CN114889850B - Double-component attitude and orbit control power device and aircraft with same - Google Patents
Double-component attitude and orbit control power device and aircraft with same Download PDFInfo
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- CN114889850B CN114889850B CN202210809721.1A CN202210809721A CN114889850B CN 114889850 B CN114889850 B CN 114889850B CN 202210809721 A CN202210809721 A CN 202210809721A CN 114889850 B CN114889850 B CN 114889850B
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- 239000003380 propellant Substances 0.000 claims abstract description 78
- 239000000446 fuel Substances 0.000 claims description 48
- 239000007800 oxidant agent Substances 0.000 claims description 48
- 238000002347 injection Methods 0.000 claims description 2
- 239000007924 injection Substances 0.000 claims description 2
- 230000010354 integration Effects 0.000 abstract description 9
- 239000000306 component Substances 0.000 description 40
- 230000001590 oxidative effect Effects 0.000 description 32
- -1 regions Substances 0.000 description 5
- 238000010586 diagram Methods 0.000 description 3
- WFPZPJSADLPSON-UHFFFAOYSA-N dinitrogen tetraoxide Chemical compound [O-][N+](=O)[N+]([O-])=O WFPZPJSADLPSON-UHFFFAOYSA-N 0.000 description 2
- 238000005096 rolling process Methods 0.000 description 2
- 238000010146 3D printing Methods 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000000295 complement effect Effects 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- HDZGCSFEDULWCS-UHFFFAOYSA-N monomethylhydrazine Chemical compound CNN HDZGCSFEDULWCS-UHFFFAOYSA-N 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/402—Propellant tanks; Feeding propellants
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/242—Orbits and trajectories
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/244—Spacecraft control systems
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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
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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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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Radar, Positioning & Navigation (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Abstract
The invention relates to a bipropellant attitude and orbit control power device and an aircraft with the same, wherein the bipropellant attitude and orbit control power device comprises a main body, two thrust chambers and four electromagnetic valves, wherein two propellant inlets are arranged at intervals on a first side of the main body, a plurality of flow channels for the circulation of a propellant are arranged in the main body, two bosses extend out from a second side of the main body opposite to the first side, and an included angle is formed between the two bosses; the two thrust chambers are respectively arranged on the two bosses, and each thrust chamber is arranged to be simultaneously communicated with the two propellant inlets; the four electromagnetic valves are installed on the third side and the fourth side of the main body in a pairwise mode, the third side and the fourth side are oppositely arranged and are located between the first side and the second side, and each electromagnetic valve is communicated with one propellant inlet and one thrust chamber respectively to control the propellant to flow from the propellant inlet to the thrust chamber. The double-component attitude and orbit control power device provided by the invention has the advantages of simple and reliable structure and high integration level.
Description
Technical Field
The invention belongs to the technical field of space aircrafts, and particularly relates to a two-component attitude and orbit control power device and an aircraft with the same.
Background
The attitude and orbit control engine is widely applied to the spacecraft, is a key execution component for determining the attitude adjustment and the orbit control of the spacecraft, is a core component of the spacecraft, and generally needs to adopt a two-component power system for the attitude and orbit control engine with higher requirement on specific impulse.
The existing two-component attitude and orbit control power system usually comprises a plurality of engines, and the problems of multiple pipelines, complex structure, large overall mass and large occupied space exist because the plurality of engines are required to be arranged in a limited space.
Disclosure of Invention
The invention aims to at least solve the problems of complex structure and low integration level of a two-component attitude and orbit control power system. The purpose is realized by the following technical scheme:
the invention provides a two-component attitude and orbit control power device in a first aspect, which comprises:
the propellant injection device comprises a main body, two propellant inlets are arranged on a first side of the main body at intervals, a plurality of flow channels for the propellant to circulate are arranged in the main body, two bosses extend out of a second side of the main body opposite to the first side, and an included angle is formed between the two bosses;
two thrust chambers respectively mounted on the two bosses, each thrust chamber being configured to be capable of simultaneous communication with the two propellant inlets;
the four electromagnetic valves are installed on a third side and a fourth side of the main body in a pairwise mode, the third side and the fourth side are arranged oppositely and are located between the first side and the second side, and each electromagnetic valve is communicated with one propellant inlet and one thrust chamber respectively so as to control the propellant to flow from the propellant inlet to the thrust chamber.
