CN106323101A - Missile-borne rudder wing spreading locking mechanism based on pin pusher actuation - Google Patents
Missile-borne rudder wing spreading locking mechanism based on pin pusher actuation Download PDFInfo
- Publication number
- CN106323101A CN106323101A CN201610811481.3A CN201610811481A CN106323101A CN 106323101 A CN106323101 A CN 106323101A CN 201610811481 A CN201610811481 A CN 201610811481A CN 106323101 A CN106323101 A CN 106323101A
- Authority
- CN
- China
- Prior art keywords
- rudder
- rudder sheet
- rudderpost
- promotional implement
- span
- Prior art date
- 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.)
- Pending
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
- F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/60—Steering arrangements
- F42B10/62—Steering by movement of flight surfaces
- F42B10/64—Steering by movement of flight surfaces of fins
Abstract
A scheme that a rudder system with a wing spreading locking function pushes rudder sheets to spread simultaneously and lock the rudder sheets is adopted by the invention. After a rocket projectile is launched, the rudder system is powered by a missile-borne controller; after a rudder spreading command is emitted, the rudder system controller receives the rudder spreading command of the missile-borne control system; current amplification is performed after the rudder system controller receives a rudder spreading command signal, so that a pin pusher is started, and a pushing disc is pushed to spread the four rudder sheets simultaneously; after spreading angles reach 90 degrees, limiting is performed through the locking mechanism, and the whole wing spreading locking function is finished; and then, the missile-borne controller gives a rudder deflecting command, so that a rudder engine is controlled to drive the rudder sheets to swing, and a servo control function is realized. Meanwhile, for ensuring that the sailing posture of the rocket projectile is not affected, the spreading time of the four rudder sheets is very short and the asynchronism of spreading is very low.
Description
Technical field
The invention belongs to servo control mechanism field, be specifically related to a kind of promotional implement and move upper rudder sheet span locking mechanism.
Background technology
Along with modernized war prepare progressively deeply, the military high-new accurate beats in the urgent need to substantial amounts of, various types of
Hit weapon.In these conventional weapon models, Electrodynamic Rudder System owing to scheduling and planning and working service are convenient, cost performance is high,
The outstanding advantages such as power-mass ratio is high, become the choice of technology trend of small-power actuator, and therefore electric steering engine is toward little
Type, integration, multifunctional direction development.
For miniaturization rocket projectile, rudder sheet takes up room big relative to body existence itself, and steering wheel performance is easily by external environment
The problems such as impact, therefore, the flight of the folding and unfolding relative monomer of rudder sheet, store, transport and all have a great impact.At present, both at home and abroad
Having begun to develop this type of and have the small-sized guided rocket bullet possessing span lock function, basic employing rudder sheet is rolled over along cabin section outline
Folded form: collapsible rudder sheet duration of run is longer, affects the flight attitude of rocket projectile；Folding rudder sheet is in flight course
Intensity can be affected, and steering wheel performance also can be caused to there is larger difference；Meanwhile, the asynchronism that rudder sheet launches is relatively big, impact
Flight attitude.
Summary of the invention
It is an object of the invention to overcome above-mentioned the deficiencies in the prior art, it is provided that a kind of span based on promotional implement start is locked
Determining mechanism's design, rudder sheet is uniformly distributed in rudder system cabin, is effectively increased the time that the span puts in place, protects rudder simultaneously
After system general assembly, performance is not by external environment influence, and rudder sheet draws in completely with the section of rudder system cabin, is greatly saved rocket projectile and deposits
Storage space, has been improved particularly the amount of shooting of single operation car launcher, promotes fight capability.
The concrete technical scheme of the present invention: rudder sheet span locking mechanism on a kind of bullet based on promotional implement start, including rudder sheet,
Span mechanism, rudderpost assembly, rudder system cabin, cabin section support；Span mechanism is fixed on rudder system cabin；Rudder sheet is arranged on rudderpost group
On part, rotated by bearing pin, be in and tighten up and open mode；Span mechanism is by fixing for rudder sheet and expansion the most rapidly；Rudder sheet and
In when rudderpost assembly tightens up, centrosymmetry is distributed in rudder system cabin.
