CN102155883A - Small-size quickly separated firer-unlocking bolt - Google Patents
Small-size quickly separated firer-unlocking bolt Download PDFInfo
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- CN102155883A CN102155883A CN2010106070067A CN201010607006A CN102155883A CN 102155883 A CN102155883 A CN 102155883A CN 2010106070067 A CN2010106070067 A CN 2010106070067A CN 201010607006 A CN201010607006 A CN 201010607006A CN 102155883 A CN102155883 A CN 102155883A
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Abstract
The invention provides a small-size quickly separated firer-unlocking bolt. The small-size quickly separated firer-unlocking bolt comprises an unlocking bolt main body (1), a sealing ring (2) and a semiconductor bridge-type pressure cartridge case (3). In the small-size quickly separated firer-unlocking bolt, a semiconductor bridge firing element is adopted as a firer connection and separation mechanism of the firing element; the whole axial length of the small-size quickly separated firer-unlocking bolt is 60 to 65 millimeters, and the radial size is less than or equal to 16 millimeters; the separation time of the small-size quickly separated firer-unlocking bolt is 1.0 to 1.1 microseconds, the separation synchronism is 0.10 to 0.15 microseconds, and the connection bearing capacity is 21 to 25kN. The small-size quickly separated firer-unlocking bolt has the characteristics of small structural size, short separation time, high synchronism, low firing energy and the like; a safe, quick and synchronous separation function of the interstage of a spacecraft can be realized; the small-size quickly separated firer-unlocking bolt can be directly applied to interstage separation systems of the spacecrafts such as high-speed guided missiles, airships, satellites and the like; meanwhile, a beneficial reference is provided for a design of a similar power source firer mechanism.
Description
Technical field
The present invention relates to spacecraft inter-stages such as a kind of guided missile, satellite and airship and connect firer's release screw bolt of using with separation function, it is made of semiconductive bridge ignition element pressure cartridge case and release bolt body.
Background technology
Firer's release screw bolt is compared characteristics such as having volume is little, simple in structure, disengaging time weak point, synchronism height with the mechanical release separating mechanism.Owing to will consider to satisfy the safety indexes requirement that 1A1W5min misfires, its disengaging time performance optimum level generally is in tens to a few tens of milliseconds magnitude (under the 5A direct current ignition condition) to existing spacecraft with firer's release screw bolt.Some special separation occasions for example stage separation require separation rapider, and disengaging time often is not more than 10ms, and synchronism is not more than 1ms.The existing pressure cartridge case firer release screw bolt that the insensitiveness ignition element is housed can not satisfy and separated requirement rapidly, the insensitiveness ignition element of pressure cartridge case is generally bridge silk formula or bridge belt at present, though this class ignition element can be realized the 1A1W5min security requirement of misfiring, but shorten action time and must improve firing current greatly, as greater than direct current 10A.Carry-on like this power supply size must increase, and power supply load is multiplied, and is difficult to provide so big electric current and load sometimes on the aircraft.The present invention studies by experiment and obtains following understanding, the disengaging time of firer's release screw bolt is made up of pressure cartridge case action time and two part-times of release bolt machine tool disengaging time, wherein the pressure cartridge case has occupied most of disengaging time action time, and release screw bolt provided by the invention machinery disengaging time is less than 1 millisecond.Therefore, can reduce the disengaging time of firer's release screw bolt by the technological approaches that shortens pressure cartridge case action time.The present invention proposes to adopt the power source of the pressure cartridge case of short semiconductive bridge ignition element action time as release screw bolt, can satisfy under safety indexes that 1A1W5min misfires requires, realize making the disengaging time of firer's release screw bolt to be not more than the technical merit that 2ms, synchronism are not more than 0.2ms.
Summary of the invention
In order to realize the quick separation of spacecraft inter-stages such as guided missile, satellite and airship, the present invention has designed a kind of firer's release screw bolt of small-sized, quick separation, its axial length is between 60～65mm, and radial dimension is not more than 16mm, and disengaging time is not more than 2ms, synchronism is not more than 0.2ms.
The technical solution adopted for the present invention to solve the technical problems is:
A kind of firer's release screw bolt of small-sized, quick separation, it is made up of release screw bolt body, sealing ring, semiconductor bridge-type pressure cartridge case.
