CN105644799A - Separated type parachute ejection capsule for an unmanned aerial vehicle - Google Patents
Separated type parachute ejection capsule for an unmanned aerial vehicle Download PDFInfo
- Publication number
- CN105644799A CN105644799A CN201610221449.XA CN201610221449A CN105644799A CN 105644799 A CN105644799 A CN 105644799A CN 201610221449 A CN201610221449 A CN 201610221449A CN 105644799 A CN105644799 A CN 105644799A
- Authority
- CN
- China
- Prior art keywords
- cabin
- parachute
- capsule
- umbrella
- ejection
- 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.)
- Granted
Links
- 239000002775 capsule Substances 0.000 title claims abstract description 37
- 230000006835 compression Effects 0.000 claims description 5
- 238000007906 compression Methods 0.000 claims description 5
- 239000004744 fabric Substances 0.000 claims description 3
- 239000011521 glass Substances 0.000 claims description 3
- 239000003292 glue Substances 0.000 claims description 3
- 239000011347 resin Substances 0.000 claims description 3
- 229920005989 resin Polymers 0.000 claims description 3
- 238000009434 installation Methods 0.000 abstract description 3
- 238000011084 recovery Methods 0.000 abstract description 2
- 108010066057 cabin-1 Proteins 0.000 description 30
- 108010066114 cabin-2 Proteins 0.000 description 14
- 238000004804 winding Methods 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000004568 cement Substances 0.000 description 1
- 238000003756 stirring Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D45/04—Landing aids; Safety measures to prevent collision with earth's surface
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D17/00—Parachutes
- B64D17/80—Parachutes in association with aircraft, e.g. for braking thereof
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
- Vehicle Step Arrangements And Article Storage (AREA)
Abstract
The invention discloses a separated type parachute ejection capsule for an unmanned aerial vehicle, relating to the technical field of parachuting recovery for the unmanned aerial vehicle and aiming at solving the problems of the existing parachute for the unmanned aerial vehicle that a parachute and a vehicle body structure are intertwined, and the parachute is ejected out and opened untimely to cause parachuting failure and the intertwining phenomenon of the vehicle body with a parachute cover and a main parachute. The separated type parachute ejection capsule for the unmanned aerial vehicle comprises a main parachute capsule, a parachute cover capsule, a parachute capsule cover, an ejection spring, an ejection plate, an unlocking mechanism and a connecting mechanism, wherein the parachute cover capsule is obliquely arranged inside the main parachute capsule, and the parachute capsule cover is movably connected with the main parachute capsule by the connecting mechanism; the ejection plate tightly presses the ejection spring into the parachute cover capsule and is locked by an ejection lock cylinder of the unlocking mechanism; and when the parachute cover is ejected out of the capsule and is expanded by the unlocking mechanism, the main parachute can be drawn to be out of the capsule. According to the separated type parachute ejection capsule, the parachute cover capsule is obliquely arranged towards the head part of the vehicle rather than upward installation perpendicular to the vehicle body, so that components of the heading ejection speed are utilized to counteract the backwards-movement trend of the parachute cover influenced by airflows, and the intertwining phenomenon of the vehicle body and the parachute cover is avoided; and the separated type parachute ejection capsule has a simple and compact structure.
Description
Technical field
The present invention relates to the parachuting recovery technology field of unmanned plane, be specifically related to the separate type parachute ejection capsule of a kind of unmanned plane.
Background technology
At present, parachuting is the major way that unmanned plane reclaims, and the Main Function of parachute is protection unmanned plane in removal process, it is prevented that damage during landing. Currently, the reliability of parachute-opening is the major issue that parachuting faces, and parachute and the winding of airframe structure, parachute go out cabin parachute-opening all can cause parachuting failure not in time. The urgent parachuting device that Chinese patent CN103895870A proposes uses throwing umbrella spring to complete to open the cabin and parachute is perpendicular to body upwards throwing, parachute impelling is comparatively reliable, but impelling is directed upwardly, the trend of air-flow force down umbrella rearward movement cannot be offset, and be not suitable for using the parachute drawing umbrella parachute-opening; Chinese patent CN203946278U propose unmanned aircraft parachute descent umbrella cabin, by tractive draw umbrella realize main chute open, structure is ingenious, but mechanism cannot be avoided completely with draw umbrella, the winding of main chute.