Further, described rudder sheet and rudderpost assembly are 4 sets, and cruciform symmetry is distributed in rudder system cabin.
Further, described span mechanism includes promotional implement, push-plate, and push-plate is fixedly connected on promotional implement, and promotional implement passes through
Promotional implement support is fixed in rudder system cabin, and rudder sheet arranges fixed groove along end face, and groove one side is arc, and push-plate is stuck in recessed
In groove, when promotional implement up moves, push-plate moment is driven up to promote at rudder sheet groove cambered surface.
Further, described rudder sheet groove span end face and promotional implement start direction are 30 degree of angles.
Further, rudderpost assembly includes that rudderpost and retaining mechanism, described retaining mechanism include positioning trip, spring, at rudder
Axle arranges tongue-and-groove, positions trip transverse shifting, and spring promotes location trip, after rudder sheet is opened and is put in place tongue-and-groove just with locator card
The tenon direction of motion is consistent, and spring promotes location trip to push tongue-and-groove.
Further, retaining mechanism also includes leaf spring, leaf spring be arranged on rudderpost both sides, rudderpost and rudder sheet all on leaf spring is set
Groove, one end of leaf spring is fixed in rudderpost leaf spring pocket by leaf spring location screw；When rudder sheet opens in-position, leaf spring snaps in
Leaf spring pocket.
Further, promotional implement longitudinally disposed " 1 " type groove, promotional implement is installed location screw alignment " 1 " type groove, positions spiral shell
Nail can vertically move along groove, should also play the push-plate guide effect to rudder sheet during rudder sheet launches by " 1 " type groove, with
Anti-thrust button spin and out of control.
Further, push-plate is shaped as dentation, is having rudder sheet direction convexly, and other positions are concavity, can save certain
Space.
Further, the outer surface of described rudderpost fixes sliding bearing.
Operation principle: the present invention uses the rudder system of band span lock function to promote rudder sheet to launch and locking scheme simultaneously,
After rocket bomb transmitting, on bullet, rudder system is powered by controller, and after sending the expansion instruction of rudder sheet, rudder system controller receives on bullet
The rudder of opening of control system instructs, and rudder system controller receives after opening rudder command signal and carries out Current amplifier, starts promotional implement, drives
Four rudder sheets are launched by push-plate simultaneously；Expanded angle is to after 90 °, spacing by locking mechanism, completes whole span lock function；It
After, on bullet, controller sends rudder and partially instructs, and controls servo driving rudder sheet and swings, it is achieved SERVO CONTROL function.Meanwhile, for ensureing fire
Arrow bullet navigation attitude unaffected, the duration of run of four rudder sheets must the shortest and launch asynchronism must be the least.
Beneficial effects of the present invention:
Using promotional implement and push-plate scheme, in existing bulk, the span time is short, version is compact, realization
The solution layout of relatively high power, meets use requirement.
Use spring and the version of reed double-locking device, effectively achieve rudder sheet and launch the locking merit after putting in place
Can, improve rudder sheet position locking reliability；
The span mechanism mode of operation of " one drags four " and cross rudder sheet locking Distribution of Institutions form make product function real
Existing concordance is high, symmetrical configuration intermountable is good, good impact resistance.
Accompanying drawing explanation
Structure chart under Fig. 1 rudder sheet span locking mechanism rounding state
Wherein: 1. cabin, rudder sheet 2. span mechanism 3. rudderpost assembly 4. rudder system cabin 5. section support
11. promotional implement 12. push-plate 13. promotional implement support 14. locking nuts 15. position screw
Structure chart under Fig. 2 rudder sheet span locking mechanism deployed condition
Distributed architecture figure on Fig. 3 deployed condition lower rudder sheet rudderpost assembly bullet
Fig. 4 rounding state lower rudder sheet rudderpost assembly general assembly structure chart
Wherein: 31. rudderpost 32. bearing pins 33. position trip 34. spring 35. sliding bearing
Fig. 5 deployed condition lower rudder sheet rudderpost assembly general assembly structure chart
Fig. 6 deployed condition lower rudder sheet rudderpost assembly reed distributed architecture figure
Wherein: 36. leaf spring 37. leaf spring location screw 38. bearings
Detailed description of the invention
Except embodiment described below, the present invention can also have other embodiments or implement by different way.Therefore,
It should be known that the invention is not limited in described in the following description or in the accompanying drawings shown in structure detailed of parts
Situation.When the most only introducing an embodiment, claim is not limited to this embodiment.