By release screw bolt body and semiconductor bridge-type pressure cartridge case are carried out parameters of structural dimension optimization and miniaturization design, the axial length that makes whole release screw bolt is between 60～65mm, and radial dimension is not more than 16mm, realizes the miniaturization of release screw bolt.
The release screw bolt body construction is by the semiconductor bridge-type pressure cartridge case that is threaded of M14 * 1-6H.
By the factors such as separation tripping force, coyote hole volume and the designing requirement of powder charge nargin of calculating firer's release screw bolt in advance, determine that powder charge is divided into two-layer in the semiconductor bridge-type pressure cartridge case, ground floor filling lead styphnate ignition charge 5mg, the second layer loads 2/1 camphor tree propellant powder 30mg.
By filling up the curing glue-line in payment to a porter in semiconductor bridge-type pressure cartridge case and the gap between the ceramic plug, increase the assembling intensity of semiconductor bridge-type pressure cartridge case and release screw bolt body, the combustion gas that gunpowder produces in the sealing semiconductor bridge-type pressure cartridge case prevents gas leakage.
Adopt the power source of semiconductor bridge-type pressure cartridge case as firer's release screw bolt, when feeding 3A～5A electric current for the semiconductive bridge ignition element, powder charge in the pressure cartridge case can be ignited by the semiconductive bridge ignition element, and then produces high-temperature high-pressure fuel gas promotion release screw bolt realization separation function.
Adopt the ignition element of semiconductive bridge as the pressure cartridge case, purpose is in order to guarantee that the pressure cartridge case has the safe current that 1A1W5min misfires, reduce pressure cartridge case time of ignition, shorten the disengaging time of firer's release screw bolt, improve the separation synchronism of firer's release screw bolt.
Beneficial effect of the present invention: through performance test, the disengaging time of firer's release screw bolt is 1.0～1.1ms, the separation synchronism is 0.10～0.15ms, the connection bearing capacity is 21～25kN, have that physical dimension is little, disengaging time is short, synchronism is high and the low four characteristics of firing energy, can guarantee safe, quick, the synchronous separation function of spacecraft inter-stage realization, can supply spacecraft stage separation systems such as high-speed missile, airship and satellite directly to use, the design for similar power source firer mechanism simultaneously provides useful reference.
Description of drawings
The invention will be further described below in conjunction with accompanying drawing and example.
Fig. 1 is by the firer's release screw bolt after being threaded by release screw bolt body and semiconductor bridge-type pressure cartridge case.Wherein 1. release screw bolt bodies, 2. sealing ring, 3. semiconductor bridge-type pressure cartridge case.
Fig. 2 is the release screw bolt body.Wherein 4. inner cores, 5. alignment pin, 6. voussoir, 7. piston, 8. sealing ring, 9. double O-ring seal baffle plate, 10. urceolus.
Fig. 3 is the semiconductor bridge-type pressure cartridge case of firer's release screw bolt.Wherein 11. payment to a porter, 12. shells, 13. soldering sealing layers, 14. epoxide-resin glues, 15. solder joints, 16. gold thread, 17. metal films close up, 18. metal films, 19. semiconductive bridge chips, 20.2/1 camphor tree propellant powder, 21. the lead styphnate ignition charge, 22. ceramic rings, 23. ceramic plugs, 24. solidify glue.
Fig. 4 is the state before and after firer's release screw bolt separates, state before wherein a. separates, and b. separates the back state.