Summary of the invention
The present invention is to solve existing unmanned plane parachute exist parachute and the winding of airframe structure, parachute go out cabin parachute-opening all can cause not in time parachuting failure and there is fuselage with draw umbrella, the problem such as the winding of main chute, it is provided that a kind of separate type parachute ejection capsule for unmanned plane.
For the separate type parachute ejection capsule of unmanned plane, including main chute cabin, draw umbrella cabin, umbrella hatchcover, ejection-spring, ejection plate, solution latch mechanism and bindiny mechanism; Described umbrella cabin of drawing is inclined at inside main chute cabin, and described umbrella hatchcover is flexibly connected by bindiny mechanism with main chute cabin; Ejection plate by ejection-spring compress put into draw umbrella cabin and by solve latch mechanism launch lock core locking; When draw umbrella by solve latch mechanism eject cabin and expansion after, main chute can be drawn and go out cabin.
Beneficial effects of the present invention: a kind of unmanned plane parachute deployment means of present invention design, ejects rapidly draw umbrella when opening parachuting pattern, and opens main chute by drawing umbrella, and the winding of parachute and fuselage when avoiding parachute-opening.Concrete advantage be presented as following some:
1, the present invention draw umbrella cabin independent of main chute cabin, it is achieved that drawing umbrella has independent ejection mechanism, it is ensured that draw the ejection mechanism unlatching without influence on main chute of umbrella;
2, the umbrella cabin of drawing of the present invention is tilted towards heading installation, and non-perpendicular to fuselage upwards, utilizes the counteracting of the ejection speed component on course to draw umbrella and be subject to the trend of airflow influence and rearward movement, it is to avoid drawing umbrella is wound around with fuselage;
3, the ejection-spring drawing umbrella of the present invention is by launching lock core locking and unblock, and umbrella hatchcover is by opening the cabin lock core locking and unblock, it is achieved that to opening the cabin and launching the control of order, it is ensured that draws umbrella and flies out and do not collide with umbrella hatchcover.
4, the present invention open the cabin lock core from launch lock core by rigidity different open the cabin lock spring with launch lock spring, one solve locking wire, one unlock steering wheel and achieve sequentially-operating, principle is simple, reliable operation.
5, present configuration is simply compact, it is achieved that the modularity in umbrella cabin, easy for installation, and versatility is good.
Accompanying drawing explanation
Fig. 1 is the axonometric drawing before the separate type parachute ejection capsule for unmanned plane of the present invention opens the cabin;
Fig. 2 is the sectional view before the separate type parachute ejection capsule for unmanned plane of the present invention opens the cabin;
Fig. 3 is the partial view solving latch mechanism before the separate type parachute ejection capsule for unmanned plane of the present invention opens the cabin;
Fig. 4 is the axonometric drawing after the separate type parachute ejection capsule for unmanned plane of the present invention opens the cabin before parachute-opening;
Fig. 5 is the sectional view after the separate type parachute ejection capsule for unmanned plane of the present invention opens the cabin before parachute-opening;
Fig. 6 is that the separate type parachute for unmanned plane of the present invention launches the partial view solving latch mechanism after opening the cabin in storehouse before parachute-opening;
Fig. 7 is of the present invention for the axonometric drawing after the separate type parachute ejection capsule parachute-opening of unmanned plane;
Fig. 8 is of the present invention for the sectional view after the separate type parachute ejection capsule parachute-opening of unmanned plane;
Fig. 9 is the partial view for solving latch mechanism after the separate type parachute ejection capsule parachute-opening of unmanned plane of the present invention;
In figure: 1, main chute cabin; 2, umbrella cabin is drawn; 3, ejection-spring; 4, ejection plate; 5, lock core is launched; 6, lock spring is launched; 7, lock box; 8, steering wheel is unlocked; 9, shifting block is unlocked; 10, open the cabin lock spring; 11, umbrella is drawn; 12, umbrella hatchcover; 13, restrict between umbrella; 14, main chute; 15, open the cabin torsion spring; 16, self-locking nut; 17, bolt; 18, lock box screw; 19, open the cabin lock core; 20, locking wire is solved.