As Figure 1-3, rudder sheet span locking mechanism on a kind of bullet based on promotional implement start, including rudder sheet 1, span machine
Structure 2, rudderpost assembly 3, rudder system cabin 4, cabin section support 5；Span mechanism 2 is fixed on rudder system cabin 4；Rudder sheet 1 is arranged on rudderpost
On assembly 3, rotated by bearing pin 32, be in and tighten up and open mode；Span mechanism 2 is by fixing for rudder sheet 1 and expansion the most rapidly；
Rudder sheet and rudderpost assembly are 4 sets, and cruciform symmetry is distributed in rudder system cabin 4.
For ensureing the position relationship that push-plate increment and rudder sheet 1 compress one by one, by location spiral shell between push-plate and promotional implement
Nail 15 carries out position locking along " 1 " type grooves of both sides to push-plate, simultaneously should " 1 " type groove also play during rudder sheet launches right
The push-plate guide effect to rudder sheet, in case thrust button spin and out of control.
When rudder sheet 1 does not ejects holding rounding state, see accompanying drawing 1 before promotional implement start, after start, see accompanying drawing 2, cross distribution
See accompanying drawing 3.
Span mechanism 2 includes promotional implement 11, push-plate 12, and push-plate 12 is fixedly connected on promotional implement, and promotional implement 11 is by pushing away
Pin device support 13 is fixed in rudder system cabin 4, and rudder sheet 1 arranges fixed groove along end face, and groove one side is arc, and push-plate 12 blocks
In groove, when promotional implement 11 up moves, push-plate 12 moment is driven up to promote at rudder sheet groove cambered surface, the groove span
End face and promotional implement start direction are 30 degree of angles.
As shown in Figure 4, Figure 5, rudderpost assembly 3 includes rudderpost 3 and retaining mechanism, and retaining mechanism includes positioning trip 33, bullet
Spring 34, positions trip 33 transverse shifting, and spring 34 promotes location trip 33 to arrange tongue-and-groove at rudderpost 31, opens when rudder sheet 1 and puts in place
Rear tongue-and-groove is just consistent with location trip 33 direction of motion, and spring 34 promotes location trip 33 to push tongue-and-groove.
As shown in Figure 6, leaf spring 36 is installed in rudderpost 31 both sides, rudderpost 31 and rudder sheet 1 is respectively provided with leaf spring pocket, the one of leaf spring
Hold and be fixed in rudderpost leaf spring pocket by leaf spring location screw 37；When rudder sheet opens in-position, leaf spring 36 snaps in leaf spring pocket；
The sliding bearing 35 that at rudderpost, installation bearing 38 and rudderpost outer surface are fixed, on bullet follow-up to rudderpost, flight course plays balance
Support and the effect of lubrication.
Rudder sheet 1 after promotional implement start, is driven the cambered surface of 12 push-plate tooth sections, moves upward by promotional implement operating bar, and moment touches
Hit 4 rudder sheet groove span end faces, be 30 degree of angles with promotional implement start direction so that it is rotate around bearing pin 32, the rudder sheet span
Function is realized by the start form of promotional implement 13 " drags four ".
When rudder sheet 1 is expanded to 90 ° of precalculated position, two groups of structure designs at rudderpost assembly 3, are had to realize position locking respectively
Function: 1). location trip 33 is by spring 34 impetus, thus is connected with rudderpost assembly 2 by rudder sheet 1, rudder sheet 1 thus lock
90 ° of positions；2). leaf spring 36 is against rapidly rudder sheet 1 grooves on two sides in rudder sheet 1 left and right sides, also achieves rudder sheet 1 and is locked in
90 ° of positions.The realization of two above function all utilizes law of conservation of energy, will spring 34 and the elastic potential energy conversion of leaf spring 36
Make rudder sheet complete to lock work after launching to put in place in very short time for kinetic energy, and after ensureing the locking of rudder sheet, spring and leaf spring are equal
Can continue to keep rudder sheet lock-out state, not affected by flight environment of vehicle.