According to the bipropellant attitude and orbit control power device provided by the embodiment of the invention, the propellant inlet is arranged on the main body, the plurality of flow channels are arranged in the main body, the two thrust chambers and the four electromagnetic valves are all arranged on the main body, so that the propellant inlet, the electromagnetic valves and the thrust chambers are respectively corresponding, under the control of the electromagnetic valves, a propellant can flow into the corresponding thrust chambers from the propellant inlet through the set flow channels to be combusted to generate thrust, a propellant pipeline is not required to be additionally arranged, the structure is simplified, the integration level is improved, and the two thrust chambers are arranged on the two bosses with a certain included angle, so that the two thrust chambers can respectively generate thrust in different directions.
In addition, in some embodiments of the present invention, an included angle between two of the bosses is set to 90 °, and an included angle between mounting surfaces of the two bosses for mounting the thrust chamber is set to 90 °.
In some embodiments of the invention, the two propellant inlets are provided as an oxidizer inlet and a fuel inlet, respectively.
In some embodiments of the present invention, the plurality of flow passages includes four first flow passages, each of the propellant inlets communicates with two of the first flow passages, and the two first flow passages extend toward and communicate with two solenoid valves located on the same side.
In some embodiments of the present invention, the main body is provided with a solenoid valve mounting hole for mounting and communicating the solenoid valve, and the first flow passages correspond to the solenoid valve mounting hole one to one and are communicated through a second flow passage.
In some embodiments of the present invention, each of the bosses is provided with two propellant outlets communicated with the thrust chamber, and the propellant outlets correspond to the solenoid valve mounting holes one by one and are communicated with a third flow passage and a fourth flow passage.
In some embodiments of the invention, a line between two propellant inlets, a line between two propellant outlets on the same boss, and an axis of the solenoid valve mounting hole are parallel.
In some embodiments of the invention, a hollowed-out portion is provided between the two propellant inlets.
In a second aspect, the invention provides an aircraft, which includes an aircraft body and a two-component attitude and orbit control power device according to any of the above embodiments, and the two-component attitude and orbit control power device is mounted on the aircraft body.
The aircraft provided by the embodiment of the invention has the same advantages as the two-component attitude and orbit control power device provided by any one of the embodiments, has a simple and reliable structure and high integration level, and can adjust the attitude and the orbit of the aircraft by using one or more two-component attitude and orbit control power devices to meet attitude control adjustment requirements and orbit change requirements of the aircraft such as pitching, yawing, rolling and the like.
In addition, in some embodiments of the present invention, the number of the two-component attitude and orbit control power devices is four, and the four two-component attitude and orbit control power devices are uniformly arranged at intervals along the circumferential direction of the aircraft body to control the aircraft to perform a setting action and/or enter a setting orbit and/or adjust a posture.
Drawings
Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. Also, like parts are designated by like reference numerals throughout the drawings.
In the drawings:
FIG. 1 is a schematic structural diagram of a two-component attitude and orbit control power device;
FIG. 2 is a first schematic structural diagram of a main body of a two-component attitude and orbit control power device;
FIG. 3 is a second schematic structural diagram of a main body of a two-component attitude and orbit control power device;
FIG. 4 is a schematic cross-sectional view of a body including a propellant inlet;
FIG. 5 is a schematic cross-sectional view of the body including a set of solenoid valve mounting holes;
FIG. 6 is a schematic cross-sectional view of the main body including a set of solenoid valve mounting holes and corresponding propellant outlets;
FIG. 7 is a schematic cross-sectional view of the body including another set of solenoid valve mounting holes;
FIG. 8 is a schematic cross-sectional view of the main body including another set of solenoid valve mounting holes and corresponding propellant outlets;
FIG. 9 is a schematic front view of an aircraft;
fig. 10 is a schematic plan view of the aircraft of fig. 9.
