CN103662093A - Pore plate assembly used for double-component thruster - Google Patents
Pore plate assembly used for double-component thruster Download PDFInfo
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- CN103662093A CN103662093A CN201310713457.2A CN201310713457A CN103662093A CN 103662093 A CN103662093 A CN 103662093A CN 201310713457 A CN201310713457 A CN 201310713457A CN 103662093 A CN103662093 A CN 103662093A
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- orifice plate
- plate assembly
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- pore plate
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Abstract
The invention relates to a pore plate assembly used for a double-component thruster, in particular to a throttle control pore plate assembly used for the double-component thruster and belongs to the technical field of spacecraft space propelling. The pore plate assembly is suitable for adjusting flow resistance in a propellant channel of the spacecraft attitude control double-component thruster. A sealing gasket is deformed under pressure to guarantee sealing through a micro cone end face frustum, a pressure bearing gasket exerts certain pressure on a pore plate through elastic deformation, the position of the pore plate is fixed, and propellant is prevented from flowing through a cavity of the outer circle of the pressure bearing gasket to a certain degree, so that the performance of the thruster is affected.
Description
Technical field
The present invention relates to a kind of orifice plate assembly for double elements thruster, be particularly related to a kind of throttling control punch board component for double elements thruster, be applicable to Spacecraft Attitude Control double elements thruster propellant channel flow resistance and regulate, belong to spacecraft spacemarching field.
Background technology
Double elements thruster is the main antagonistic force execution unit of Spacecraft Attitude Control, by ejection high temperature, high-speed fuel gas, produces thrust, carries out Spacecraft Attitude Control and track and shifts.For meeting the requirement of propulsion subsystem to thruster thrust and mixture ratio control accuracy, need to accurately control propellant channel flow resistance, common employing is installed suitable throttle plate additional and is regulated.
At present, China's double elements thruster throttle plate is installed on thruster entrance, and because double elements thruster propellant flow rate is very little, orifice plate passage aperture is also very little, has the hidden danger that causes Actuator failure because of upstream superfluity obstruction orifice plate.
For head it off, the present invention proposes a kind of new orifice structure for double elements thruster, this structure can be installed on electromagnetic valve and injector interface, is not directly connected with propellant pipeline, thereby has avoided stopping up because of pipeline superfluity the problem that orifice plate passage causes Actuator failure.
Summary of the invention
The object of the invention is in order to propose a kind of orifice plate assembly for double elements thruster.
The object of the invention is to be achieved through the following technical solutions.
A kind of orifice plate assembly for double elements thruster of the present invention, external equipment is electromagnetic valve and injector, and solenoid valve interface structure adopts cylinder-shaped joint, and there is through hole at the center of cylinder-shaped joint, and injector interface structure adopts inner conical cavity form;
This orifice plate assembly comprises packing seal, pressure-bearing pad and orifice plate;
Packing seal is directly installed on electromagnetic valve and injector interface, and pressure-bearing pad is positioned at electromagnetic valve cylinder-shaped joint downstream, and orifice plate is positioned at pressure-bearing pad downstream, and presses close to injector conical cavity internal face.
Described packing seal is annulus, and its end face has tapered protrusion, and its material is titanium;
The material of described pressure-bearing pad is plastics, is preferably perfluoroethylene-propylene (copolymer), has elasticity, for compressing orifice plate; Prevent that orifice plate from affecting the flow of thruster pressure drop performance because shaking in vibration processes, and stop propellant by flowing in the sealed cavity outside orifice plate in orifice plate passage, have influence on the small-pulse effect performance of thruster;
Described orifice plate is circular table structure, and central punch reaches the object of accurate control propellant flow rate by changing the diameter of centre hole; The material of orifice plate is titanium.
Solenoid valve interface structure adopts cylindrical, the structure of central punch, and injector interface adopts inner conical cavity structure.
Wherein packing seal is directly installed on electromagnetic valve and injector interface, by distortion under pressure, guarantees sealing, and pressure-bearing pad is positioned at electromagnetic valve cylinder-shaped joint downstream, and orifice plate is positioned at pressure-bearing pad downstream, and presses close to injector conical cavity wall.
Packing seal is out of shape and is guaranteed sealing by the micro-frustum of micro-cone end face under pressure, pressure-bearing pad gives orifice plate certain pressure by elastic deformation, fixed orifice Board position, and played certain cavity of avoiding propellant runner pressure-bearing pad outer shroud, thus affect the performance of thruster.
Accompanying drawing explanation
Fig. 1 is the structural representation of orifice plate assembly of the present invention;
Fig. 2 is the structural representation of packing seal of the present invention;
Fig. 3 is the structural representation of pressure-bearing pad of the present invention;
Fig. 4 is the structural representation of orifice plate of the present invention.
The specific embodiment
Below in conjunction with drawings and Examples, the invention will be further described.
Embodiment
As shown in Figure 1, a kind of orifice plate assembly for double elements thruster, this orifice plate assembly comprises packing seal 1, pressure-bearing pad 2 and orifice plate 3;
As shown in Figure 2, described packing seal 1 is annulus, and its end face has tapered protrusion, and its material is titanium;
As shown in Figure 3, the material of described pressure-bearing pad 2 is plastics, is preferably perfluoroethylene-propylene (copolymer), has elasticity, for compressing orifice plate; Prevent that orifice plate from affecting the flow of thruster pressure drop performance because shaking in vibration processes, and stop propellant by flowing in the sealed cavity outside orifice plate in orifice plate passage, have influence on the small-pulse effect performance of thruster;
As shown in Figure 4, described orifice plate 3 is circular table structure, and central punch reaches the object of accurate control propellant flow rate by changing the diameter of centre hole; The material of orifice plate 3 is titanium.