Detailed description of the invention
Detailed description of the invention one, in conjunction with Fig. 1 to Fig. 9, present embodiment is described, for the separate type parachute ejection capsule of unmanned plane, including main chute cabin 1, main chute 14, draw umbrella cabin 2, draw umbrella 11, between umbrella hatchcover 12, umbrella, restrict 13, ejection-spring 3, ejection plate 4, solve latch mechanism and bindiny mechanism. Drawing umbrella cabin 2 and be inclined at inside, main chute cabin 1, the bottom drawing umbrella cabin 2 adopts resin glue and glass cloth to be bonded in inside, main chute cabin 1; Umbrella hatchcover 12 is flexibly connected by bindiny mechanism with main chute cabin 1; Ejection-spring 3 is compressed and puts into and draws umbrella cabin 2 by ejection plate 4, and launches lock core 5 locking by what solve latch mechanism; Draw and be connected by rope 13 between umbrella between umbrella 11 with main chute 14, draw umbrella and build up cylindric filling in and draw umbrella cabin 2, compress ejection plate 4, main chute 14 folded neat after put into main chute cabin 1, when drawing after umbrella 11 ejects cabin expansion, main chute 14 can be drawn and go out cabin.
Bindiny mechanism described in present embodiment includes open the cabin torsion spring 15, self-locking nut 16 and bolt 17, and the bolt 17 that umbrella hatchcover 12 passes through to be cased with opening the cabin torsion spring 15 with main chute cabin 1 is hinged, and locks with self-locking nut 16; Described torsion spring 15 one end of opening the cabin is stuck on umbrella hatchcover 12, and the other end is stuck on main chute cabin 1.
Solution latch mechanism described in present embodiment also includes launching lock spring 6, lock box 7, unlocks steering wheel 8, unlocks shifting block 9, open the cabin lock spring 10, lock box screw 18, the lock core 19 that opens the cabin conciliate locking wire 20; Launch lock core 5 locking ejection-spring 3, draw umbrella 11 lay in power for launching; Open the cabin lock core 19 front end through the square hole on main chute cabin 1, and rear end is through lock spring 10 and the lock box 7 of opening the cabin, and compresses, by the shoulder of the lock core 19 that opens the cabin, the lock spring 10 that opens the cabin; Launching the circular hole on traverse main chute cabin 1, lock core 5 front end, rear end is through launching lock spring 6 and lock box 7, and launches lock spring 6 by the shoulder compression of the lock core 19 that opens the cabin; Open the cabin lock core 19 with launch lock core 5 rear end by solve locking wire 20 be connected; Unlocking steering wheel 8 and be arranged on main chute cabin 1 by screw, unlock the fixing shifting block 9 that unlocks in steering wheel 8 rear end, unblock shifting block 9 is positioned on the left of the solution locking wire 20 of tensioning, and lock box 7 is arranged on main chute cabin 1 by four lock box screws 18.
In conjunction with Fig. 2, Fig. 5 and Fig. 8, present embodiment being described, described umbrella cabin 2 of drawing separates with main chute cabin 1, it is achieved that draw the individual ejection of umbrella 11. Described umbrella cabin 2 of drawing is placed in main chute cabin 1 inner inclination, and incline direction, towards the direction of advance of aircraft, draws umbrella 11 with partial offset and is subject to the trend of airflow influence and rearward movement.
