valve (24), and the branch is communicated with a fuel supply pipeline between the attitude control fuel storage tank (10) and the attitude control thrust chamber (23) through a second throttle valve (21) and a second one-way valve (18).
3. A space power system combining compression and electric pump assisted supercharging according to claim 1 or 2, characterized in that: at least one rail-controlled oxidant storage tank (5) and at least one rail-controlled fuel storage tank (6) are arranged; when a plurality of rail-controlled oxidant storage tanks (5) are arranged, the plurality of rail-controlled oxidant storage tanks (5) are arranged in parallel, the inlet ends of the rail-controlled oxidant storage tanks are connected with the outlet end of the second pressure reducer (4) through respective pipelines, and the outlet ends of the rail-controlled oxidant storage tanks are simultaneously connected with the oxidant inlet ends of a plurality of rail-controlled thrust chambers (22) which are arranged in parallel through respective pipelines; when the rail-controlled fuel storage tanks (6) are multiple, the multiple rail-controlled fuel storage tanks (6) are arranged in parallel, the inlet ends of the multiple rail-controlled fuel storage tanks are connected with the outlet end of the second pressure reducer (4) through respective pipelines, and the outlet ends of the multiple rail-controlled fuel storage tanks are simultaneously connected with the fuel inlet ends of the multiple rail-controlled thrust chambers (22) arranged in parallel through respective pipelines.
4. The combination squeeze and motor-pump assisted boost space power system according to claim 3, wherein: the first isolation valve (2), the second isolation valve (7) and the third isolation valve (8) are all electric control valves and are controlled by a controller (16).
5. The combination squeeze and motor-pump assisted boost space power system according to claim 4, wherein: the battery (15) is a lithium ion battery which can be repeatedly charged and discharged.
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| CN113944570B (en) * | 2021-08-31 | 2023-02-03 | 北京航空航天大学 | Track control method based on electric pump engine and computing equipment |
| CN114408222B (en) * | 2021-12-20 | 2023-07-14 | 上海空间推进研究所 | Pneumatic supercharged engine system |
| CN114291300B (en) * | 2021-12-21 | 2024-03-29 | 上海空间推进研究所 | Ground-moon shuttle aircraft propulsion system |
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