CN114030655B - Light modularized liquid attitude and orbit control engine - Google Patents
Light modularized liquid attitude and orbit control engine Download PDFInfo
- Publication number
- CN114030655B CN114030655B CN202111415227.9A CN202111415227A CN114030655B CN 114030655 B CN114030655 B CN 114030655B CN 202111415227 A CN202111415227 A CN 202111415227A CN 114030655 B CN114030655 B CN 114030655B
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- electromagnetic valve
- type electromagnetic
- shaft type
- injector
- control engine
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- 239000007788 liquid Substances 0.000 title claims abstract description 21
- 238000002485 combustion reaction Methods 0.000 claims abstract description 29
- 238000007789 sealing Methods 0.000 claims abstract description 29
- 239000003380 propellant Substances 0.000 claims abstract description 18
- 230000005540 biological transmission Effects 0.000 claims description 5
- 210000001503 joint Anatomy 0.000 claims description 4
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 230000004075 alteration Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 230000001627 detrimental effect Effects 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- 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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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Automation & Control Theory (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Radar, Positioning & Navigation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Fuel-Injection Apparatus (AREA)
Abstract
The invention discloses a light modularized liquid attitude and orbit control engine which comprises a shell, a combustion chamber, an injector, a high-temperature resistant sealing gasket, a bearing, a propellant inlet joint, a sealing sphere, a sealing ring and a shaft type electromagnetic valve. According to the invention, through the light modular design of the engine and adopting the shaft type electromagnetic valve and rotary sliding type injector structure, the working mode of function exchange among the engine injectors is realized on the basis of basically not increasing the weight and layout space of a power system, and the redundancy and reliability of the engine module are improved. The invention can even reduce the number of the injectors in the engine module under certain conditions, and reduce the layout space and weight of each engine.
Description
Technical Field
The invention relates to a light modularized liquid attitude and orbit control engine which is mainly used for attitude and orbit control in the fields of aerospace and the like.
Background
The liquid attitude and orbit control engine is mainly used for controlling the attitude and orbit of an aircraft in the field of aerospace. Because the power system belongs to the application product of the upper level, the design process has more severe requirements on the layout space and quality of the liquid attitude and orbit control engine, and the margin for redundancy design is smaller.
The traditional liquid rocket engines all adopt a structure mode that a combustion chamber and an injector are in one-to-one fixed correspondence, when a problem occurs, the engines cannot continue to normally work, and only the rest redundant backup engines can be used for replacing work; if no backup engine is available, the system will fly with a great failure risk.
In another aspect, the redundancy mode of the back-up design greatly increases the weight and cost of the power system for a liquid-operated power system having multiple engines and is detrimental to system miniaturization.
Disclosure of Invention
The invention aims to design a light modularized liquid attitude and orbit control engine, which is suitable for and meets the requirements of a related attitude and orbit control power system on layout space and weight, and improves the design redundancy and the working reliability of the engine.
In order to achieve the above purpose, the present invention adopts the following technical scheme:
a light modularized liquid attitude and orbit control engine comprises a main body,
a shaft solenoid valve having one or more outlet passages thereon;
the driving device is connected with the shaft type electromagnetic valve, and when the driving device acts, the driving device drives the shaft type electromagnetic valve to rotate around the axis of the shaft type electromagnetic valve;
one or more injectors connected at the outlet passage of the solenoid valve and rotating with the solenoid valve when the solenoid valve is rotated;
the combustion chamber, the propellant entry end of combustion chamber distributes on the cylindrical surface taking axis of rotation of shaft type solenoid valve as the central axis, and the nozzle of the injector is located on the cylindrical surface or in the cylindrical surface.
Further, the light modularized liquid attitude and orbit control engine also comprises a shell,
the shell is provided with a through hole penetrating through the upper end face and the lower end face of the shell, and the shaft type electromagnetic valve is arranged in the through hole;
the shell is provided with a connecting hole on the circumferential surface, the connecting hole is intersected with the through hole, the propellant inlet end of the combustion chamber is positioned at the outer side of the connecting hole, and the nozzle of the injector is positioned at the inner side of the connecting hole.
Further, a spherical cavity is arranged in the shell, the spherical cavity is intersected with the through hole and the connecting hole at the same time, and the surface of the spherical cavity is a sealing spherical surface;
the surface of the injector comprises a spherical surface, and the injector is matched with the sealing spherical surface through the spherical surface to form a sealing structure.
Further, a high-temperature-resistant sealing gasket is arranged on the spherical surface of the injector.