In present embodiment, described umbrella cabin 2 and the main chute cabin 1 of drawing is controlled by the lock core 19 that opens the cabin and opens umbrella hatchcover 12 simultaneously when opening parachuting pattern, and ejection-spring 3 is controlled by and launches lock core 5 delay and launch, it is ensured that draws umbrella 11 and flies out and do not collide with umbrella hatchcover 12. Outside the described bolt 17 in order to hinged umbrella hatchcover 12 with main chute cabin 1 is installed on main chute cabin 1, it is to avoid hindered by any bulge-structure when main chute 14 is opened.
Illustrating that present embodiment, described opening the cabin install the lock spring 10 that opens the cabin between lock core 19 and lock box 7 in conjunction with Fig. 3, Fig. 6 and Fig. 9, described launching is installed between lock core 5 and lock box 7 and is launched lock spring 6, launches lock spring 6 bigger than the stiffness coefficient of the lock spring 10 that opens the cabin. The described lock core 19 and launch between lock core 5 unthreaded hole by the two afterbody of opening the cabin, connects with solving locking wire 20, it is ensured that the lock spring 10 that opens the cabin will open the cabin lock core 19, launch lock spring 6 will launch lock core 5 compress time, solution locking wire 20 is tensioning; Described unblock steering wheel 8 afterbody is fixing unlocks shifting block 9, in order to stir solution locking wire 20, during unblock, unlock steering wheel 8 and swing, drive and unlock shifting block 9 compression solution locking wire 20, solve locking wire 20 traction to open the cabin lock core 19 and launch lock core 5, owing to the rigidity of the lock spring 10 that opens the cabin is less than launching lock spring 6, the lock core 19 that opens the cabin first is retracted, and to opening the cabin, lock spring 10 shortens to the shortest, launch lock core 5 to start to retract, it is achieved order unlocks.
Detailed description of the invention two, present embodiment are the assembling process of the separate type parachute ejection capsule for unmanned plane described in detailed description of the invention one: realized by following steps:
Step one, the bottom surface that umbrella cabin 2 will be drawn and the bottom surface in main chute cabin 1, side-fit, and ensure that launching lock core 5 can pass through the two, use resin glue and glass cloth will draw umbrella cabin 2 and main chute cabin 1 cements in bottom surface.
Step 2, ejection-spring 3 and ejection plate 4 are sequentially placed into and draw in umbrella cabin 2, by ejection plate 4, ejection-spring 3 is compressed, and with launching lock core 5 through drawing umbrella cabin 2 and main chute cabin 1 clamping ejection-spring 3 and ejection plate 4.
Step 3, putting into main chute cabin 1 after folding for main chute 14, will draw umbrella 11 and build up cylindric putting into and draw umbrella cabin 2, the connection rope between two umbrellas is put in the groove drawn on umbrella cabin 2.
Step 4, the pin shaft hole of umbrella hatchcover 12 with main chute cabin 1 is aligned, pin shaft hole and the torsion spring 15 that opens the cabin with the bolt 17 traverse pin shaft hole of umbrella hatchcover 12, main chute cabin 1, finally compressing umbrella hatchcover 12 and main chute cabin 1 with self-locking nut 10, compression degree keeps allowing that umbrella hatchcover 12 is relative to main chute cabin 1 flexible rotating. Open the cabin torsion spring 15 two ends be respectively clamped into umbrella hatchcover 12 with in the draw-in groove on main chute cabin 1.
Step 5, by unlock shifting block 9 be threaded connection be fixed on unlock steering wheel 8 afterbody, it is connected by screw the sidewall being fastened on main chute cabin 1 by unlocking steering wheel 8, the lock spring 10 that opens the cabin is enclosed within the tail end of the lock core 19 that opens the cabin, in the square hole insert lock core 19 head that opens the cabin on main chute cabin 1.