Obviously, those skilled in the art can carry out various change and the modification essence without deviating from the present invention to the present invention
God and scope.If these amendments and modification belong within the scope of the claims in the present invention and equivalent technologies thereof, then the present invention
It is intended to also comprise these change and modification.
Claims (9)
1. rudder sheet span locking mechanism on a bullet based on promotional implement start, it is characterised in that include rudder sheet (1), span mechanism
(2), rudderpost assembly (3), rudder system cabin (4), cabin section support (5)；Span mechanism (2) is fixed on rudder system cabin (4)；Rudder sheet
(1) it is arranged on rudderpost assembly (3), is rotated by bearing pin (32), be in and tighten up and open mode；Span mechanism (2) is by rudder sheet
(1) fixing and the rapidest expansion；In when rudder sheet (1) and rudderpost assembly (3) tighten up, centrosymmetry is distributed in rudder system cabin (4).
2. rudder sheet span locking mechanism on bullet based on promotional implement start as claimed in claim 1, it is characterised in that described rudder
Sheet and rudderpost assembly are 4 sets, and cruciform symmetry is distributed in rudder system cabin.
3. rudder sheet span locking mechanism on bullet based on promotional implement start as claimed in claim 1, it is characterised in that the described wing
Exhibition mechanism (2) includes promotional implement (11), push-plate (12), and push-plate (12) is fixedly connected on promotional implement, and promotional implement (11) is by pushing away
Pin device support (13) is fixed in rudder system cabin (4), and rudder sheet (1) arranges fixed groove along end face, and groove one side is arc, pushes away
Dish (12) is stuck in groove, when promotional implement (11) up moves, drives push-plate (12) moment up to promote rudder sheet groove cambered surface
Place.
4. rudder sheet span locking mechanism on bullet based on promotional implement start as claimed in claim 3, it is characterised in that described
Groove span end face and promotional implement start direction are 30 degree of angles.
5. rudder sheet span locking mechanism on bullet based on promotional implement start as claimed in claim 1, it is characterised in that at rudderpost
Assembly (3) includes rudderpost (3) and retaining mechanism, and described retaining mechanism includes positioning trip (33), spring (34), in rudderpost (31)
Arranging tongue-and-groove, position trip (33) transverse shifting, spring (34) promotes location trip (33), tenon after rudder sheet (1) is opened and put in place
Groove is just consistent with location trip (33) direction of motion, and spring (34) promotes location trip (33) to push tongue-and-groove.
6. rudder sheet span locking mechanism on bullet based on promotional implement start as claimed in claim 5, it is characterised in that described lock
Tight mechanism also includes leaf spring (36), and leaf spring is arranged on rudderpost (31) both sides, rudderpost (31) and rudder sheet all on leaf spring pocket, leaf spring are set
One end by leaf spring location screw (37) be fixed in rudderpost leaf spring pocket；When rudder sheet opens in-position, leaf spring (36) is blocked
Enter leaf spring pocket.
7. rudder sheet span locking mechanism on bullet based on promotional implement start as claimed in claim 3, it is characterised in that described in push away
Pin device longitudinally disposed " 1 " type groove, promotional implement is installed location screw (15) alignment " 1 " type groove, and location screw (15) can edge
Groove vertically moves.
8. rudder sheet span locking mechanism on bullet based on promotional implement start as claimed in claim 3, it is characterised in that described in push away
Disk shape is dentation, is having rudder sheet direction convexly, and other positions are concavity.
