CN108730071B - Multidirectional supplementary propulsion system - Google Patents
Multidirectional supplementary propulsion system Download PDFInfo
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- CN108730071B CN108730071B CN201810322660.XA CN201810322660A CN108730071B CN 108730071 B CN108730071 B CN 108730071B CN 201810322660 A CN201810322660 A CN 201810322660A CN 108730071 B CN108730071 B CN 108730071B
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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
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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 multidirectional supplementary propulsion system, which comprises an oxygen path component, a fuel path component, a butt joint component and an engine; the oxygen path component stores and conveys oxidant, and the fuel path component stores and conveys fuel; the oxygen path assembly and the fuel path assembly are both connected to the engine; the oxygen path butt joint component and the fuel path butt joint component are respectively connected with the oxygen path component and the fuel path component; the docking interface component comprises any one or more of the following: a forward orientation docking interface; a radially oriented docking port; a docking port in a rearward orientation. The invention is designed for the integration of propulsion and supplement, and realizes the switching of the propulsion and supplement functions of the system through the switch of the valve; the on-orbit propellant replenishing in multiple directions such as the forward direction, the backward direction, the radial direction and the like is realized, and the condition that the replenishing function cannot be finished due to the failure of a certain butt joint of the replenished aircraft or the occupation of a certain butt joint by other aircraft is avoided.
Description
Technical Field
The invention relates to the field of aerospace, in particular to a multi-way supplement propulsion system, and particularly relates to a forward, backward, radial and bypass supplement propulsion system.
Background
The on-orbit service life of a spacecraft is directly related to the carried propellant amount, and for a large aircraft with long service life, the flight with the whole service life cannot be realized through one-time carrying of the propellant, so that the on-orbit propellant supplement is a key technology with long service life.
For the aircraft needing to be supplemented for many times, in order to increase the reliability of a supplementing system, supplementing ports are added in different butt joint directions as much as possible. Meanwhile, if the in-orbit propellant replenishing function is realized, the aircrafts need to be crossed and butted firstly, however, the interfaces of some replenished aircrafts and the replenishing and replenishing aircrafts butting device or the added aircrafts are the active end or the added aircrafts are the passive end, and the vehicles cannot be directly crossed and butted, so that one aircraft is required to serve as a connecting bridge and is respectively butted with the replenishing aircrafts and the replenishing aircrafts, and the in-orbit propellant replenishing function is realized.
Disclosure of Invention
In view of the deficiencies in the prior art, it is an object of the present invention to provide a multi-directional supplemental propulsion system.
The multidirectional supplement propulsion system provided by the invention comprises an oxygen path component, a fuel path component, a butt joint component and an engine;
the oxygen path component stores and delivers an oxidant, and the fuel path component stores and delivers a fuel; the oxygen path assembly and the fuel path assembly are both connected to the engine;
the oxygen path butt joint component and the fuel path butt joint component are respectively connected with the oxygen path component and the fuel path component;
the docking interface component comprises any one or more of the following:
-a forward oriented docking port;
-a radially oriented docking port;
-a docking port in a rearward orientation.
Preferably, the oxygen path assembly comprises an oxygen path gas cylinder, a self-locking valve V3, a first pressure reducer, an oxidant storage tank, a self-locking valve V7 and a self-locking valve V9;
one end of the oxygen path gas cylinder, the self-locking valve V3, the first pressure reducer and the oxidant storage tank are connected in sequence; the other end of the oxidant storage tank is divided into two oxygen path branches, and the two oxygen path branches are respectively connected with the engine and the oxygen path interface assembly through a self-locking valve V7 and a self-locking valve V9.
Preferably, the fuel line assembly comprises a fuel line gas cylinder, a self-locking valve V4, a second pressure reducer, a fuel storage tank, a self-locking valve V8, a self-locking valve V10;
one end of the fuel gas cylinder, the self-locking valve V4, the second pressure reducer and the fuel storage tank are connected in sequence; the other end of the fuel storage tank is divided into two fuel path branches, and the two oxygen path branches are respectively connected with the engine and the fuel path butt joint component through a self-locking valve V8 and a self-locking valve V10.
Preferably, the oxygen path component also comprises an oxygen path discharge port and a self-locking valve V15;
one end of the self-locking valve V9 is connected with the oxidant storage tank; the other end of the self-locking valve V9, the self-locking valve V15 and an oxygen passage discharge port are connected in sequence;
the fuel circuit assembly also comprises a fuel circuit discharge port and a self-locking valve V16;
one end of the self-locking valve V10 is connected with the fuel storage tank; the other end of the self-locking valve V10, the self-locking valve V16 and the fuel way discharge port are connected in sequence.