Further, the shaft type electromagnetic valve is connected in the through hole of the shell through a bearing.
Further, the number of the bearings is two, and the bearings are respectively arranged in the through holes and close to the upper end face and the lower end face.
Further, the driving device comprises a driving device,
controlling a motor;
and the control motor is connected with the shaft type electromagnetic valve through the transmission gear.
Further, an inlet channel of the shaft type electromagnetic valve is movably connected with the propellant inlet connector, and the inlet channel is dynamically sealed with the propellant inlet connector through a sealing ring.
Further, the shaft type electromagnetic valve is connected with the injector through surface butt joint, and no connecting piece is arranged between the shaft type electromagnetic valve and the injector.
Alternatively, the injector is a mutually-striking, centrifugal, pintle, or shower injector.
Compared with the prior art, the invention realizes the working mode of function exchange among the engine injectors by carrying out light modular design on the engine and adopting the shaft type electromagnetic valve and rotary sliding injector structure on the basis of basically not increasing the weight and layout space of a power system, and improves the redundancy and reliability of the engine module; even the number of injectors in the engine module can be reduced under certain conditions, and the layout space and weight of each engine are reduced.
Drawings
FIGS. 1 and 2 are schematic views of the overall structure of a light modular liquid attitude and orbit control engine;
FIGS. 3 and 4 are schematic views of engine module housing structures;
FIG. 5 is a schematic view of the internal structure and the working principle of a light modular liquid attitude and orbit control engine;
in the figure, 1-combustion chamber; 2-injector; 3-high temperature resistant sealing gasket; 4-sealing sphere; 5-bearing; 6-propellant inlet fitting; 7-a sealing ring; 8-axis electromagnetic valve; 9-a transmission gear; 10-controlling the motor.
Detailed Description
The present invention will be further described with reference to the drawings and the specific embodiments, but it should not be construed that the scope of the subject matter of the present invention is limited to the following embodiments, and various modifications, substitutions and alterations made according to the ordinary skill and familiar means of the art to which this invention pertains are included within the scope of the present invention without departing from the above technical idea of the invention.
As an embodiment of the present invention, as shown in fig. 1 to 5, the light modular liquid attitude and control engine includes a housing, the circumferential surface of which is connected with 4 combustion chambers 1,4 combustion chambers 1 and the like (90 degrees) are distributed on a circumference with the axis of the through hole as the central axis (the plane of the circumference is perpendicular to the axis of the through hole), a shaft type electromagnetic valve 8 is rotatably connected to the through hole penetrating through the upper end face and the lower end face of the housing, the rotation axis of the shaft type electromagnetic valve 8 coincides with the axis of the through hole, at least 2 injectors 2 are connected to the circumferential surface of the shaft type electromagnetic valve 8, the two injectors 2 are distributed on the circumferential plane with the 4 combustion chambers 1 at an included angle of 90 degrees (as shown in fig. 5, the axis of the injectors 2 is coaxial with the axis of the combustion chambers 1), a spherical cavity intersecting with the through hole is formed inside the housing, the surface of the spherical cavity is a sealing spherical surface 4, the injector 2 is located between the sealing spherical surface 4 and the spherical surface 8 when the shaft type electromagnetic valve 8 rotates around the axis itself, the surface of the injector 2 is attached to the sealing spherical surface 4 and rotates with the shaft type electromagnetic valve 8 until the injector 2 rotates with the shaft type electromagnetic valve 8 until the propellant moves to the inlet port of the next combustion chamber 1.
As shown in fig. 5, the light modularized liquid attitude and orbit control engine mainly comprises a shell, a combustion chamber 1, an injector 2, a high-temperature-resistant sealing gasket 3, a bearing 5, a propellant inlet joint 6, a sealing ring 7, a shaft type electromagnetic valve 8 and the like, and adopts modularized design. The whole engine module is connected with an external control motor 10 module through a transmission gear 9 on a shaft type electromagnetic valve 8.
The engine module shell consists of a combustion chamber 1 and a shell with a smooth sealing sphere 4, wherein the number of the combustion chambers 1 can be designed and adjusted according to the system requirements, such as a single combustion chamber 1, a double combustion chamber 1, a triple combustion chamber 1 and a four combustion chamber 1. The number of the injectors 2 and the combustion chambers 1 in the engine module can be in one-to-one correspondence or one-to-many-to-one correspondence according to the working mode of the engine module, for example, four injectors 2 are arranged in four combustion chambers 1, three injectors 2 are arranged in four combustion chambers 1, four injectors 2 are arranged in three combustion chambers 1, and the like.