As shown in Figure 1, orifice plate assembly of the present invention is installed on the interface of double elements thruster electromagnetic valve and injector, and solenoid valve interface structure adopts cylindrical, the structure of central punch, and injector interface adopts inner conical cavity structure.
Wherein packing seal is directly installed on electromagnetic valve and injector interface, by distortion under pressure, guarantees sealing, and pressure-bearing pad 2 is positioned at electromagnetic valve cylinder-shaped joint downstream, and orifice plate is positioned at pressure-bearing pad downstream, and presses close to injector conical cavity wall.
Packing seal is out of shape and is guaranteed sealing by the micro-frustum of micro-cone end face under pressure, pressure-bearing pad gives orifice plate certain pressure by elastic deformation, fixed orifice Board position, and played certain cavity of avoiding propellant runner pressure-bearing pad outer shroud, thus affect the performance of thruster.
Claims (5)
1. the orifice plate assembly for double elements thruster, external equipment is electromagnetic valve (4) and injector (5), electromagnetic valve (4) interface structure adopts cylinder-shaped joint, and there is through hole at the center of cylinder-shaped joint, and injector (5) interface structure adopts inner conical cavity form;
It is characterized in that: this orifice plate assembly comprises packing seal (1), pressure-bearing pad (2) and orifice plate (3);
Packing seal (1) is directly installed on electromagnetic valve (4) and injector (5) interface, and pressure-bearing pad (2) is positioned at electromagnetic valve (4) cylinder-shaped joint downstream, and orifice plate (3) is positioned at pressure-bearing pad (2) downstream, and presses close to injector (5) conical cavity internal face.
2. a kind of orifice plate assembly for double elements thruster according to claim 1, is characterized in that: packing seal (1) is annulus, and its end face has tapered protrusion, and its material is titanium.
3. a kind of orifice plate assembly for double elements thruster according to claim 1, is characterized in that: the material of pressure-bearing pad (2) is plastics.
4. a kind of orifice plate assembly for double elements thruster according to claim 3, is characterized in that: the material of pressure-bearing pad (2) is perfluoroethylene-propylene (copolymer).
5. a kind of orifice plate assembly for double elements thruster according to claim 1, is characterized in that: orifice plate (3) is circular table structure, central punch, and the material of orifice plate (3) is titanium.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310713457.2A CN103662093B (en) | 2013-12-20 | 2013-12-20 | A kind of orifice plate assembly for double elements thruster |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310713457.2A CN103662093B (en) | 2013-12-20 | 2013-12-20 | A kind of orifice plate assembly for double elements thruster |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103662093A true CN103662093A (en) | 2014-03-26 |
| CN103662093B CN103662093B (en) | 2015-08-19 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201310713457.2A Active CN103662093B (en) | 2013-12-20 | 2013-12-20 | A kind of orifice plate assembly for double elements thruster |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114030655A (en) * | 2021-11-25 | 2022-02-11 | 贵州航天朝阳科技有限责任公司 | Light modularized liquid attitude and orbit control engine |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5117627A (en) * | 1989-10-27 | 1992-06-02 | Centre National D'etudes Spatiales | Method and device to protect a propulsive catalytic bed from degrading passed through by a fuel |
| RU2443895C1 (en) * | 2010-09-02 | 2012-02-27 | Государственное образовательное учреждение высшего профессионального образования "Уфимский государственный авиационный технический университет" | Adjustable solid-propellant rocket engine |
| CN102767631A (en) * | 2011-05-05 | 2012-11-07 | 上海威含德石油机械设备有限公司 | Orifice-plate type adjustable throttle valve and manufacturing method thereof |
| CN103075270A (en) * | 2013-01-15 | 2013-05-01 | 西北工业大学 | High-pressure-intensity external pulse excitation device for T-shaped burner |
| CN103410632A (en) * | 2013-08-09 | 2013-11-27 | 南京理工大学 | Electric conical valve type gas flow regulator for solid rocket ramjets |
-
2013
- 2013-12-20 CN CN201310713457.2A patent/CN103662093B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5117627A (en) * | 1989-10-27 | 1992-06-02 | Centre National D'etudes Spatiales | Method and device to protect a propulsive catalytic bed from degrading passed through by a fuel |
| RU2443895C1 (en) * | 2010-09-02 | 2012-02-27 | Государственное образовательное учреждение высшего профессионального образования "Уфимский государственный авиационный технический университет" | Adjustable solid-propellant rocket engine |
| CN102767631A (en) * | 2011-05-05 | 2012-11-07 | 上海威含德石油机械设备有限公司 | Orifice-plate type adjustable throttle valve and manufacturing method thereof |
| CN103075270A (en) * | 2013-01-15 | 2013-05-01 | 西北工业大学 | High-pressure-intensity external pulse excitation device for T-shaped burner |
| CN103410632A (en) * | 2013-08-09 | 2013-11-27 | 南京理工大学 | Electric conical valve type gas flow regulator for solid rocket ramjets |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114030655A (en) * | 2021-11-25 | 2022-02-11 | 贵州航天朝阳科技有限责任公司 | Light modularized liquid attitude and orbit control engine |
| CN114030655B (en) * | 2021-11-25 | 2023-09-26 | 贵州航天朝阳科技有限责任公司 | Light modularized liquid attitude and orbit control engine |
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| Publication number | Publication date |
|---|---|
| CN103662093B (en) | 2015-08-19 |
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