Preferably, the oxygen path pair interface assembly comprises an oxygen path forward interface, an oxygen path radial interface, an oxygen path backward interface, a self-locking valve V11, a self-locking valve V13 and a self-locking valve V17;
the oxygen path forward butt joint port, the oxygen path radial butt joint port and the oxygen path backward butt joint port are respectively connected to the other end of the self-locking valve V9 through a self-locking valve V11, a self-locking valve V13 and a self-locking valve V17.
Preferably, the fuel path butt joint assembly comprises a fuel path forward butt joint, a fuel path backward butt joint, a latching valve V12, a latching valve V14, and a latching valve V18;
the fuel path forward butt joint port, the fuel path forward butt joint port and the fuel path backward butt joint port are respectively connected to the other end of the self-locking valve V10 through a self-locking valve V12, a self-locking valve V14 and a self-locking valve V18.
Preferably, a gas pressurizing device is also included;
the gas supercharging device is respectively connected with one end of an oxygen path gas cylinder, a fuel path gas cylinder, one end of an oxidant storage tank and one end of a fuel storage tank through a self-locking valve V1, a self-locking valve V2, a self-locking valve V5 and a self-locking valve V6.
Preferably, any one or more of the following positions are provided with pressure sensors:
an oxygen cylinder; a gas cylinder; one end of the oxidant reservoir; the other end of the oxidant storage tank; one end of the fuel reservoir; the other end of the fuel tank; the other end of the self-locking valve V9; the other end of the latching valve V10.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention is designed for the integration of propulsion and supplement, and realizes the switching of the propulsion and supplement functions of the system through the switch of the valve;
2. the on-orbit propellant replenishing in multiple directions such as the forward direction, the backward direction, the radial direction and the like is realized, and the condition that the replenishing function cannot be finished due to the failure of a certain butt joint of the replenished aircraft or the occupation of a certain butt joint by other aircraft is avoided;
3. the function of adding the propellant in the on-track way is realized, the butt joint device is helped to realize butt joint for two aircrafts with the same polarity, and the propellant is added in the on-track way.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic structural view of a multi-directionally supplemented propulsion system provided by the present invention;
FIG. 2 is a schematic view of the docking of a supplemental aircraft with a forward docking interface;
FIG. 3 is a schematic view of the docking of a supplemental aircraft with a rearward docking interface;
FIG. 4 is a schematic view of the docking of a supplemental aircraft with a radial docking interface;
FIG. 5 is a schematic view of the supplemental aircraft docking with the forward docking interface and the supplemental aircraft docking with the aft docking interface;
FIG. 6 is a schematic view of the docking of a supplemental aircraft with a forward facing interface and the docking of a supplemental aircraft with a radial interface.
The figures show that:
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications can be made by persons skilled in the art without departing from the spirit of the invention. All falling within the scope of the present invention.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention.
As shown in fig. 1, the present invention provides a multi-way supplemental propulsion system comprising an oxygen path assembly that stores and delivers an oxidant, a fuel path assembly that stores and delivers a fuel, a docking port assembly, and an engine 6. The oxidant and the fuel both belong to propellants of the aircraft, the oxygen path assembly comprises an oxidant supplement pipeline, and the fuel path assembly comprises a fuel supplement pipeline. The oxygen way assembly and the fuel way assembly are both connected to the engine 6, and the engine 6 can realize the propelling function of the structure of the invention. The oxygen path butt joint component and the fuel path butt joint component are formed by the butt joint component, the oxygen path butt joint component and the fuel path butt joint component are respectively connected with the oxygen path component and the fuel path component, and the butt joint component comprises any one or more of the following butt joints: a forward orientation docking interface; a radially oriented docking port; and a backward oriented docking interface, wherein the docking interface assembly is used for docking between other aircraft (such as the supplemental aircraft 17 and/or the supplemented aircraft 18) and the invention, thereby completing the propellant feeding and supplementing operation.