The reference symbols in the drawings denote the following:
1000. an aircraft; 1001. an aircraft body; 100. a two-component attitude and orbit control power device;
10. a main body; 101. a propellant inlet; 1011. an oxidant inlet; 1012. a fuel inlet;
11. a first flow passage; 111. a first oxidant flow passage; 112. a first fuel flow passage;
12. a second flow passage; 121. a second oxidant flow passage; 122. a second fuel flow passage;
13. a third flow path; 131. a third oxidant flow channel; 132. a third fuel flow passage;
14. a fourth flow path; 141. a fourth oxidant flow channel; 142. a fourth fuel flow passage;
15. a boss; 151. a mounting surface; 16. a solenoid valve mounting hole; 17. a propellant outlet; 171. an oxidant outlet; 172. a fuel outlet; 18. a hollow-out section;
20. a thrust chamber; 21. a first thrust chamber; 22. a second thrust chamber; 23. a third thrust chamber; 24. a fourth thrust chamber; 25. a fifth thrust chamber; 26. a sixth thrust chamber; 27. a seventh thrust chamber; 28. an eighth thrust chamber; 30. an electromagnetic valve.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.
It is to be understood that the terminology used herein is for the purpose of describing particular example embodiments only, and is not intended to be limiting. As used herein, the singular forms "a", "an" and "the" may be intended to include the plural forms as well, unless the context clearly indicates otherwise. The terms "comprises," "comprising," "including," and "having" are inclusive and therefore specify the presence of stated features, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, steps, operations, elements, components, and/or groups thereof.
Although the terms first, second, third, etc. may be used herein to describe various elements, components, regions, layers and/or sections, these elements, components, regions, layers and/or sections should not be limited by these terms. These terms may be only used to distinguish one element, component, region, layer or section from another region, layer or section. Terms such as "first," "second," and other numerical terms when used herein do not imply a sequence or order unless clearly indicated by the context. Thus, a first element, component, region, layer or section discussed below could be termed a second element, component, region, layer or section without departing from the teachings of the example embodiments.
For convenience of description, spatially relative terms, such as "inner", "outer", "lower", "below", "upper", "above", and the like, may be used herein to describe one element or feature's relationship to another element or feature as illustrated in the figures. This spatially relative term is intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "below" or "beneath" other elements or features would then be oriented "above" or "over" the other elements or features. Thus, the example term "below … …" may include both an up and down orientation.
As shown in fig. 1 to 3, an embodiment of the invention provides a two-component attitude and orbit control power device 100, where the two-component attitude and orbit control power device 100 includes a main body 10, two thrust chambers 20, and four solenoid valves 30, a first side of the main body 10 is provided with two propellant inlets 101 at intervals, the main body 10 is provided with a plurality of flow channels for propellant to flow through, a second side of the main body 10 opposite to the first side is provided with two bosses 15 in an extending manner, and an included angle is formed between the two bosses 15; two thrust chambers 20 are respectively mounted on the two bosses 15, each thrust chamber 20 being arranged so as to be able to communicate simultaneously with the two propellant inlets 101; the four solenoid valves 30 are installed two by two on the third side and the fourth side of the main body 10, the third side and the fourth side are oppositely arranged and are all located between the first side and the second side, and each solenoid valve 30 is respectively communicated with one propellant inlet 101 and one thrust chamber 20 so as to control the propellant to flow from the propellant inlet 101 to the thrust chamber 20.
The bipropellant attitude and orbit control power device 100 provided by the embodiment of the invention has the advantages that the propellant inlet 101 is arranged on the main body 10, the plurality of flow channels are arranged in the main body 10, the two thrust chambers 20 and the four electromagnetic valves 30 are all arranged on the main body 10, so that the propellant inlet 101, the electromagnetic valves 30 and the thrust chambers 20 are respectively corresponding, under the control of the electromagnetic valves 30, a propellant can flow into the corresponding thrust chambers 20 from the propellant inlet 101 through the set flow channels to be combusted to generate thrust, propellant pipelines are not required to be additionally arranged, the structure is simplified, the integration level is improved, the two thrust chambers 20 can respectively generate thrust in different directions by arranging the two thrust chambers 20 on the two bosses 15 with certain included angles, and the thrust can be increased and the flight direction can be changed accordingly, so that the bipropellant attitude and orbit control power device 100 provided by the embodiment of the invention is simple and reliable in structure and high in integration level, is convenient for adjusting the attitude and orbit of the aircraft 1000 when being applied to the aircraft, and the problems that the conventional bipropellant attitude and orbit control power system is complex in structure and low in integration level are solved.