The specific embodiment
A kind of firer's release screw bolt of small-sized, quick separation, it is made up of release screw bolt body, sealing ring, semiconductor bridge-type pressure cartridge case.By release screw bolt body and semiconductor bridge-type pressure cartridge case are carried out parameters of structural dimension optimization and miniaturization design, the axial length that makes whole release screw bolt is between 60～65mm, and radial dimension is not more than 16mm, realizes the miniaturization of release screw bolt.The release screw bolt body construction is by the semiconductor bridge-type pressure cartridge case that is threaded of M14 * 1-6H.By the factors such as separation tripping force, coyote hole volume and the designing requirement of powder charge nargin of calculating firer's release screw bolt in advance, determine that powder charge is divided into two-layer in the semiconductor bridge-type pressure cartridge case, ground floor filling lead styphnate ignition charge 5mg, the second layer loads 2/1 camphor tree propellant powder 30mg.By filling up the curing glue-line in payment to a porter in semiconductor bridge-type pressure cartridge case and the gap between the ceramic plug, increase the assembling intensity of semiconductor bridge-type pressure cartridge case and release screw bolt body, the combustion gas that gunpowder produces in the sealing semiconductor bridge-type pressure cartridge case prevents gas leakage.Adopt the power source of semiconductor bridge-type pressure cartridge case as firer's release screw bolt, when feeding 3A～5A electric current for the semiconductive bridge ignition element, powder charge in the pressure cartridge case can be ignited by the semiconductive bridge ignition element, and then produces high-temperature high-pressure fuel gas promotion release screw bolt realization separation function.Adopt the ignition element of semiconductive bridge as the pressure cartridge case, purpose is in order to guarantee that the pressure cartridge case has the safe current that 1A1W5min misfires, reduce pressure cartridge case time of ignition, shorten the disengaging time of firer's release screw bolt, improve the separation synchronism of firer's release screw bolt.Through performance test, the disengaging time of firer's release screw bolt is 1.0～1.1ms, the separation synchronism is 0.10～0.15ms, the connection bearing capacity is 21～25kN, have that physical dimension is little, disengaging time is short, synchronism is high and the low four characteristics of firing energy, can guarantee that the spacecraft inter-stage realizes safe, quick, synchronous separation function, can supply spacecraft stage separation systems such as high-speed missile, airship and satellite directly to use, the design for similar power source firer mechanism simultaneously provides useful reference.
Fig. 1 is firer's release screw bolt structure of small-sized, a quick separation.Wherein release screw bolt body 1 and semiconductor bridge-type pressure cartridge case 3 in order to make better tightness, are installed sealing ring 2 by being threaded on semiconductor bridge-type pressure cartridge case 3.
In Fig. 2, inner core 4, urceolus 10 and piston 7 position installation by alignment pin 5; Three voussoir 6 locking inner cores 4 and urceolus 10; The double O-ring seal baffle plate 9 that has two sealing rings 8 contacts cooperation with piston 7 thin rod ends.In addition, the one-level of spacecrafts such as the end of thread of inner core 4 and guided missile is threaded, and carries out contraposition by the front end of urceolus 10 and one-level in addition and cooperates installations, the formation connection.
In Fig. 3, when electric current by having solder joint 15 payment to a porter 11 and during the gold thread 16 that passes to, heavy doping silicon bridge in the semiconductive bridge chip produces plasma after the vaporization rapidly under height input energy, begin the lead styphnate ignition charge 21 that ignites after a period of time, and then the 2/1 camphor tree propellant powder 20 that ignites, and discharge component movement in the combustion gas formation high-temperature high-pressure fuel gas promotion release screw bolt body rapidly.Ceramic plug 23 and ceramic ring 22 are not only realized the fixed installation effect of payment to a porter 11 and semiconductive bridge chip 19, also play thermolysis; Soldering sealing layer 13 is for firm ceramic plug 23 and the ceramic ring 22 of boning, and plays the intensity that increases them; Epoxide-resin glue 14 is for semiconductive bridge chip 19 is bonded on the ceramic plug 23; In addition, adopt metal film 19 encapsulation coyote holes, and adopt metal film closing in 17 devices.At last, for semiconductor bridge-type pressure cartridge case can be closely cooperated with the release screw bolt body, wrap up in each assembly of dress semiconductor bridge-type pressure cartridge case according to body interface size design shell 12, and glue 24 firm shells 12, ceramic plug 23 and payment to a porter 11 are solidified in use, both play fixation, played sealing effectiveness again.
Fig. 4 is the state before and after firer's release screw bolt separates.Wherein a is a state before separating, and along with semiconductor bridge-type pressure cartridge case ignition back produces high-temperature high-pressure fuel gas pressure, promotes the release of release screw bolt body locking mechanism, and bolt is separated, and reaches separation back state b.
Claims (6)
1. firer's release screw bolt is characterized in that: be made up of release screw bolt body (1), sealing ring (2), semiconductor bridge-type pressure cartridge case (3).
2. firer's release screw bolt according to claim 1 is characterized in that: the release screw bolt body construction is by the semiconductor bridge-type pressure cartridge case (3) that is threaded of M14 * 1-6H.
3. firer's release screw bolt according to claim 1 and 2 is characterized in that: the lead styphnate ignition charge that the interior ground floor powder charge of semiconductor bridge-type pressure cartridge case (3) is 5mg, second layer powder charge are the 2/1 camphor tree propellant powder of 30mg.
