CN105736754A - Sealed gas reversing device - Google Patents
Sealed gas reversing device Download PDFInfo
- Publication number
- CN105736754A CN105736754A CN201410748304.6A CN201410748304A CN105736754A CN 105736754 A CN105736754 A CN 105736754A CN 201410748304 A CN201410748304 A CN 201410748304A CN 105736754 A CN105736754 A CN 105736754A
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- Prior art keywords
- gas
- combustion gas
- lining
- rudderpost
- sealed
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Abstract
The invention provides a sealed gas reversing device which comprises a gas reversing valve, a lining, a rudder spindle, a gas inlet guide pipe and gas outlet jet pipes. Three gas holes are formed in the gas reversing valve. One gas hole communicates with a gas generator through the gas inlet guide pipe. The other two gas holes communicate with the left gas outlet jet pipe and the right gas outlet jet pipe correspondingly. The lining is located in the middle of the gas reversing valve and connected with the rudder spindle. By the adoption of the sealed gas reversing device, gas flow is made to be jetted on the left side and on the right side alternately, so that lateral thrust is generated, and posture control over a guided missile in the initial stage is achieved. In the initial stage of launch of the guided missile, the rapidity for responding to control signals, the close-range assault capacity of the guided missile and the operation convenience of a launcher are improved.
Description
Technical field
The present invention relates to a kind of gas reversing arrangement, be specifically related to a kind of sealed combustion gas reversing arrangement being applied to control missile flight attitude.
Background technology
The flight attitude of guided missile relies on rudder face to control, and rudder face controls power and affected by airflow acting force, and the size of object active force is changed by air-flow with the change of flight speed.In the MISSILE LAUNCHING starting stage owing to flight speed is low, rudder face control efficiency is low, it is difficult to control flight attitude well, can make guided missile that low coverage targeting rate is greatly lowered.
For improving the operation convenience of rapidity, the close attack ability of guided missile and shooter that control signal respond by the starting stage, after guided missile goes out cylinder, by the method for fuel gas injection generation side force, it is achieved the gesture stability of starting stage.A kind of sealed combustion gas reversing arrangement is the vitals in side force device, it is possible to complete combustion gas switching.
Summary of the invention
In order to solve problems of the prior art, the present invention proposes a kind of sealed combustion gas reversing arrangement, including: combustion gas reversal valve, lining, rudderpost, air induction conduit, jet pipe of giving vent to anger.Described combustion gas reversal valve is provided with 3 pores, and wherein 1 pore is communicated with gas generator by air induction conduit, and other 2 jet pipes of giving vent to anger with left and right communicate；Described lining is positioned in the middle of combustion gas commutation valve seat, and is connected with rudderpost.
Combustion gas is inputted by air inlet, drives rudderpost to rotate, can seal one of them venthole in rudderpost rotation process, and therefore combustion gas stream can produce lateral thrust by alternating spray.
Wherein, described lining is graphite material, utilizes the physical characteristic that graphite material is soft, high temperature resistant, lubricity is good, it is possible to overcome the gas high-temperature impact on steering wheel.
Wherein, described bushing design is stepped, and two ends, left and right are limited by combustion gas reversal valve and rudderpost respectively, and are interference fit between lining and valve body, to prevent lining from rotating and gas leakage.
Wherein, 3 pores are connected by seal washer with air induction conduit, jet pipe of giving vent to anger and carry out flat seal, to meet gas sealing requirement.
The beneficial effects of the present invention is: after guided missile goes out cylinder, utilize the present invention to make combustion gas stream left and right alternating spray produce lateral thrust, it is achieved the gesture stability of guided missile starting stage.The operation convenience to the rapidity of control signal response, the close attack ability of guided missile and shooter is improve in the MISSILE LAUNCHING starting stage.
Accompanying drawing explanation
Fig. 1 show the sealed combustion gas reversing arrangement schematic diagram of the embodiment of the present invention.
Fig. 2 show in Fig. 1 A-A sectional view.
It is rudderpost structural representation that Fig. 3 show the embodiment of the present invention.
Detailed description of the invention
Below in conjunction with accompanying drawing, describe the present invention in detail.
Fig. 1 is the sealed combustion gas reversing arrangement schematic diagram of the embodiment of the present invention, and Fig. 2 show in Fig. 1 A-A sectional view.In this embodiment, including combustion gas reversal valve 1, lining 2, rudderpost 3, air induction conduit 4, jet pipe 5 of giving vent to anger, jet pipe 6 of giving vent to anger, seal washer 7.Combustion gas reversal valve 1 is provided with 3 pores, air inlet 11, venthole 12, venthole 13.Air induction conduit 4 is connected to rudderpost 3 by air inlet 11, and jet pipe 5 of giving vent to anger, jet pipe 6 of giving vent to anger are connected to 3,3 pores of rudderpost by venthole 12, venthole 13 and are connected by seal washer 7 with air induction conduit, jet pipe of giving vent to anger and carry out flat seal.Combustion gas is inputted from air inlet by air induction conduit, and due to combustion gas commutation valve seat employing is rudderpost linkage, can seal one of them venthole hole 12 or 13 in rudderpost rotation process, and combustion gas will produce lateral thrust from jet pipe 5 of giving vent to anger, alternating spray between jet pipe 6 of giving vent to anger.
