CN103063204A - Sealing method of control moment gyroscope inner frame - Google Patents
Sealing method of control moment gyroscope inner frame Download PDFInfo
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- CN103063204A CN103063204A CN2011103169183A CN201110316918A CN103063204A CN 103063204 A CN103063204 A CN 103063204A CN 2011103169183 A CN2011103169183 A CN 2011103169183A CN 201110316918 A CN201110316918 A CN 201110316918A CN 103063204 A CN103063204 A CN 103063204A
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Abstract
The invention discloses a sealing method of a control moment gyroscope inner frame. The method comprises the steps of: determining the parts needing sealing on the inner frame, i.e. shells, a connector and a suction hole; adopting the following sealing measures for different parts: first conducting gold-plating brazing sealing, then carrying out alloy coating brazing sealing on the shells, and pumping out the air in the inner frame with an air pump first when sealing the suction hole; and performing air tightness detection on the control moment gyroscope inner frame. Compared with the prior art, the sealing method provided in the invention has the beneficial effects that: the sealing method combining brazing sealing and O-shaped ring sealing replaces traditional rubber ring sealing, the sealing reliability is improved, and the sealed inner frame has the advantages of low leakage rate and long service life, etc. By adopting a repeatable air pumping method, adjustability of the inner frame pressure is realized, and the sealing requirements of the control moment gyroscope inner frame are satisfied.
Description
Technical field
The present invention relates to the Spacecraft Attitude Control technology, especially the inner frame of the actuating mechanism controls moment gyro of spacecraft attitude control system is realized the method for sealing.
Background technology
The control-moment gyro technology both can realize the attitude control of Large Spacecraft, can realize again the quick motor-driven of middle-size and small-size satellite.Along with the in recent years fast development of Chinese Space station technology, and the development of the national economy is more and more urgent to the demand of middle-size and small-size quick satellite, and control-moment gyro has become very popular research field.
The control-moment gyro complete machine is comprised of inner frame and outside framework.Wherein, inner frame is a hermetic high-speed rotation fly wheel system, and it provides required angular momentum for the attitude control of spacecraft.For characteristic and the demand of control-moment gyro product, need to have the characteristics such as less leakage rate, long-life to the sealing of inner frame, its Main Function has three aspects::
At first, because Speed of Reaction Wheels is higher, and produce very large windage in the meeting of rotation of air high speed, so in the ground experiment process, in order to reduce windage, reduce power consumption, need internal frame case to seal, then reduce enclosure interior air pressure and keep certain vacuum tightness by bleeding.
Secondly, good housing seal can also stop the volatilization of the high-speed bearing component lubrication oil of inner frame inside, thereby reduces the wearing and tearing of bearing, extending shaft bearing assembly life-span.Because the control-moment gyro machine life also depends primarily on the life-span of this bearing assembly, so good sealing is that the control-moment gyro complete machine is realized long-life assurance.
In addition, the assemblies such as the bearing of inner frame inside, motor all need to be worked under the higher environment of cleanliness factor, and good sealing can prevent entering of introduced contaminants, thereby improve the reliability of product.
Traditional flywheel generally is to adopt the seal with O ring method, and this encapsulating method leak rate is higher, is difficult to realize and keeps the long-time higher vacuum tightness of enclosure interior; Because the elastomeric material of O shape circle is easily aging, be difficult to realize the extended life seal of flywheel in addition; And elastomeric material is very poor to extreme environment adaptability such as high and low temperature, intense radiations, is difficult to guarantee to be sealed in the reliability of extreme environment.
So, for the performance requirement of control-moment gyro inner frame, must overcome the defective of traditional flywheel sealing, work out a kind of encapsulating method that can realize less leakage rate, long-life and have good environmental suitability.
Summary of the invention
The technical problem to be solved in the present invention provides a kind of control-moment gyro inner frame encapsulating method, can realize less leakage rate, extended life seal, can improve the sealing property of control-moment gyro inner frame.
For solving the problems of the technologies described above, the present invention realizes by following technical scheme, a kind of control-moment gyro inner frame encapsulating method, and it comprises the steps:
1) determines the required sealing of inner frame position
Comprise docking plugin card installation hole, housing junction, three position sealings of aspirating hole.
2) seal approach of each position employing
Dock first the plugin card installation hole and adopt gold-plated sealed with brazing; Again alloy layer low temperature brazing sealing is adopted in the housing junction; When aspirating hole seals, with aspiration pump the air in the inner frame is extracted out first at last, then spool is fastened on the aspirating hole, some layers of O-ring seal are compacted on the spool at this moment, thereby realize the sealing of aspirating hole.
3) with the sealing leak rate of helium mass spectrometer leak detector test control-moment gyro inner frame, realized the quantitative testing of control-moment gyro inner frame sealing effectiveness.