4. firer's release screw bolt according to claim 3, it is characterized in that: by filling up the curing glue-line in payment to a porter in semiconductor bridge-type pressure cartridge case (3) and the gap between the ceramic plug, increase the assembling intensity of semiconductor bridge-type pressure cartridge case (3) and release screw bolt body (1), the combustion gas that gunpowder produces in the sealing semiconductor bridge-type pressure cartridge case (3).
5. firer's release screw bolt according to claim 4 is characterized in that: adopt semiconductor bridge-type pressure cartridge case to realize separation function as the power source of firer's release screw bolt.
6. firer's release screw bolt according to claim 5 is characterized in that: adopt semiconductive bridge to remove to shorten the disengaging time of firer's release screw bolt as the ignition element of pressure cartridge case, improve and separate synchronism.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010106070067A CN102155883A (en) | 2010-12-27 | 2010-12-27 | Small-size quickly separated firer-unlocking bolt |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010106070067A CN102155883A (en) | 2010-12-27 | 2010-12-27 | Small-size quickly separated firer-unlocking bolt |
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| CN102155883A true CN102155883A (en) | 2011-08-17 |
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| CN2010106070067A Pending CN102155883A (en) | 2010-12-27 | 2010-12-27 | Small-size quickly separated firer-unlocking bolt |
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Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102589367A (en) * | 2012-01-09 | 2012-07-18 | 南京航空航天大学 | Direct pushing type hot work nut and working method thereof |
| CN103335565A (en) * | 2013-06-18 | 2013-10-02 | 上海宇航系统工程研究所 | Wrapping tape connecting and unlocking device |
| CN103511409A (en) * | 2013-10-11 | 2014-01-15 | 上海宇航系统工程研究所 | Self-unlocking separation nut |
| CN103615450A (en) * | 2013-12-02 | 2014-03-05 | 北京化工大学 | Spacecraft unlocking and separating device |
| CN103673786A (en) * | 2013-11-26 | 2014-03-26 | 北京宇航系统工程研究所 | Impact reducing tail-section linear explosion separating device for small-diameter assisted takeoff rocket |
| CN104214186A (en) * | 2013-05-31 | 2014-12-17 | 中国人民解放军国防科学技术大学 | Heat knife type bolt device capable of achieving unlocking and releasing |
| CN105070587A (en) * | 2015-08-07 | 2015-11-18 | 贺佳国 | Micro gas generator and micro gas thruster |
| CN106481633A (en) * | 2016-11-02 | 2017-03-08 | 北京空间机电研究所 | A kind of low impact high-mechanic firer's release screw bolt |
| CN106628272A (en) * | 2016-11-15 | 2017-05-10 | 北京空间机电研究所 | Explosive unlocking device with bidirectional bearing function |
| CN106853871A (en) * | 2015-12-08 | 2017-06-16 | 上海机电工程研究所 | A kind of wedge lock separating mechanism |
| CN107235154A (en) * | 2017-06-22 | 2017-10-10 | 中国人民解放军总参谋部第六十研究所 | A kind of machine umbrella separating mechanism of firer's release |
| CN107651217A (en) * | 2017-10-25 | 2018-02-02 | 航宇救生装备有限公司 | A kind of automatically controlled ball bead type separator |
| CN109292070A (en) * | 2018-12-04 | 2019-02-01 | 湖南工业职业技术学院 | A kind of gondola connection separator and aerostatics |
| CN110749251A (en) * | 2019-11-07 | 2020-02-04 | 北京理工大学 | Charging sequence of combustion-driven high-temperature-resistant fire separation device for deep space probe |
| CN111673674A (en) * | 2020-06-29 | 2020-09-18 | 北京空间技术研制试验中心 | Pin puller and unlocking separation verification device thereof |
| CN113911210A (en) * | 2021-09-30 | 2022-01-11 | 东风汽车集团股份有限公司 | Full frame type auxiliary frame goat's horn leg support connecting piece and vehicle |
| GB2587360B (en) * | 2019-09-24 | 2022-01-19 | Martin Baker Aircraft Co Ltd | A linkage |