Owing to the high temperature of combustion gas can affect the performance of steering wheel, the material of lining 2 is chosen as graphite material, utilizes the physical characteristic that graphite material is soft, high temperature resistant, lubricity is good, it is possible to overcome the gas high-temperature impact on steering wheel.Lining 2 is designed to stepped, and two ends, left and right are limited by combustion gas reversal valve 1 and rudderpost 3 respectively, and is interference fit between lining 2 and combustion gas reversal valve 1, to prevent lining from rotating and gas leakage.
Described above, it is only presently preferred embodiments of the present invention, it is impossible to limit scope of the invention process with this, the impartial change that namely those skilled in the art in the art make according to the present invention, all should drop in the protection domain of the application.
Claims (4)
1. a sealed combustion gas reversing arrangement, it is characterised in that including: combustion gas reversal valve, lining, rudderpost, air induction conduit, jet pipe of giving vent to anger；Described combustion gas reversal valve is provided with 3 pores, and wherein 1 pore is communicated with gas generator by air induction conduit, and other 2 jet pipes of giving vent to anger with left and right communicate；Described lining is positioned in the middle of combustion gas commutation valve seat, and is connected with rudderpost；Combustion gas is inputted by air inlet, drives rudderpost to rotate, can seal one of them venthole in rudderpost rotation process, and therefore combustion gas stream can produce lateral thrust by alternating spray.
2. sealed combustion gas reversing arrangement according to claim 1, it is characterised in that described lining is graphite material, utilizes the physical characteristic that graphite material is soft, high temperature resistant, lubricity is good, it is possible to overcome the gas high-temperature impact on steering wheel.
3. sealed combustion gas reversing arrangement according to claim 1, it is characterised in that described bushing design is stepped, two ends, left and right are limited by combustion gas reversal valve and rudderpost respectively, and are interference fit between lining and valve body, to prevent lining from rotating and gas leakage.
4. sealed combustion gas reversing arrangement according to claim 1, it is characterised in that 3 pores are connected by seal washer with air induction conduit, jet pipe of giving vent to anger and carry out flat seal, to meet gas sealing requirement.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410748304.6A CN105736754A (en) | 2014-12-10 | 2014-12-10 | Sealed gas reversing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410748304.6A CN105736754A (en) | 2014-12-10 | 2014-12-10 | Sealed gas reversing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105736754A true CN105736754A (en) | 2016-07-06 |
Family
ID=56239065
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410748304.6A Pending CN105736754A (en) | 2014-12-10 | 2014-12-10 | Sealed gas reversing device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105736754A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113776386A (en) * | 2020-06-10 | 2021-12-10 | 北京机械设备研究所 | Short-distance launching method for shipborne vertical launching load |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001132857A (en) * | 1999-11-08 | 2001-05-18 | Sumio Ando | Selector valve |
| CN201028056Y (en) * | 2007-04-29 | 2008-02-27 | 武汉奋进电力技术有限公司 | Reversal valve |
| KR20080045920A (en) * | 2006-11-21 | 2008-05-26 | 주식회사 씨엔텍엠제이보일러 | Distribution control valve |
| CN202418722U (en) * | 2012-01-03 | 2012-09-05 | 山东交通学院 | Pneumatic directional control valve |
| CN103148243A (en) * | 2013-03-21 | 2013-06-12 | 中联重科股份有限公司渭南分公司 | Reversing ball valve |
| CN203322353U (en) * | 2013-06-24 | 2013-12-04 | 孙卫东 | Dynamic commutator for airplane |
| CN203948741U (en) * | 2014-05-21 | 2014-11-19 | 航天长征化学工程股份有限公司 | A kind of three-way diverter valve |
-
2014
- 2014-12-10 CN CN201410748304.6A patent/CN105736754A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001132857A (en) * | 1999-11-08 | 2001-05-18 | Sumio Ando | Selector valve |
| KR20080045920A (en) * | 2006-11-21 | 2008-05-26 | 주식회사 씨엔텍엠제이보일러 | Distribution control valve |
| CN201028056Y (en) * | 2007-04-29 | 2008-02-27 | 武汉奋进电力技术有限公司 | Reversal valve |
| CN202418722U (en) * | 2012-01-03 | 2012-09-05 | 山东交通学院 | Pneumatic directional control valve |
| CN103148243A (en) * | 2013-03-21 | 2013-06-12 | 中联重科股份有限公司渭南分公司 | Reversing ball valve |
| CN203322353U (en) * | 2013-06-24 | 2013-12-04 | 孙卫东 | Dynamic commutator for airplane |
| CN203948741U (en) * | 2014-05-21 | 2014-11-19 | 航天长征化学工程股份有限公司 | A kind of three-way diverter valve |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113776386A (en) * | 2020-06-10 | 2021-12-10 | 北京机械设备研究所 | Short-distance launching method for shipborne vertical launching load |
| CN113776386B (en) * | 2020-06-10 | 2023-05-09 | 北京机械设备研究所 | Close range throwing method for carrier-based vertical emission load |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB03 | Change of inventor or designer information | ||
| CB03 | Change of inventor or designer information |
Inventor after: He Feng Inventor after: Chen Hui Inventor after: Kang Meiling Inventor after: Xu Tingting Inventor before: He Feng Inventor before: Chen Hui Inventor before: Xu Tingting |
|
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160706 |