As shown in fig. 1, 2 and 3, the main body 10 of the present embodiment is a polyhedron with an irregular shape, wherein the first side and the second side are opposite sides, the first side of the main body 10 is provided with a plane, the two propellant inlets 101 have the same structure and are both recessed inwards from the plane, that is, a blind hole is formed on the main body 10, the axes of the propellant inlets 101 can be perpendicular to the plane, and the two propellant inlets 101 are separated from each other by a certain distance. As shown in fig. 2 and 3, in some embodiments of the present invention, two propellant inlets 101 are provided as an oxidant inlet 1011 and a fuel inlet 1012, respectively, the oxidant inlet 1011 is used for flowing in an oxidant, and the oxidant may be selected from green dinitrogen tetroxide; the fuel inlet 1012 is used for supplying fuel, which may be monomethylhydrazine, and the specific types of the oxidant and the fuel are not limited in this embodiment and may be selected according to actual needs.
On the basis of the above embodiment, a plurality of flow passages are provided in the main body 10, wherein a part of the flow passages communicate with the oxidant inlet 1011 for flowing the oxidant into each thrust chamber 20, and the remaining part of the flow passages communicate with the fuel inlet 1012 for flowing the fuel into each thrust chamber 20, and the flow passages will be described below with reference to the specific structure of the main body 10 and the thrust chambers 20.
With reference to fig. 2 and fig. 3, two bosses 15 are disposed on the second side of the main body 10, a first included angle is formed between the two bosses 15, the first included angle is in a range of 30 ° to 180 °, and may be set to 60 °, 90 ° or 120 °, which is not limited in this embodiment, and may be set according to an actual situation. In the present embodiment, two bosses 15 are disposed at an angle to each other, so that two thrust chambers 20 installed on the bosses 15 are angled to each other, thereby generating thrust in different directions to facilitate changing the track or adjusting the posture. As shown in fig. 2, the two bosses 15 may have the same structure, and the bosses 15 are provided with mounting surfaces 151 for mounting the thrust chamber 20, and a second included angle is formed between the two mounting surfaces 151, which is complementary to the first included angle, and is exemplarily set to 90 °.
In addition to the above-described embodiment, as shown in fig. 1, two thrust chambers 20 are respectively mounted on the mounting surfaces 151 of the two bosses 15, and each thrust chamber 20 can be simultaneously communicated with the two propellant inlets 101, that is, simultaneously communicated with the oxidant inlet 1011 and the fuel inlet 1012, in this connection, the two-component attitude and orbit control power device 100 includes four solenoid valves 30, as shown in fig. 1, four solenoid valves 30 are mounted on the main body 10, and two solenoid valves 30 are mounted on a third side of the main body 10, and two other solenoid valves 30 are mounted on a fourth side of the main body 10, it should be noted that, referring to fig. 2 and 3, the third side is disposed opposite to the fourth side and is located between the first side and the second side.
Taking two thrust chambers 20 as an example of a first thrust chamber 21 and a second thrust chamber 22, respectively, according to the above-described embodiment, each of the electromagnetic valves 30 communicates with one of the propellant inlets 101 and one of the thrust chambers 20, respectively, to control the flow of propellant from the propellant inlet 101 to the thrust chamber 20, that is, the four electromagnetic valves 30 are used to control the flow of oxidizer between the oxidizer inlet 1011 and the first thrust chamber 21, the flow of oxidizer between the oxidizer inlet 1011 and the second thrust chamber 22, the flow of fuel between the fuel inlet 1012 and the first thrust chamber 21, and the flow of fuel between the fuel inlet 1012 and the second thrust chamber 22, respectively. Therefore, the two-component attitude and orbit control power device 100 can control the circulation of the oxidant and the fuel inside the main body 10 by opening and closing different electromagnetic valves 30, thereby controlling one or two thrust chambers 20 to generate thrust according to actual requirements.
Further, in some embodiments of the present invention, the main body 10 is configured as an integrally formed structure, the propellant inlets 101 and the bosses 15 on the main body 10 and the flow passages in the main body 10 can be formed by 3D printing or integrally casting, and further, as shown in fig. 3, a hollow portion 18 is further disposed between two propellant inlets 101, in this embodiment, the hollow portion 18 serves as a weight reduction device, which can reduce the mass of the main body 10, and make the whole bipropellant attitude and orbit control power device 100 lightweight.