The oxygen path component comprises an oxygen path gas cylinder 1, a self-locking valve V3, a first pressure reducer 15, an oxidant storage tank 3, a self-locking valve V7 and a self-locking valve V9. One ends of the oxygen path gas cylinder 1, the self-locking valve V3, the first pressure reducer 15 and the oxidant storage tank 3 are connected in sequence; the other end of the oxidant storage tank 3 is divided into two oxygen path branches, and the two oxygen path branches are respectively connected with the engine 6 and the oxygen path interface assembly through a self-locking valve V7 and a self-locking valve V9. The fuel path assembly comprises a fuel path gas bottle 2, a self-locking valve V4, a second pressure reducer 16, a fuel storage tank 4, a self-locking valve V8 and a self-locking valve V10. The fuel gas bottle 2, the self-locking valve V4, the second pressure reducer 16 and one end of the fuel storage tank 4 are connected in sequence; the other end of the fuel storage tank 4 is divided into two fuel path branches, and the two oxygen path branches are respectively connected with the engine 6 and the fuel path butt joint component through a self-locking valve V8 and a self-locking valve V10. The oxygen path component also comprises an oxygen path discharge port 13 and a self-locking valve V15; one end of the self-locking valve V9 is connected with the oxidant storage tank 3; the other end of the self-locking valve V9, the self-locking valve V15 and the oxygen passage discharge port 13 are connected in sequence. The fuel circuit assembly further comprises a fuel circuit discharge port 14 and a self-locking valve V16; one end of the self-lock valve V10 is connected to the fuel tank 4; the other end of the self-locking valve V10, the self-locking valve V16 and the fuel way discharge port 14 are connected in sequence. The oxygen path discharge port 13 can exhaust the residual oxidant in the oxidant supplementing pipeline; residual fuel in the fuel replenishment line is evacuated through the fuel line vent 14 to prevent residual propellant contamination of the docking assembly upon subsequent aircraft separation. In practical application, one end of the oxidant storage tank 3 and one end of the oxygen material storage tank correspond to an air cavity of the storage tank, and the other end of the oxidant storage tank 3 and the other end of the oxygen material storage tank correspond to a liquid cavity of the storage tank.
In one embodiment, the oxygen port-to-port assembly comprises an oxygen port forward port 11, an oxygen port radial port 9, an oxygen port backward port 7, a latching valve V11, a latching valve V13, and a latching valve V17; the oxygen path forward butt joint port 11, the oxygen path radial butt joint port 9 and the oxygen path backward butt joint port 7 are connected to the other end of the latching valve V9 through the latching valve V11, the latching valve V13 and the latching valve V17, respectively. The fuel path butt joint assembly comprises a fuel path forward butt joint port 12, a fuel path backward butt joint port 10, a fuel path backward butt joint port 8, a self-locking valve V12, a self-locking valve V14 and a self-locking valve V18; the fuel path forward butt joint port 12, the fuel path forward butt joint port 10, and the fuel path backward butt joint port 8 are connected to the other end of the latching valve V10 through a latching valve V12, a latching valve V14, and a latching valve V18, respectively. By providing a forward orientation interface, a radial orientation interface, and a backward orientation interface simultaneously, the failure of a certain interface by the replenishment aircraft 18, or the failure of the replenishment function by another aircraft due to the occupation of a certain interface by another aircraft, is avoided.
In the embodiment, the multi-way replenishing propulsion system further comprises a gas pressurizing device 5, the gas pressurizing device 5 is respectively connected with one end of the oxygen path gas cylinder 1, one end of the fuel path gas cylinder 2, one end of the oxidant storage tank 3 and one end of the fuel storage tank 4 through a self-locking valve V1, a self-locking valve V2, a self-locking valve V5 and a self-locking valve V6, and the recycling of pressurized gas is realized through the arrangement of the gas pressurizing device 5. In addition, pressure sensors are provided at any one or more of the following positions: an oxygen cylinder 1 (corresponding to a pressure sensor P1); a gas cylinder 2 (corresponding to the pressure sensor P2); one end of the oxidizer tank 3 (corresponding to the pressure sensor P3); the other end of the oxidizer tank 3 (corresponding to the pressure sensor P7); one end of the fuel tank 4 (corresponding to the pressure sensor P4); the other end of the fuel tank 4 (corresponding to the pressure sensor P8); the other end of the latching valve V9 (corresponding to pressure sensor P5); the other end of the latching valve V10 (corresponding to pressure sensor P6). The pressure sensor can be used for measuring and monitoring the pressure of the gas cylinder, the storage tank and the supplementing pipeline.