The outer end face of each injector 2 is matched with the sealing sphere 4 of the engine module shell. The high temperature resistant sealing gasket 3 is adopted to seal between each injector 2 and the sealing sphere 4, so that high temperature fuel gas is prevented from entering the rear of the injector 2 when the engine works. As shown in fig. 5, which is a partially enlarged view i, the refractory seal 3 is located in a spherical surface seal groove on the surface of the injector 2, and is in a one-to-one correspondence in number with the injector 2.
The shaft type electromagnetic valve 8 is an integrated electromagnetic valve, structurally plays a role in transmitting torque of the control motor 10, and functionally plays a role in controlling the on-off of the engine in all directions. The axial electromagnetic valve 8 has a one-to-one correspondence in form and quantity with the propellant outlet channels of each injector 2; in the control relationship, each azimuth control channel is in one-to-one correspondence with the injector 2. The injector 2 and the shaft type electromagnetic valve 8 are in a molded surface butt joint mode on an assembly structure, as shown in a partial enlarged view II in FIG. 5, a screw connection structure of the injector 2 and the shaft type electromagnetic valve 8 is omitted through a butt joint coordination relationship of all the components, the structural weight of an engine is reduced, and the internal layout space of an engine module is optimized. The injector 2 is held in position between the shaft solenoid valve 8 and the sealing sphere 4 by virtue of compression of both.
The shaft type electromagnetic valve 8 and the engine module shell are assembled and positioned by adopting 2 bearings 5, and a transmission gear 9 is designed on the outer side of a channel of the propellant inlet of the shaft type electromagnetic valve 8 and is connected with a control motor 10 module. By means of control commands, the combustion chambers 1 with different orientations or quadrants can be matched with different injectors 2.
The propellant inlet joint 6 is connected with an external supply pipeline and is dynamically sealed with the shaft type electromagnetic valve 8 by adopting a radial sealing ring 7. When the shaft type electromagnetic valve 8 rotates, the propellant inlet joint 6 is kept motionless, and the sealing ring 7 contacted with the propellant in the channel can be effectively cooled by the propellant, so that the friction of the sealing ring 7 is prevented from being damaged.
Before the engine module works, the motor 10 is controlled to drive the shaft type electromagnetic valve 8 to rotate, so that the position relation between the injector 2 and the combustion chamber 1 is adjusted, and the normal work of the engine module is ensured. When the channel or the injector 2 in a certain direction of the shaft type electromagnetic valve 8 cannot work normally, the motor 10 is controlled to drive the shaft type electromagnetic valve 8 to rotate, the matching relation between the injector 2 and the combustion chamber 1 is readjusted, the required thrust direction can be ensured to output thrust normally, and the occurrence of the condition of out-of-flight caused by the failure of the shaft type electromagnetic valve 8 or the injector 2 in a certain direction channel is reduced.
In a two-component or multi-component engine module application, the injector 2 may be a mutually-firing, centrifugal, pintle, or other form of injector; in a single component engine module application, the injector 2 may be a shower or other form of injector.
The above examples are illustrative of the inventive concept and do not limit the final scope of protection, and any embodiments based on the inventive concept should fall within the scope of protection of the invention.
Claims (7)
1. A light modularized liquid attitude and orbit control engine is characterized in that: comprising the steps of (a) a step of,
a shaft-type electromagnetic valve (8), wherein the shaft-type electromagnetic valve (8) is provided with one or more outlet channels; the inlet channel of the shaft type electromagnetic valve (8) is movably connected with the propellant inlet joint (6), and the inlet channel is dynamically sealed with the propellant inlet joint (6) through a sealing ring (7);
the driving device is connected with the shaft type electromagnetic valve (8), and when the driving device acts, the driving device drives the shaft type electromagnetic valve (8) to rotate around the axis of the shaft type electromagnetic valve (8);
one or more injectors (2), wherein the injectors (2) are connected at the outlet channel of the shaft type electromagnetic valve (8), and when the shaft type electromagnetic valve (8) rotates, the injectors (2) rotate together with the shaft type electromagnetic valve (8);
the combustion chamber (1), the said combustion chamber (1) has one or more, the propellant inlet end of the combustion chamber (1) distributes on the cylindrical surface taking axis of rotation of the shaft type electromagnetic valve (8) as central axis, and the nozzle of the injector (2) is located on or in the cylindrical surface;
the electromagnetic valve comprises a shell, a shaft type electromagnetic valve (8) and a control unit, wherein the shell is provided with a through hole penetrating through the upper end surface and the lower end surface of the shell, and the shaft type electromagnetic valve (8) is arranged in the through hole; the circumferential surface of the shell is provided with a connecting hole which is intersected with the through hole, the propellant inlet end of the combustion chamber (1) is positioned at the outer side of the connecting hole, and the nozzle of the injector (2) is positioned at the inner side of the connecting hole; the inside of the shell is also provided with a spherical cavity which is intersected with the through hole and the connecting hole at the same time, and the surface of the spherical cavity is a sealing spherical surface (4); the surface of the injector (2) comprises a spherical surface, and the injector (2) is matched with the sealing spherical surface (4) through the spherical surface to form a sealing structure.