Referring to fig. 4, in some embodiments of the present invention, the plurality of flow channels in the main body 10 include four first flow channels 11, each of the propellant inlets 101 is respectively communicated with two first flow channels 11, and the two first flow channels 11 respectively extend toward the two solenoid valves 30 located at the same side and are communicated with the solenoid valves 30, it can be understood that, as shown in fig. 1 and 4, two first oxidant flow channels 111 are respectively communicated with two sides of the oxidant inlet 1011, and the two first oxidant flow channels 111 are communicated with the corresponding two solenoid valves 30; two sides of the fuel inlet 1012 are communicated with the two first fuel flow passages 112, respectively, and the two first fuel flow passages 112 are communicated with the corresponding two electromagnetic valves 30.
Further, as shown in fig. 2 and 3, in some embodiments of the present invention, four solenoid valve mounting holes 16 are provided on the main body 10, the four solenoid valve mounting holes 16 may have the same structure, and the solenoid valve mounting holes 16 are used for mounting the solenoid valve 30 and communicating with the solenoid valve 30, as shown in fig. 5 and 7, the solenoid valve mounting holes 16 are provided as blind holes opened on the side wall of the main body 10, each solenoid valve mounting hole 16 corresponds to one first flow channel 11 and communicates with the first flow channel 11 through the second flow channel 12, and it can be understood that the two solenoid valves 30 on the side close to the oxidant inlet 1011 are respectively used for controlling the oxidant in the two first oxidant flow channels 111 and the corresponding two second oxidant flow channels 121 to flow to the two thrust chambers 20; the two electromagnetic valves 30 on the side close to the fuel inlet 1012 are used to control the flow of fuel in the two first fuel flow passages 112 and the corresponding two second fuel flow passages 122 to the two thrust chambers 20, respectively.
In some embodiments of the invention, as shown in fig. 2, each boss 15 of the body 10 is provided with two propellant outlets 17, and when the thrust chamber 20 is mounted on the boss 15, the two propellant outlets 17 are both in communication with the thrust chamber 20, and the thrust chamber 20 includes an oxidizer port, a fuel port, an injector, a combustion chamber, and a large nozzle, and it is understood that the oxidizer port is in aligned communication with the oxidizer outlet 171, and the fuel port is in aligned communication with the fuel outlet 172, so that oxidizer and fuel can simultaneously flow into the thrust chamber 20, and the oxidizer and fuel enter the thrust chamber 20 through the injector to undergo a violent chemical reaction to generate high-temperature and high-pressure gas, and the gas is ejected from the large nozzle to generate thrust.
On the basis of the above embodiment, as shown in fig. 6 and 8, the plurality of flow passages in the main body 10 further include a third flow passage 13 and a fourth flow passage 14 between the solenoid valve mounting hole 16 and the propellant outlet 17, in this embodiment, the propellant outlets 17 correspond to the solenoid valve mounting holes 16 one to one, and the two are communicated with each other through the third flow passage 13 and the fourth flow passage 14, that is, the solenoid valve mounting hole 16, the third flow passage 13, the fourth flow passage 14 and the propellant outlet 17 are communicated in sequence.
As will be appreciated, the two solenoid valves 30 on the side close to the oxidizer inlet 1011 are respectively in communication with the two propellant outlets 17 (oxidizer outlets 171) via a third oxidizer flow channel 131 and a fourth oxidizer flow channel 141, so as to allow the oxidizer to flow into the corresponding thrust chambers 20; the two solenoid valves 30 on the side close to the fuel inlet 1012 communicate with the two propellant outlets 17 (fuel outlets 172) through one third fuel flow passage 132 and one fourth fuel flow passage 142, respectively, to flow the fuel into the corresponding thrust chambers 20. Therefore, the two-component attitude and orbit control power device 100 can control the circulation of the oxidant and the fuel in the main body 10 by opening and closing different electromagnetic valves 30, thereby controlling one or two thrust chambers 20 to generate thrust according to actual requirements.