The working principle is as follows:
1) the self-locking valve V3 is opened, the gas in the oxygen path gas cylinder 1 is decompressed to working pressure through the first decompressor 15, and the pressurization of the oxidant storage tank 3 is realized; the self-locking valve V4 is opened, the gas in the fuel gas bottle 2 is decompressed to working pressure through the second decompressor 16, and the fuel storage tank 4 is pressurized; the self-locking valve V7 and the self-locking valve V8 are opened, the propellant in the oxidant storage tank 3 and the propellant in the fuel storage tank 4 are filled in a pipeline, the engine 6 is opened, and the engine 6 starts to work, so that the propelling function is realized;
2) opening the self-locking valve V5, starting the gas supercharging device 5, and opening the self-locking valve V1 to realize the process of supercharging and pumping the gas in the gas cavity of the oxidant storage tank 3 to the oxygen path gas cylinder 1; opening the self-locking valve V6, starting the gas supercharging device 5, opening the self-locking valve V2, and realizing the process that the gas in the gas cavity of the fuel storage tank 4 is supercharged and pumped back to the gas cylinder 2;
3) when the supplementary aircraft 17 is butted through the butt joint port in the forward direction, the oxidant path of the supplementary aircraft 17 is connected with the forward butt joint port 11 of the oxygen path, and the self-locking valve V11 and the self-locking valve V9 are opened to realize oxidant supplement to the oxidant storage tank 3; the fuel path of the aircraft 17 is supplemented with fuel to the fuel storage tank 4 by connecting the fuel path with the forward butt joint port 12 and opening the self-locking valve V12 and the self-locking valve V10, as shown in FIG. 2;
4) when the supplementary aircraft 17 is butted with the butt joint port in the backward direction, the oxidant path of the supplementary aircraft 17 is connected with the oxygen path and then butted with the butt joint port 7, and the self-locking valve V17 and the self-locking valve V9 are opened to realize oxidant supplement to the oxidant storage tank 3; the fuel path of the aircraft 17 is supplemented with fuel to the interface 8 after being connected with the fuel path, and the self-locking valve V18 and the self-locking valve V10 are opened to realize the fuel supplement to the fuel storage tank 4, as shown in FIG. 3;
5) when the supplementary aircraft 17 is butted through the butt joint port in the radial direction, the oxidant path of the supplementary aircraft 17 is connected with the radial butt joint port 9 of the oxygen path, and the self-locking valve V13 and the self-locking valve V9 are opened to realize oxidant supplement to the oxidant storage tank 3; the fuel path of the aircraft 17 is supplemented to the interface 10 through the connecting fuel path, and the self-locking valve V14 and the self-locking valve V10 are opened to realize the fuel supplement to the fuel storage tank 4, as shown in FIG. 4;
6) when the replenishing aircraft 17 is butted through the butt joint port in the forward direction and the added aircraft is butted through the butt joint port in the backward direction, the added aircraft can be connected with the oxidant path of the replenished aircraft 18 through the oxygen path backward butt joint port 7, the oxygen path forward butt joint port 11 is connected with the oxidant path of the replenishing aircraft 17, and the through-path replenishing function of the replenishing aircraft 17 for replenishing oxidant to the replenished aircraft 18 is realized by opening the self-locking valve V17 and the self-locking valve V11; the fuel path of the aircraft 18 to be supplemented can be connected through the fuel path backward butt joint port 8, the fuel path forward butt joint port 12 is connected with the fuel path of the aircraft 17 to be supplemented, and the self-locking valve V18 and the self-locking valve V12 are opened to realize the function of passing the way and supplementing the aircraft 17 to the aircraft 18 to be supplemented for supplementing fuel, as shown in FIG. 5;
7) when the supplementary aircraft 17 is butted through the butt joint port in the forward direction and the added aircraft is butted through the butt joint port in the radial direction, the oxygen path can be connected to the oxidant path of the supplementary aircraft 18 through the radial butt joint port 9, the oxygen path forward butt joint port 11 is connected to the oxidant path of the supplementary aircraft 17, and the through-path supplementary function of the supplementary aircraft 17 for supplementing oxidant to the supplementary aircraft 18 is realized by opening the self-locking valve V13 and the self-locking valve V11; the fuel circuit of the supplemented aircraft 18 can be connected to the interface 10 through a fuel path, the fuel circuit is connected to the interface 12 in front of the interface and is connected with the fuel circuit of the supplemented aircraft 17, and the self-locking valve V14 and the self-locking valve V12 are opened to realize the bypass supplementing function of the supplemented aircraft 17 for supplementing fuel to the supplemented aircraft 18, as shown in FIG. 6.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes and modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (5)