9. rudder sheet span locking mechanism on bullet based on promotional implement start as claimed in claim 3, it is characterised in that described rudder
The outer surface of axle fixes sliding bearing (35).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610811481.3A CN106323101A (en) | 2016-09-08 | 2016-09-08 | Missile-borne rudder wing spreading locking mechanism based on pin pusher actuation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610811481.3A CN106323101A (en) | 2016-09-08 | 2016-09-08 | Missile-borne rudder wing spreading locking mechanism based on pin pusher actuation |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106323101A true CN106323101A (en) | 2017-01-11 |
Family
ID=57786728
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610811481.3A Pending CN106323101A (en) | 2016-09-08 | 2016-09-08 | Missile-borne rudder wing spreading locking mechanism based on pin pusher actuation |
Country Status (1)
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|---|---|
| CN (1) | CN106323101A (en) |
Cited By (23)
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|---|---|---|---|---|
| CN107655366A (en) * | 2017-10-23 | 2018-02-02 | 贵州航天林泉电机有限公司 | A kind of steering wheel is with can collapsible rudder piece component twice |
| CN107976120A (en) * | 2017-10-23 | 2018-05-01 | 四川大学 | A kind of rudder piece pop-up and arrangement for deflecting |
| CN108168379A (en) * | 2017-11-27 | 2018-06-15 | 西安创联超声技术有限责任公司 | Alternating axis high overload rotary traveling wave ultrasonic wave steering engine |
| CN108408027A (en) * | 2018-03-21 | 2018-08-17 | 北京瑞极通达科技有限公司 | A kind of rudder face folding rotating mechanism |
| CN108871103A (en) * | 2018-06-14 | 2018-11-23 | 湖北三江航天红峰控制有限公司 | A kind of miniature missile folds the delay unfolding mechanism of rudder piece |
| CN109625243A (en) * | 2018-12-24 | 2019-04-16 | 湖南云箭集团有限公司 | A kind of folded surface expansion Aeroassisted driving device |
| CN109625244A (en) * | 2018-12-24 | 2019-04-16 | 湖南云箭集团有限公司 | Folding efficient forward swept rudder wing component |
| CN109649637A (en) * | 2018-12-05 | 2019-04-19 | 兰州飞行控制有限责任公司 | A kind of self-locking steering engine |
| CN110104161A (en) * | 2019-04-25 | 2019-08-09 | 北京理工大学 | Folding fin unfolding mechanism and its method of deploying |
| CN110260727A (en) * | 2019-07-05 | 2019-09-20 | 贵州航天控制技术有限公司 | A kind of small-sized rudder face fold mechanism component |
| CN110733630A (en) * | 2019-10-25 | 2020-01-31 | 北京机电工程研究所 | steering engine for miniature aircraft |
| CN111059965A (en) * | 2019-12-27 | 2020-04-24 | 中国航天科工集团八五一一研究所 | Small-diameter missile wing piece unfolding mechanism with limiting and self-locking functions |
| CN111272025A (en) * | 2020-01-23 | 2020-06-12 | 西安现代控制技术研究所 | Timing sequence expansion bullet speed control device |
| CN112066821A (en) * | 2020-08-19 | 2020-12-11 | 北京航天光华电子技术有限公司 | Universal integrated four-way servo rudder control device |
| CN112319768A (en) * | 2020-11-12 | 2021-02-05 | 西安长峰机电研究所 | Embedded folding wing mechanism |
| CN112683114A (en) * | 2020-12-23 | 2021-04-20 | 北京航天飞腾装备技术有限责任公司 | Vibration reduction self-locking device of missile wing unfolding mechanism |
| CN113357971A (en) * | 2021-06-16 | 2021-09-07 | 重庆航天工业有限公司 | Pushing pin mechanism |
| WO2022015409A1 (en) * | 2020-07-15 | 2022-01-20 | Raytheon Company | Frangible detent pin |
| WO2022082383A1 (en) * | 2020-10-19 | 2022-04-28 | 深圳市大疆创新科技有限公司 | Self-locking structure, arm assembly and movable platform |
| CN114427808A (en) * | 2022-01-19 | 2022-05-03 | 湖北三江航天红峰控制有限公司 | Foldable steering wheel |