Further, as shown in fig. 2 and 3, in some embodiments of the present invention, the connecting line between two propellant inlets 101 and the connecting line between two propellant outlets 17 on the same boss 15 are parallel to the axis of each solenoid valve mounting hole 16, which not only makes the structure of the main body 10 reasonably compact, but also facilitates the circulation of propellant inside the main body 10 and the rapid flow of propellant into the thrust chamber 20, and facilitates the solenoid valve 30 to control the on/off of propellant.
In summary, referring to fig. 1 to 8, during the operation of the two-component attitude and orbit control power device 100, the oxidant enters the interior of the main body 10 from the oxidant inlet 1011 and flows towards two sides of the two thrust chambers 20, respectively, and the oxidant flows into the thrust chambers 20 through the oxidant outlet 171 after flowing through the first oxidant flow channel 111, the second oxidant flow channel 121, the electromagnetic valve 30, the third oxidant flow channel 131 and the fourth oxidant flow channel 141, which is described by taking one side as an example; meanwhile, fuel enters the inside of the main body 10 from the fuel inlet 1012 and flows towards two sides of the two thrust chambers 20, and taking one of the two sides as an example, after the fuel flows through the first fuel flow channel 112, the second fuel flow channel 122, the electromagnetic valve 30, the third fuel flow channel 132 and the fourth fuel flow channel 142, the fuel flows into the thrust chambers 20 through the fuel outlet 172, and the oxidant and the fuel are mixed in the thrust chambers 20 and then are combusted to generate high-temperature and high-pressure gas, thereby generating thrust.
As shown in fig. 9 and 10, an embodiment of the second aspect of the present invention provides an aircraft 1000, where the aircraft 1000 includes an aircraft body 1001 and a two-component attitude and orbit control power device 100 according to any of the above embodiments, and the two-component attitude and orbit control power device 100 is mounted on the aircraft body 1001. The two-component attitude and orbit control power device 100 in this embodiment may be configured as one or more, and may be specifically configured according to the actual needs of the aircraft 1000, which is not specifically limited in this embodiment.
The aircraft 1000 provided by the embodiment of the invention has the same advantages as the two-component attitude and orbit control power device 100 provided by any one of the embodiments, the aircraft 1000 provided by the embodiment of the invention has a simple and reliable structure and high integration level, one or more two-component attitude and orbit control power devices 100 can be used for adjusting the attitude and the orbit of the aircraft 1000, the attitude control adjustment requirements and the orbit change requirements of the aircraft 1000 such as pitching, yawing and rolling are met, and a plurality of two-component attitude and orbit control power devices 100 can generate larger thrust.
Further, in some embodiments of the present invention, the number of the two-component attitude and orbit control power devices 100 is four, as shown in fig. 9 and 10, the four two-component attitude and orbit control power devices 100 are uniformly arranged at intervals along the circumference of the aircraft body 1001, and the aircraft 1000 can be controlled to perform a setting action, and/or the aircraft 1000 can be controlled to enter a setting orbit, and/or the aircraft 1000 can be controlled to adjust the attitude by opening one or more thrust chambers 20 in one or more of the two-component attitude and orbit control power devices 100.