Step 6, it is enclosed within, by launching lock spring 6, the tail end launching lock core 5, will launch in the circular hole that lock core 5 inserts on main chute cabin 1. By on lock box 7 corresponding to the lock core 19 that opens the cabin, launch and after the circular hole of lock core 5 afterbody aligns with the two, push down the lock spring 10 and launch and lock spring 6 of opening the cabin, be fixed on main chute cabin 1 sidewall by lock box screw 18.
Step 7, by solution locking wire 20 through the lock core 19 that opens the cabin, launch lock core 5, through unlocking the right side tensioning of shifting block 9 and tying jail, cut off excessive thread ends.
Check to promote and unlock shifting block 9, compress and solve locking wire 20 and so as to deform, see and open the cabin lock core 19 and launch lock core and 5 whether be fully retracted successively neatly in the sidewall of main chute cabin 1, complete the assembling that umbrella cabin is overall.
The umbrella cabin entirety assembled is put into associated unmanned plane, connects the control line power line unlocking steering wheel 8, complete to install.
In present embodiment, when unmanned plane opens parachuting pattern, unlock steering wheel 8 to rotate clockwise, drive and unlock shifting block 9 compression solution locking wire 20, solve locking wire 20 and apply pulling force at the lock core 19 that opens the cabin, the afterbody that launches lock core 5 simultaneously, rigidity owing to the launching lock spring 6 lock spring 10 that relatively opens the cabin be big, and the lock spring 10 that therefore opens the cabin is first is pressed short, the lock core 19 that opens the cabin first to retract. Now, umbrella hatchcover 12 is released, and umbrella hatchcover 12 is opened rapidly under the driving of the torsion spring 15 that opens the cabin. To opening the cabin, lock spring 10 is retracted into the most in short-term, launch lock spring 6 just start to be pressed short, launch lock core 5 and just start retraction. Now, ejection-spring 3 promote ejection plate 4 will draw the relative aircraft of umbrella 11 towards front upper place eject; Drawing umbrella 11 to go out and launch behind cabin, and draw main chute 9 and go out cabin, expansion, the parachuting completing unmanned plane is reclaimed.
Claims (7)
1., for the separate type parachute ejection capsule of unmanned plane, including main chute cabin (1), draw umbrella cabin (2), umbrella hatchcover (12), ejection-spring (3), ejection plate (4), solution latch mechanism and bindiny mechanism; It is characterized in that, described in draw umbrella cabin (2) to be inclined at main chute cabin (1) internal, described umbrella hatchcover (12) is flexibly connected by bindiny mechanism with main chute cabin (1); Ejection plate (4) by ejection-spring (3) compress put into draw umbrella cabin (2) and by solve latch mechanism launch lock core (5) locking; When draw umbrella (11) by solve latch mechanism eject cabin and expansion after, main chute (14) can be drawn and go out cabin.
2. the separate type parachute ejection capsule for unmanned plane according to claim 1, it is characterized in that, described solution latch mechanism also includes launching lock spring (6), lock box (7), unlocks steering wheel (8), unlocks shifting block (9), opens the cabin and lock spring (10), the lock core that opens the cabin (19) reconciliation locking wire (20);Launch lock core (5) locking ejection-spring (3), draw umbrella (11) deposit power for launching; Open the cabin lock core (19) front end through the square hole on main chute cabin (1), and rear end is locked spring (10) and lock box (7) and compresses, by the shoulder of the lock core (19) that opens the cabin, lock spring (10) that opens the cabin through opening the cabin; Launch lock core (5) front end through the circular hole on main chute cabin (1), afterwards through launching lock spring (6) and lock box (7) and launching lock spring (6) by the shoulder compression of the lock core (19) that opens the cabin; Open the cabin lock core (19) with launch lock core (5) afterwards by solve locking wire (20) be connected; Unlock steering wheel (8) and be arranged on main chute cabin (1) by screw, unlock steering wheel (to fix on 8 and unlock shifting block (9), described unblock shifting block (9) is positioned at solution locking wire (20) left side of tensioning, and lock box (7) is arranged on main chute cabin (1) by lock box screw (18).