The method that the present invention adopts, compared with prior art, its advantage and beneficial effect are:
The encapsulating method that combines with sealed with brazing and O-ring seal sealing has replaced traditional seal with O ring, has improved sealing reliability, has the advantages such as less leakage rate, long-life.But adopt the method for repeatedly pumping, realized the controllability of inner frame air pressure, thereby found the optimum air pressure environment of flywheel work.Control-moment gyro inner frame seal request and repeatedly pumping pressure regulation demand have been satisfied.With the helium mass spectrometer leak detector test, control-moment gyro inner frame leak rate can reach 5*10-8PaL/s after the sealing.
Description of drawings
The invention will be further described below with reference to drawings and Examples.
Fig. 1 is control-moment gyro bearing wall and frame structure of the present invention and needs sealing position synoptic diagram;
Fig. 2 is connector mounting hole sealing synoptic diagram of the present invention;
Fig. 3 is housing of the present invention junction sealing synoptic diagram;
Fig. 4 is the inner frame of the present invention principle schematic of bleeding;
Fig. 5 is aspirating hole sealing synoptic diagram of the present invention.
Among the figure:
Embodiment
Referring to Fig. 1, be control-moment gyro bearing wall and frame structure of the present invention and need sealing position synoptic diagram that inner frame mainly is made of two housings (comprising base housing 1 and top cover housing 2) and the flywheel assembly 3 that is installed in enclosure interior.
Need to seal respectively three positions on the inner frame: connector mounting hole 4, housing junction 5, aspirating hole 6, to guarantee the sealing effectiveness of control-moment gyro inner frame.
Whole sealing with the flow process of bleeding is: first welded seal connector mounting hole 4-bleeds behind the 5-of welded seal housing junction and seals aspirating hole 6.
Referring to Fig. 2, be connector mounting hole sealing synoptic diagram of the present invention, dock respectively first the sidewall in plugin card installation hole 4 and the sidewall plated solder of Y26C type connector 7, then connector 7 is pressed on the connector mounting hole 4, use welding gun that both are heated, treat that the scolder fusing just finishes welding.Because inner frame inside and outside differential pressure after vacuumizing is larger, so connector mounting hole 4 is designed to the support level shape, is used for offsetting the outside atmospheric pressure that produces, thereby reduces the stressed of weld zone.In addition, the step design also can stop excessive fusion welding to flow into enclosure interior formation fifth wheel.
Referring to Fig. 3, be housing of the present invention junction sealing synoptic diagram, housing comprises base housing 1 and top cover housing 2, these two housings need to be connected sealing, the difficult point of sealing is that the sealing band is a major diameter round surface, and the larger sealing property of band more is difficult to guarantee.This example adopts the method for alloy layer low temperature brazing sealing, is about to these two housing plating Ni base alloys to be sealed, then a long copper strips 8 is covered seal area one week around the housing seal district and is brazed together with the housing of both sides.In whole welding process, by the temperature sensor measurement welding temperature, guarantee that welding temperature is no more than 90 degrees centigrade (protection housing internal electronic components) in welding process.Support ring 9 plays two effects in welding process: 1, the relative position of location two housings is constant; 2, prevent that solder flux impurity from flowing into enclosure interior.Adopt copper strips 8 welding to increase bonding area, greatly reduce the probability of housing junction 5 gas leakage, improved the reliability of sealing, solved not long problem of traditional seal with O ring life-span.
Referring to Fig. 4 and Fig. 5, be inner frame of the present invention principle and the aspirating hole sealing synoptic diagram of bleeding, adopt a cover inner frame to be bled and sealing frock 10 (by applying unit's self-control).The frock of bleeding is connected with aspiration pump 11, start aspiration pump 11, then the air of inner frame is drawn out of by the diagram path, and the screw thread among the figure on transmission rod 12 and the aspirating hole spool 13 is chamfered edge screw thread 14, air-flow can be flow through from both sides, can not affect the unimpeded of the path of bleeding.When enclosure interior drops to required air pressure, beginning turn transmission rod 12.A because transferring rotational motion between transmission rod 12 and the aspirating hole spool 13, and do not retrain each other axial degree of freedom, so aspirating hole spool 13 also will be tightened gradually, until two O-ring seals 15 that carry on the aspirating hole spool 13 are compacted, just finished the sealing that inner frame is bled and realized simultaneously aspirating hole, (see Fig. 5).The test of use helium mass spectrometer leak detector, control-moment gyro inner frame leak rate can reach 5*10-8PaL/s after the sealing.
Claims (2)
1. control-moment gyro inner frame encapsulating method is characterized in that:
1) determines required sealing position
Comprise docking plugin card installation hole, housing junction, three position sealings of aspirating hole;
2) seal approach of each position employing
Dock first the plugin card installation hole and adopt gold-plated sealed with brazing; Again alloy layer low temperature brazing sealing is adopted in the housing junction; When aspirating hole seals, with aspiration pump the air in the inner frame is extracted out first at last, then spool is fastened on the aspirating hole, some layers of O-ring seal are compacted on the spool at this moment, thereby realize the sealing of aspirating hole;
3) realize that control-moment gyro inside casing impermeability detects
With helium mass spectrometer leak detector test control-moment gyro inner frame impermeability.