Illustratively, the four two-component attitude and orbit control power device 100 includes eight thrust chambers 20, as shown in fig. 9 and 10, the eight thrust chambers 20 are respectively a first thrust chamber 21, a second thrust chamber 22, a third thrust chamber 23, a fourth thrust chamber 24, a fifth thrust chamber 25, a sixth thrust chamber 26, a seventh thrust chamber 27 and an eighth thrust chamber 28, and during the flight of the aircraft 1000, as shown in fig. 9, the aircraft 1000 can be made to roll clockwise around the central axis by controlling the first thrust chamber 21 and the fourth thrust chamber 24 to work simultaneously; by controlling the second thrust chamber 22 and the third thrust chamber 23 to operate simultaneously, the aircraft 1000 may be rolled counterclockwise about the central axis; by controlling the first thrust chamber 21 and the third thrust chamber 23, or the second thrust chamber 22 and the fourth thrust chamber 24, or the fifth thrust chamber 25 and the eighth thrust chamber 28, or the sixth thrust chamber 26 and the seventh thrust chamber 27 to work simultaneously, the pitch or yaw attitude of the aircraft 1000 can be adjusted; by controlling the fifth and seventh thrust chambers 25 and 27, and the sixth and eighth thrust chambers 26 and 28 to operate simultaneously, the flight trajectory of the aircraft 1000 can be made high or low. Therefore, the aircraft 1000 provided by the embodiment can also meet the requirements of various attitude adjustment and rail control on the basis of simple structure and high integration level.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are also included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (6)
1. A two-component attitude and orbit control power device is characterized by comprising:
the propellant injection device comprises a main body, two propellant inlets are arranged on a first side of the main body at intervals, a plurality of flow channels for the propellant to circulate are arranged in the main body, two bosses extend out of a second side of the main body opposite to the first side, and an included angle is formed between the two bosses;
two thrust chambers respectively mounted on the two bosses, each thrust chamber being configured to be capable of simultaneous communication with the two propellant inlets;
four electromagnetic valves, wherein the four electromagnetic valves are installed on a third side and a fourth side of the main body in pairs, the third side and the fourth side are arranged oppositely and are positioned between the first side and the second side, and each electromagnetic valve is respectively communicated with one propellant inlet and one thrust chamber so as to control the propellant to flow from the propellant inlet to the thrust chamber;
the plurality of flow channels comprise four first flow channels, each propellant inlet is communicated with two first flow channels, the two first flow channels extend towards two electromagnetic valves positioned on the same side and are communicated with the electromagnetic valves, the main body is provided with electromagnetic valve mounting holes used for mounting and communicating the electromagnetic valves, the first flow channels are in one-to-one correspondence with the electromagnetic valve mounting holes and are communicated through second flow channels, each boss is provided with two propellant outlets communicated with the thrust chamber, the propellant outlets are in one-to-one correspondence with the electromagnetic valve mounting holes and are communicated through third flow channels and fourth flow channels, and connecting lines between the propellant inlets and connecting lines between the propellant outlets on the same boss are parallel to the axis of the electromagnetic valve mounting holes.
2. The two-component attitude and orbit control power device according to claim 1, wherein the included angle between the two bosses is set to 90 °, and the included angle between the mounting surfaces of the two bosses for mounting the thrust chamber is set to 90 °.
3. The bipropellant attitude control power device of claim 1, wherein the two propellant inlets are configured as an oxidizer inlet and a fuel inlet, respectively.
4. The bipropellant attitude and orbit control power device of claim 1, wherein a hollowed out portion is provided between the two propellant inlets.
5. An aircraft, characterized in that it comprises an aircraft body and at least one two-component attitude and orbit control power plant according to any one of claims 1 to 4, mounted on said aircraft body.
6. The aircraft of claim 5, wherein the number of the two-component attitude and orbit control power devices is four, and the four two-component attitude and orbit control power devices are uniformly arranged at intervals along the circumferential direction of the aircraft body so as to control the aircraft to perform a set action and/or enter a set orbit and/or adjust the posture.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210809721.1A CN114889850B (en) | 2022-07-11 | 2022-07-11 | Double-component attitude and orbit control power device and aircraft with same |
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| CN202210809721.1A CN114889850B (en) | 2022-07-11 | 2022-07-11 | Double-component attitude and orbit control power device and aircraft with same |
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| CN114889850A CN114889850A (en) | 2022-08-12 |
| CN114889850B true CN114889850B (en) | 2022-10-14 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US8104264B2 (en) * | 2008-08-11 | 2012-01-31 | Honeywell International Inc. | Low minimum impulse bit propellant gas thruster |
| CN106516165B (en) * | 2016-10-27 | 2018-10-09 | 北京控制工程研究所 | A method of improving double elements attitude control thruster Pulse Width Control precision |
| CN111237088A (en) * | 2020-03-30 | 2020-06-05 | 北京宇航推进科技有限公司 | Double-component five-machine combined power system |
| CN113107710B (en) * | 2021-05-10 | 2023-10-20 | 苏州旗磐科技有限公司 | Low-thrust double-component attitude control engine |
| CN113431707A (en) * | 2021-07-27 | 2021-09-24 | 北京宇航推进科技有限公司 | Single-component attitude control engine module and combination thereof |
| CN114291299B (en) * | 2021-12-21 | 2023-08-11 | 上海空间推进研究所 | Solid-liquid dual-mode attitude and orbit control power system and control method thereof |
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