3. the separate type parachute ejection capsule for unmanned plane according to claim 1 and 2, it is characterized in that, described bindiny mechanism includes open the cabin torsion spring (15), self-locking nut (16) and bolt (17), the bolt (17) that described umbrella hatchcover (12) and main chute cabin (1) are passed through to be cased with opening the cabin torsion spring (15) is hinged, and locks with self-locking nut (16); The described torsion spring that opens the cabin (15) one end is stuck on umbrella hatchcover (12), and the other end is stuck on main chute cabin (1).
4. the separate type parachute ejection capsule for unmanned plane according to claim 3, it is characterized in that, it is outside that the described bolt (17) in order to hinged umbrella hatchcover (12) Yu main chute cabin (1) is installed on main chute cabin (1).
5. the separate type parachute ejection capsule for unmanned plane according to claim 1, it is characterised in that described in draw the bottom in umbrella cabin (2) to adopt resin glue and glass cloth to be bonded in main chute cabin (1) internal.
6. the separate type parachute ejection capsule for unmanned plane according to claim 1, it is characterized in that, described drawing is connected by rope (13) between umbrella between umbrella (11) with main chute (14), draw umbrella (11) to build up cylindric filling in and draw umbrella cabin (2) and compress ejection plate (4), described main chute (14) folded neat after put into main chute cabin (1).
7. the separate type parachute ejection capsule for unmanned plane according to claim 1, it is characterised in that described in draw umbrella cabin (2) to be inclined at main chute cabin (1) internal, incline direction is towards the direction of advance of aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610221449.XA CN105644799B (en) | 2016-04-11 | 2016-04-11 | Separate type parachute ejection capsule for unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610221449.XA CN105644799B (en) | 2016-04-11 | 2016-04-11 | Separate type parachute ejection capsule for unmanned plane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105644799A true CN105644799A (en) | 2016-06-08 |
| CN105644799B CN105644799B (en) | 2017-10-20 |
Family
ID=56496352
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610221449.XA Active CN105644799B (en) | 2016-04-11 | 2016-04-11 | Separate type parachute ejection capsule for unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105644799B (en) |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106275453A (en) * | 2016-08-29 | 2017-01-04 | 航宇救生装备有限公司 | A kind of escape parachute is thrown and is put device |
| CN106428586A (en) * | 2016-07-19 | 2017-02-22 | 深圳市创翼睿翔天空科技有限公司 | Forced landing device and unmanned aerial vehicle with same |
| CN107757925A (en) * | 2017-10-20 | 2018-03-06 | 中国工程物理研究院总体工程研究所 | Parachute compartment separating mechanism |
| CN108045603A (en) * | 2017-12-21 | 2018-05-18 | 星际漫步（北京）航天科技有限公司 | Cube star ejector and its method of work |
| CN108688821A (en) * | 2018-07-30 | 2018-10-23 | 桂林航天工业学院 | Unmanned plane parachute system |
| CN109250111A (en) * | 2018-09-29 | 2019-01-22 | 长光卫星技术有限公司 | A kind of Modularized unmanned machine parachute cabin system |
| CN109353519A (en) * | 2018-12-06 | 2019-02-19 | 中国科学院工程热物理研究所 | Unmanned plane parachuting Emergency recovery system |
| CN109833580A (en) * | 2017-11-28 | 2019-06-04 | 廊坊市华森集团有限公司 | A kind of unmanned plane fire extinguishing fly bomb emitter |