2. The lightweight modular liquid attitude and orbit control engine of claim 1, which is characterized in that: the spherical surface of the injector (2) is provided with a high-temperature-resistant sealing gasket (3).
3. The lightweight modular liquid attitude and orbit control engine of claim 1, which is characterized in that: the shaft type electromagnetic valve (8) is connected in the through hole of the shell through the bearing (5).
4. A lightweight modular liquid attitude and orbit control engine according to claim 3, wherein: the number of the bearings (5) is two, and the bearings are respectively arranged in the through holes and close to the upper end face and the lower end face.
5. The lightweight modular liquid attitude and orbit control engine of claim 1, which is characterized in that: the driving means may comprise a drive mechanism which is configured to drive the drive mechanism,
-controlling the motor (10);
and the control motor (10) is connected with the shaft type electromagnetic valve (8) through the transmission gear (9).
6. The lightweight modular liquid attitude and orbit control engine of claim 1, which is characterized in that: the shaft type electromagnetic valve (8) is connected with the injector (2) through surface butt joint, and no connecting piece is arranged between the shaft type electromagnetic valve (8) and the injector (2).
7. The lightweight modular liquid attitude and orbit control engine of claim 1, which is characterized in that: the injector (2) is a mutually striking, centrifugal, needle-bolt or shower injector.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111415227.9A CN114030655B (en) | 2021-11-25 | 2021-11-25 | Light modularized liquid attitude and orbit control engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111415227.9A CN114030655B (en) | 2021-11-25 | 2021-11-25 | Light modularized liquid attitude and orbit control engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114030655A CN114030655A (en) | 2022-02-11 |
| CN114030655B true CN114030655B (en) | 2023-09-26 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111415227.9A Active CN114030655B (en) | 2021-11-25 | 2021-11-25 | Light modularized liquid attitude and orbit control engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114030655B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001165016A (en) * | 1999-12-13 | 2001-06-19 | Shigeya Nishida | Fuel injection device for direct injection engine |
| US6289669B1 (en) * | 1999-02-25 | 2001-09-18 | LKF Lenkflugkörpersysteme GmbH | Lateral-thrust control arrangement for missiles with solid-fuel hot-gas generator |
| JP2003294398A (en) * | 2002-04-03 | 2003-10-15 | Mitsubishi Electric Corp | Side thruster |
| JP2007085213A (en) * | 2005-09-21 | 2007-04-05 | Ihi Aerospace Co Ltd | Thin rocket motor |
| CN103662093A (en) * | 2013-12-20 | 2014-03-26 | 北京控制工程研究所 | Pore plate assembly used for double-component thruster |
| CN109707537A (en) * | 2018-12-07 | 2019-05-03 | 上海空间推进研究所 | A kind of small-sized rocket motor structure layout |
-
2021
- 2021-11-25 CN CN202111415227.9A patent/CN114030655B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6289669B1 (en) * | 1999-02-25 | 2001-09-18 | LKF Lenkflugkörpersysteme GmbH | Lateral-thrust control arrangement for missiles with solid-fuel hot-gas generator |
| JP2001165016A (en) * | 1999-12-13 | 2001-06-19 | Shigeya Nishida | Fuel injection device for direct injection engine |
| JP2003294398A (en) * | 2002-04-03 | 2003-10-15 | Mitsubishi Electric Corp | Side thruster |
| JP2007085213A (en) * | 2005-09-21 | 2007-04-05 | Ihi Aerospace Co Ltd | Thin rocket motor |
| CN103662093A (en) * | 2013-12-20 | 2014-03-26 | 北京控制工程研究所 | Pore plate assembly used for double-component thruster |
| CN109707537A (en) * | 2018-12-07 | 2019-05-03 | 上海空间推进研究所 | A kind of small-sized rocket motor structure layout |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114030655A (en) | 2022-02-11 |
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