1. A multi-way supplemental propulsion system, comprising an oxygen path assembly, a fuel path assembly, a docking port assembly, and an engine (6);
the oxygen path component stores and delivers an oxidant, and the fuel path component stores and delivers a fuel; the oxygen path component and the fuel path component are both connected to an engine (6);
the oxygen path butt joint component and the fuel path butt joint component are respectively connected with the oxygen path component and the fuel path component;
the docking interface assembly comprises any of the following docking interfaces:
-a forward oriented docking port;
-a radially oriented docking port;
-a docking port in a rearward orientation;
the oxygen path component comprises an oxygen path gas cylinder (1), a self-locking valve V3, a first pressure reducer (15), an oxidant storage tank (3), a self-locking valve V7 and a self-locking valve V9;
one end of the oxygen path gas cylinder (1), the self-locking valve V3, the first pressure reducer (15) and the oxidant storage tank (3) are connected in sequence; the other end of the oxidant storage tank (3) is divided into two oxygen path branches, and the two oxygen path branches are respectively connected with the engine (6) and the oxygen path interface assembly through a self-locking valve V7 and a self-locking valve V9;
the fuel path assembly comprises a fuel path gas bottle (2), a self-locking valve V4, a second pressure reducer (16), a fuel storage tank (4), a self-locking valve V8 and a self-locking valve V10;
one ends of the gas cylinder (2), the self-locking valve V4, the second pressure reducer (16) and the fuel storage box (4) are connected in sequence; the other end of the fuel storage tank (4) is divided into two fuel path branches, and the two oxygen path branches are respectively connected with the engine (6) and the fuel path butt joint component through a self-locking valve V8 and a self-locking valve V10;
the oxygen path component also comprises an oxygen path discharge port (13) and a self-locking valve V15;
one end of the self-locking valve V9 is connected with the oxidant storage tank (3); the other end of the self-locking valve V9, the self-locking valve V15 and an oxygen passage discharge port (13) are connected in sequence;
the fuel circuit assembly further comprises a fuel circuit discharge port (14) and a self-locking valve V16;
one end of the self-locking valve V10 is connected with the fuel storage tank (4); the other end of the self-locking valve V10, the self-locking valve V16 and the fuel way discharge port (14) are connected in sequence.
2. The multi-feed propulsion system of claim 1, wherein the oxygen port docking port assembly comprises an oxygen port forward docking port (11), an oxygen port radial docking port (9), an oxygen port aft docking port (7), a latching valve V11, a latching valve V13, and a latching valve V17;
the oxygen path forward butt joint port (11), the oxygen path radial butt joint port (9) and the oxygen path backward butt joint port (7) are respectively connected to the other end of the self-locking valve V9 through a self-locking valve V11, a self-locking valve V13 and a self-locking valve V17.
3. The multi-feed propulsion system of claim 2, wherein the fuel path docking port assembly comprises a fuel path forward docking port (12), a fuel path forward docking port (10), a fuel path aft docking port (8), a latching valve V12, a latching valve V14, and a latching valve V18;
the fuel path forward butt joint port (12), the fuel path forward butt joint port (10) and the fuel path backward butt joint port (8) are respectively connected to the other end of the self-locking valve V10 through a self-locking valve V12, a self-locking valve V14 and a self-locking valve V18.
4. A multi-fed propulsion system according to claim 3, further comprising a gas pressurising means (5);
the gas supercharging device (5) is respectively connected with one end of the oxygen path gas cylinder (1), the fuel path gas cylinder (2), one end of the oxidant storage tank (3) and one end of the fuel storage tank (4) through a self-locking valve V1, a self-locking valve V2, a self-locking valve V5 and a self-locking valve V6.
5. The multi-fed propulsion system of claim 4, wherein pressure sensors are provided at any one or more of the following locations:
an oxygen cylinder (1); a gas cylinder (2); one end of the oxidant storage tank (3); the other end of the oxidant storage tank (3); one end of the fuel storage tank (4); the other end of the fuel storage tank (4); the other end of the self-locking valve V9; the other end of the latching valve V10.
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| CN109515759B (en) * | 2018-11-15 | 2020-11-10 | 中国空间技术研究院 | Static orbit communication satellite propulsion system with optimized manufacturability |
| CN109281774B (en) * | 2018-12-03 | 2019-12-06 | 上海空间推进研究所 | Electric pump pressure type liquid oxygen methane space propulsion system |
| CN110131073B (en) * | 2019-05-06 | 2022-02-18 | 上海空间推进研究所 | Space propulsion system suitable for filling of large-capacity storage tank |
| CN110566369A (en) * | 2019-08-27 | 2019-12-13 | 上海空间推进研究所 | Pressure supplementing type space propulsion system suitable for high-capacity surface tension storage tank |
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