| CN110588990A (en) * | 2019-09-25 | 2019-12-20 | 北京凌空天行科技有限责任公司 | Parachute separation assembly and parachute system for aircraft recovery |
| CN110654553A (en) * | 2018-06-29 | 2020-01-07 | 海鹰航空通用装备有限责任公司 | Unmanned aerial vehicle steering wheel mechanism of opening umbrella |
| CN112278288A (en) * | 2020-11-05 | 2021-01-29 | 湖南浩天翼航空技术有限公司 | Parachute opening buffer mechanism of parachuting unmanned aerial vehicle and using method thereof |
| CN112441238A (en) * | 2020-11-20 | 2021-03-05 | 航天时代飞鸿技术有限公司 | Mechanical elastic parachute unfolding device and unfolding method |
| CN116424560A (en) * | 2023-06-08 | 2023-07-14 | 西安羚控电子科技有限公司 | Unmanned aerial vehicle separating and hanging-preventing mechanism, unmanned aerial vehicle and separation control method thereof |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB516292A (en) * | 1937-06-29 | 1939-12-29 | Axel Raoul Thoernblad | Improvements in or relating to parachutes |
| GB1221790A (en) * | 1967-07-17 | 1971-02-10 | Irving Air Chute Gb Ltd | Parachute |
| WO1997014611A1 (en) * | 1995-10-18 | 1997-04-24 | Irvin Aerospace Limited | Parachutes |
| CN1994821A (en) * | 2006-01-05 | 2007-07-11 | 严松山 | Whole-airplane parachute landing device |
| CN101857089A (en) * | 2009-04-07 | 2010-10-13 | 陈昌志 | Plane parachute |
| CN205602148U (en) * | 2016-04-11 | 2016-09-28 | 长光卫星技术有限公司 | A disconnect -type parachute ejection capsule for unmanned aerial vehicle |
-
2016
- 2016-04-11 CN CN201610221449.XA patent/CN105644799B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB516292A (en) * | 1937-06-29 | 1939-12-29 | Axel Raoul Thoernblad | Improvements in or relating to parachutes |
| GB1221790A (en) * | 1967-07-17 | 1971-02-10 | Irving Air Chute Gb Ltd | Parachute |
| WO1997014611A1 (en) * | 1995-10-18 | 1997-04-24 | Irvin Aerospace Limited | Parachutes |
| CN1994821A (en) * | 2006-01-05 | 2007-07-11 | 严松山 | Whole-airplane parachute landing device |
| CN101857089A (en) * | 2009-04-07 | 2010-10-13 | 陈昌志 | Plane parachute |
| CN205602148U (en) * | 2016-04-11 | 2016-09-28 | 长光卫星技术有限公司 | A disconnect -type parachute ejection capsule for unmanned aerial vehicle |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106428586A (en) * | 2016-07-19 | 2017-02-22 | 深圳市创翼睿翔天空科技有限公司 | Forced landing device and unmanned aerial vehicle with same |
| CN106275453A (en) * | 2016-08-29 | 2017-01-04 | 航宇救生装备有限公司 | A kind of escape parachute is thrown and is put device |
| CN106275453B (en) * | 2016-08-29 | 2019-01-22 | 航宇救生装备有限公司 | Device is put in a kind of throwing of escape parachute |
| CN107757925A (en) * | 2017-10-20 | 2018-03-06 | 中国工程物理研究院总体工程研究所 | Parachute compartment separating mechanism |
| CN107757925B (en) * | 2017-10-20 | 2024-01-16 | 中国工程物理研究院总体工程研究所 | Parachute cabin separating mechanism |
| CN109833580A (en) * | 2017-11-28 | 2019-06-04 | 廊坊市华森集团有限公司 | A kind of unmanned plane fire extinguishing fly bomb emitter |
| CN108045603A (en) * | 2017-12-21 | 2018-05-18 | 星际漫步（北京）航天科技有限公司 | Cube star ejector and its method of work |
| CN110654553A (en) * | 2018-06-29 | 2020-01-07 | 海鹰航空通用装备有限责任公司 | Unmanned aerial vehicle steering wheel mechanism of opening umbrella |
| CN108688821A (en) * | 2018-07-30 | 2018-10-23 | 桂林航天工业学院 | Unmanned plane parachute system |
| CN109250111A (en) * | 2018-09-29 | 2019-01-22 | 长光卫星技术有限公司 | A kind of Modularized unmanned machine parachute cabin system |
| CN109353519A (en) * | 2018-12-06 | 2019-02-19 | 中国科学院工程热物理研究所 | Unmanned plane parachuting Emergency recovery system |