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| CN107976120A (en) * | 2017-10-23 | 2018-05-01 | 四川大学 | A kind of rudder piece pop-up and arrangement for deflecting |
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| CN107655366B (en) * | 2017-10-23 | 2023-07-28 | 贵州航天林泉电机有限公司 | Steering wheel is with folded cascade rudder piece subassembly twice |
| CN107976120B (en) * | 2017-10-23 | 2024-01-19 | 四川大学 | Rudder sheet popup and deflection device |
| CN108168379A (en) * | 2017-11-27 | 2018-06-15 | 西安创联超声技术有限责任公司 | Alternating axis high overload rotary traveling wave ultrasonic wave steering engine |
| CN108408027A (en) * | 2018-03-21 | 2018-08-17 | 北京瑞极通达科技有限公司 | A kind of rudder face folding rotating mechanism |
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| CN109625244A (en) * | 2018-12-24 | 2019-04-16 | 湖南云箭集团有限公司 | Folding efficient forward swept rudder wing component |
| CN109625243B (en) * | 2018-12-24 | 2021-08-17 | 湖南云箭集团有限公司 | Pneumatic auxiliary driving device for unfolding of folding wing surface |
| CN109625243A (en) * | 2018-12-24 | 2019-04-16 | 湖南云箭集团有限公司 | A kind of folded surface expansion Aeroassisted driving device |
| CN110104161A (en) * | 2019-04-25 | 2019-08-09 | 北京理工大学 | Folding fin unfolding mechanism and its method of deploying |
| CN110260727A (en) * | 2019-07-05 | 2019-09-20 | 贵州航天控制技术有限公司 | A kind of small-sized rudder face fold mechanism component |
| CN110733630A (en) * | 2019-10-25 | 2020-01-31 | 北京机电工程研究所 | steering engine for miniature aircraft |
| CN110733630B (en) * | 2019-10-25 | 2021-11-02 | 北京机电工程研究所 | Micro aircraft steering engine |
| CN111059965A (en) * | 2019-12-27 | 2020-04-24 | 中国航天科工集团八五一一研究所 | Small-diameter missile wing piece unfolding mechanism with limiting and self-locking functions |
| CN111059965B (en) * | 2019-12-27 | 2022-04-08 | 中国航天科工集团八五一一研究所 | Small-diameter missile wing piece unfolding mechanism with limiting and self-locking functions |
| CN111272025B (en) * | 2020-01-23 | 2020-10-30 | 西安现代控制技术研究所 | Timing sequence expansion bullet speed control device |
| CN111272025A (en) * | 2020-01-23 | 2020-06-12 | 西安现代控制技术研究所 | Timing sequence expansion bullet speed control device |
| WO2022015409A1 (en) * | 2020-07-15 | 2022-01-20 | Raytheon Company | Frangible detent pin |
| CN112066821A (en) * | 2020-08-19 | 2020-12-11 | 北京航天光华电子技术有限公司 | Universal integrated four-way servo rudder control device |
| CN112066821B (en) * | 2020-08-19 | 2023-03-31 | 北京航天光华电子技术有限公司 | Universal integrated four-way servo rudder control device |
| WO2022082383A1 (en) * | 2020-10-19 | 2022-04-28 | 深圳市大疆创新科技有限公司 | Self-locking structure, arm assembly and movable platform |
| CN112319768A (en) * | 2020-11-12 | 2021-02-05 | 西安长峰机电研究所 | Embedded folding wing mechanism |
| CN112683114A (en) * | 2020-12-23 | 2021-04-20 | 北京航天飞腾装备技术有限责任公司 | Vibration reduction self-locking device of missile wing unfolding mechanism |
| CN113357971A (en) * | 2021-06-16 | 2021-09-07 | 重庆航天工业有限公司 | Pushing pin mechanism |
| CN114427808A (en) * | 2022-01-19 | 2022-05-03 | 湖北三江航天红峰控制有限公司 | Foldable steering wheel |
| CN114963884A (en) * | 2022-03-01 | 2022-08-30 | 宁波天擎航天科技有限公司 | Pneumatic controllable unfolding mechanism for target projectile rudder piece and target projectile with pneumatic controllable unfolding mechanism |
| CN114923373A (en) * | 2022-03-29 | 2022-08-19 | 四川美创达电子科技有限公司 | Large overload pushing pin device for parachute opening of shell steering engine |
| CN115218728A (en) * | 2022-08-26 | 2022-10-21 | 上海翔骜电子科技有限公司 | Electric steering engine and control system thereof |
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Application publication date: 20170111 |