| CN115493462A (en) * | 2022-08-29 | 2022-12-20 | 中国兵器工业第二一三研究所 | Cross-shaped four-way missile wing synchronous unlocking mechanism |
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Cited By (27)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102589367B (en) * | 2012-01-09 | 2013-12-18 | 南京航空航天大学 | Direct pushing type hot work nut and working method thereof |
| CN102589367A (en) * | 2012-01-09 | 2012-07-18 | 南京航空航天大学 | Direct pushing type hot work nut and working method thereof |
| CN104214186A (en) * | 2013-05-31 | 2014-12-17 | 中国人民解放军国防科学技术大学 | Heat knife type bolt device capable of achieving unlocking and releasing |
| CN103335565A (en) * | 2013-06-18 | 2013-10-02 | 上海宇航系统工程研究所 | Wrapping tape connecting and unlocking device |
| CN103335565B (en) * | 2013-06-18 | 2015-11-18 | 上海宇航系统工程研究所 | A kind of band connects tripper |
| CN103511409A (en) * | 2013-10-11 | 2014-01-15 | 上海宇航系统工程研究所 | Self-unlocking separation nut |
| CN103511409B (en) * | 2013-10-11 | 2015-12-09 | 上海宇航系统工程研究所 | A kind of Self-unlocking separation nut |
| CN103673786A (en) * | 2013-11-26 | 2014-03-26 | 北京宇航系统工程研究所 | Impact reducing tail-section linear explosion separating device for small-diameter assisted takeoff rocket |
| CN103673786B (en) * | 2013-11-26 | 2015-07-08 | 北京宇航系统工程研究所 | Impact reducing tail-section linear explosion separating device for small-diameter assisted takeoff rocket |
| CN103615450A (en) * | 2013-12-02 | 2014-03-05 | 北京化工大学 | Spacecraft unlocking and separating device |
| CN105070587A (en) * | 2015-08-07 | 2015-11-18 | 贺佳国 | Micro gas generator and micro gas thruster |
| CN106853871A (en) * | 2015-12-08 | 2017-06-16 | 上海机电工程研究所 | A kind of wedge lock separating mechanism |
| CN106481633B (en) * | 2016-11-02 | 2019-04-09 | 北京空间机电研究所 | A kind of low impact high-mechanic firer's release screw bolt |
| CN106481633A (en) * | 2016-11-02 | 2017-03-08 | 北京空间机电研究所 | A kind of low impact high-mechanic firer's release screw bolt |
| CN106628272B (en) * | 2016-11-15 | 2018-11-02 | 北京空间机电研究所 | A kind of firer's tripper with two-way bearing function |
| CN106628272A (en) * | 2016-11-15 | 2017-05-10 | 北京空间机电研究所 | Explosive unlocking device with bidirectional bearing function |
| CN107235154A (en) * | 2017-06-22 | 2017-10-10 | 中国人民解放军总参谋部第六十研究所 | A kind of machine umbrella separating mechanism of firer's release |
| CN107651217A (en) * | 2017-10-25 | 2018-02-02 | 航宇救生装备有限公司 | A kind of automatically controlled ball bead type separator |
| CN109292070A (en) * | 2018-12-04 | 2019-02-01 | 湖南工业职业技术学院 | A kind of gondola connection separator and aerostatics |
| CN109292070B (en) * | 2018-12-04 | 2023-10-20 | 湖南工业职业技术学院 | Nacelle connection and separation device and aerostat |
| GB2587360B (en) * | 2019-09-24 | 2022-01-19 | Martin Baker Aircraft Co Ltd | A linkage |
| CN110749251A (en) * | 2019-11-07 | 2020-02-04 | 北京理工大学 | Charging sequence of combustion-driven high-temperature-resistant fire separation device for deep space probe |
| CN110749251B (en) * | 2019-11-07 | 2020-09-04 | 北京理工大学 | Charging sequence of combustion-driven high-temperature-resistant fire separation device for deep space probe |
| CN111673674A (en) * | 2020-06-29 | 2020-09-18 | 北京空间技术研制试验中心 | Pin puller and unlocking separation verification device thereof |
| CN111673674B (en) * | 2020-06-29 | 2022-04-19 | 北京空间技术研制试验中心 | Pin puller and unlocking separation verification device thereof |
| CN113911210A (en) * | 2021-09-30 | 2022-01-11 | 东风汽车集团股份有限公司 | Full frame type auxiliary frame goat's horn leg support connecting piece and vehicle |
| CN115493462A (en) * | 2022-08-29 | 2022-12-20 | 中国兵器工业第二一三研究所 | Cross-shaped four-way missile wing synchronous unlocking mechanism |
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Application publication date: 20110817 |