| CN110588990A (en) * | 2019-09-25 | 2019-12-20 | 北京凌空天行科技有限责任公司 | Parachute separation assembly and parachute system for aircraft recovery |
| CN112278288A (en) * | 2020-11-05 | 2021-01-29 | 湖南浩天翼航空技术有限公司 | Parachute opening buffer mechanism of parachuting unmanned aerial vehicle and using method thereof |
| CN112441238A (en) * | 2020-11-20 | 2021-03-05 | 航天时代飞鸿技术有限公司 | Mechanical elastic parachute unfolding device and unfolding method |
| CN116424560A (en) * | 2023-06-08 | 2023-07-14 | 西安羚控电子科技有限公司 | Unmanned aerial vehicle separating and hanging-preventing mechanism, unmanned aerial vehicle and separation control method thereof |
| CN116424560B (en) * | 2023-06-08 | 2023-09-08 | 西安羚控电子科技有限公司 | Unmanned aerial vehicle separating and hanging-preventing mechanism, unmanned aerial vehicle and separation control method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105644799B (en) | 2017-10-20 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105644799A (en) | Separated type parachute ejection capsule for an unmanned aerial vehicle | |
| CN205602148U (en) | A disconnect -type parachute ejection capsule for unmanned aerial vehicle | |
| US20090308979A1 (en) | Parachute Release Device and Methods | |
| CN207809824U (en) | Microsatellite separator | |
| CN218113003U (en) | Cabin cover throwable deceleration parachute cabin and unmanned aerial vehicle | |
| CN207889993U (en) | A kind of multi-rotor unmanned aerial vehicle including parachute construction | |
| CN206914650U (en) | Unmanned plane parachute catapult-launching gear | |
| CN106184770B (en) | A kind of unmanned plane parachuting unit and unmanned plane | |
| CN110316398A (en) | A kind of unmanned plane takes off and recycles institutional operation vehicle | |
| CN106184701A (en) | Unmanned plane parachute automatic open device | |
| CN210707854U (en) | Novel wing connection structure | |
| US3107887A (en) | Aircraft safety system | |
| CN118238994A (en) | Automatic parachute opening device and automatic parachute opening method | |
| US3258230A (en) | High speed delivery container | |
| CN207809821U (en) | Cube star ejector | |
| CN111017213B (en) | Unmanned aerial vehicle recovery system guide umbrella penetrates umbrella mechanism | |
| CN111232222A (en) | Unmanned aerial vehicle emergency landing device and storage and ejection method thereof | |
| CN107600436A (en) | A kind of light fixed-wing aircraft cold air throws umbrella lifesaving appliance | |
| CN112441238A (en) | Mechanical elastic parachute unfolding device and unfolding method | |
| CN116062205B (en) | Unmanned aerial vehicle with integral fuselage cargo hold throwing and recycling device and throwing method | |
| CN110803289A (en) | Airplane stall-improving parachute system with parachute barrel recovery function | |
| CN205971798U (en) | Automatic opening device of unmanned aerial vehicle parachute | |
| CN115991295A (en) | Folding wing patrol aircraft mounting and throwing device and throwing method | |
| CN201086826Y (en) | Back pushing type veil opening device of minitype pilotless plane | |
| CN108033033A (en) | Microsatellite ejector and its catapult technique |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: No. 1299, Mingxi Road, Beihu science and Technology Development Zone, Changchun City, Jilin Province Patentee after: Changguang Satellite Technology Co.,Ltd. Address before: No.1759 Mingxi Road, Gaoxin North District, Changchun City, Jilin Province Patentee before: CHANG GUANG SATELLITE TECHNOLOGY Co.,Ltd. |