2. control-moment gyro inner frame encapsulating method according to claim 1, it is characterized in that: described step 1-2), the band of housing seal is a major diameter round surface, elder generation's plating alloy, after a long copper strips covered seal area one week around the housing seal district and be brazed together with the housing of both sides.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011103169183A CN103063204A (en) | 2011-10-18 | 2011-10-18 | Sealing method of control moment gyroscope inner frame |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011103169183A CN103063204A (en) | 2011-10-18 | 2011-10-18 | Sealing method of control moment gyroscope inner frame |
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| CN103063204A true CN103063204A (en) | 2013-04-24 |
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| CN2011103169183A Pending CN103063204A (en) | 2011-10-18 | 2011-10-18 | Sealing method of control moment gyroscope inner frame |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103672390A (en) * | 2013-11-29 | 2014-03-26 | 北京兴华机械厂 | Helium filling device of floater component of triple-floating gyroscope |
| CN104567852A (en) * | 2015-01-23 | 2015-04-29 | 北京航天时代光电科技有限公司 | Airtight structural component of optical fiber gyroscope and gas tightness test method of airtight structural component |
| CN106556385A (en) * | 2016-10-20 | 2017-04-05 | 北京控制工程研究所 | A kind of Novel control moment gyro frame assembly structure |
| CN106884932A (en) * | 2017-02-07 | 2017-06-23 | 上海航天控制技术研究所 | A kind of counteraction flyback sealing structure |
| CN109604753A (en) * | 2018-11-21 | 2019-04-12 | 中国船舶重工集团公司第七0七研究所 | Solid wave/resonant gyroscope automates package system |
| CN115430592A (en) * | 2022-08-15 | 2022-12-06 | 西安航天精密机电研究所 | Gyro floater sealing auxiliary process |
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| CN2150387Y (en) * | 1992-11-11 | 1993-12-22 | 王廷波 | Mechanical sealing friction pair |
| CN1092140A (en) * | 1993-03-04 | 1994-09-14 | 西北有色金属研究院 | Sealing movable ring with combined braze-welded structure |
| US20060279046A1 (en) * | 2005-06-09 | 2006-12-14 | Carl Freudenberg Kg | Seal and system of sealing lips arranged in series |
| CN201096590Y (en) * | 2007-11-13 | 2008-08-06 | 洛阳轴研科技股份有限公司 | Momentum wheel base and seal cover leakage rate inspection device |
| CN102168758A (en) * | 2011-05-09 | 2011-08-31 | 北京航空航天大学 | Sealing bayonet device for vacuumizing |
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2011
- 2011-10-18 CN CN2011103169183A patent/CN103063204A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2150387Y (en) * | 1992-11-11 | 1993-12-22 | 王廷波 | Mechanical sealing friction pair |
| CN1092140A (en) * | 1993-03-04 | 1994-09-14 | 西北有色金属研究院 | Sealing movable ring with combined braze-welded structure |
| US20060279046A1 (en) * | 2005-06-09 | 2006-12-14 | Carl Freudenberg Kg | Seal and system of sealing lips arranged in series |
| CN201096590Y (en) * | 2007-11-13 | 2008-08-06 | 洛阳轴研科技股份有限公司 | Momentum wheel base and seal cover leakage rate inspection device |
| CN102168758A (en) * | 2011-05-09 | 2011-08-31 | 北京航空航天大学 | Sealing bayonet device for vacuumizing |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103672390A (en) * | 2013-11-29 | 2014-03-26 | 北京兴华机械厂 | Helium filling device of floater component of triple-floating gyroscope |
| CN104567852A (en) * | 2015-01-23 | 2015-04-29 | 北京航天时代光电科技有限公司 | Airtight structural component of optical fiber gyroscope and gas tightness test method of airtight structural component |
| CN104567852B (en) * | 2015-01-23 | 2018-08-31 | 北京航天时代光电科技有限公司 | A kind of fibre optic gyroscope airtight construction part and its air tightness testing method |
| CN106556385A (en) * | 2016-10-20 | 2017-04-05 | 北京控制工程研究所 | A kind of Novel control moment gyro frame assembly structure |
| CN106556385B (en) * | 2016-10-20 | 2019-10-22 | 北京控制工程研究所 | A kind of Novel control moment gyro frame assembly structure |
| CN106884932A (en) * | 2017-02-07 | 2017-06-23 | 上海航天控制技术研究所 | A kind of counteraction flyback sealing structure |
| CN109604753A (en) * | 2018-11-21 | 2019-04-12 | 中国船舶重工集团公司第七0七研究所 | Solid wave/resonant gyroscope automates package system |
| CN115430592A (en) * | 2022-08-15 | 2022-12-06 | 西安航天精密机电研究所 | Gyro floater sealing auxiliary process |
| CN115430592B (en) * | 2022-08-15 | 2023-05-23 | 西安航天精密机电研究所 | Gyro float sealing auxiliary process |
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Application publication date: 20130424 |