CN201895770U - Locking and unlocking mechanism for aircraft airfoil - Google Patents
Locking and unlocking mechanism for aircraft airfoil Download PDFInfo
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- CN201895770U CN201895770U CN2010205468208U CN201020546820U CN201895770U CN 201895770 U CN201895770 U CN 201895770U CN 2010205468208 U CN2010205468208 U CN 2010205468208U CN 201020546820 U CN201020546820 U CN 201020546820U CN 201895770 U CN201895770 U CN 201895770U
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- aerofoil
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- 230000007246 mechanism Effects 0.000 title claims abstract description 27
- 230000000903 blocking effect Effects 0.000 claims description 9
- 229910000831 Steel Inorganic materials 0.000 claims description 4
- 239000010959 steel Substances 0.000 claims description 4
- 238000000034 method Methods 0.000 description 8
- 230000000694 effects Effects 0.000 description 6
- 230000008569 process Effects 0.000 description 6
- 230000033001 locomotion Effects 0.000 description 5
- 238000005381 potential energy Methods 0.000 description 5
- 238000009825 accumulation Methods 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000005474 detonation Methods 0.000 description 2
- 238000004146 energy storage Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000000470 constituent Substances 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000007373 indentation Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 230000002427 irreversible effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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Abstract
The utility model discloses a locking and unlocking mechanism for an aircraft airfoil, which consists of a locking releaser, an unfolding device and a lock device, wherein the unfolding device comprises a torsional spring component and a torsional spring location pin; the torsional spring component consists of two torsional springs which have the same performance and opposite rotating directions; opposite support lugs of the two torsional springs are mutually connected and are supported at the root edge of a rudder surface; and another two support lugs are sheathed and connected with a torsional spring location pin shaft fixedly connected with a rudder shaft. The locking and unlocking mechanism has small volume and simple structure, works reliably and is particularly applicable to the applications occasions that the airfoil of the minitype or micro aircraft is concealed in a cabin body and is unfolded in accordance with design requirements.
Description
Technical field
The utility model belongs to the servo control technique field, particularly relates to a kind of lockmaking release mechanism that is used for the aircraft aerofoil, and what be applicable to the aircraft aerofoil packs up and launch to lock occasion.
Background technology
Concerning small-sized or minute vehicle, it is to make it have higher operational mobility and alerting ability that aerofoil is placed in the body of cabin, the comfort feature that good working service and individual soldier use and the important assurance of alerting ability, to being placed in the aerofoil in the body of cabin, mechanism---the lockmaking release mechanism is realized by a cover to the deployed condition conversion by collapsed state, immediate lockmaking release mechanism technical scheme is by release gear in the prior art, expanding unit and blocking device are formed, as shown in Figure 1, the technological deficiency that exists is: 1. release gear adopts automatically controlled releasing mechanism, the aerofoil pivot pin that is connected, can be pushed down around the slotting arm that a certain axle rotates; rocking arm is locked by electrical control mechanism; release order when system sends; lock office and opens by the electric detonation mode; under aerofoil drives, make the rotation of locking rocking arm; the pivot pin on the release aerofoil is to reach the purpose that discharges aerofoil; the processing safety extreme difference of the automatically controlled mode of aforementioned electric detonation; simultaneously because mechanism's complexity; and rely on the rotation of aerofoil to realize complete release, unfailing performance is reduced greatly; 2. expanding unit adopts the compression spring system, when aerofoil is packed up, spring is in the compress energy storage state, when aerofoil is unlocked release, the potential energy of stage clip is converted into the kinetic energy that aerofoil rotates, aerofoil is pushed out to mode of operation, the spacing length of spring compressed that makes of obstacle axle when aforementioned compression spring is packed up by aerofoil, produce the accumulation of energy of elastic potential energy, bigger at release initial elasticity potential energy, but when aerofoil launches near mode of operation, disappeared, the phenomenon that maybe can't lock not in place can appear launching, it is unreliable to launch, and volume is bigger because this spring system takes up room simultaneously, therefore is not suitable for the limited small-sized or micro missile in space; 3. this technical scheme is to be placed in the design-calculated that requires in the body of cabin at aerofoil, relatively be applicable to and launch the fixing occasion in back, concerning the aircraft aerofoil, because requiring to launch the back is connected with wing axle, rotate with wing axle again, produce the air operated control power of control missile maneuvers, make its application be subjected to very big restriction.
The utility model content
For solving the problems of the technologies described above, the utility model provides a kind of lockmaking release mechanism that is used for the aircraft aerofoil, not only volume is little, simple in structure for this lockmaking release mechanism, reliable operation, and the application scenario that is specially adapted to that small-sized or minute vehicle aerofoil is placed in the body of cabin and launches by designing requirement.
Lockmaking release mechanism described in the utility model is to be made up of lockmaking release gear, expanding unit and blocking device, it is characterized in that: described expanding unit comprises torsion spring assembly and torsion spring locating dowel pin, the torsion spring assembly is made up of two torsion springs that performance is identical, rotation direction is opposite, the relative journal stirrup of two torsion springs links to each other and is supported on the root edge place of aerofoil, and two journal stirrups are socketed on the torsion spring alignment pin that is connected with wing axle in addition.
Described lockmaking release gear comprises electromagnetism pin, supporting plate and lock shaft, one end of electromagnetism pin is provided with supporting plate, the supporting plate middle part is provided with through hole, and the bearing pin of electromagnetism pin is connected by described through hole and lock shaft, and the other end of lock shaft directly inserts in the lock hole of aerofoil end setting.
Described blocking device comprises aerofoil lock hole, lock pin, locking spring and limited cover, one end of wing axle is provided with fork groove, aerofoil in the fork groove is provided with lock hole, and lock pin inserts in the lock hole, and the locking spring is in fork groove between lock pin and the limited cover.
Compared with prior art, the technique effect that the utility model reaches is: (1) the utility model adopts the torsional spring type expanding unit, and the potential energy converting and energy that torsion spring is stored is the kinetic energy that aerofoil rotates, and makes the expansion of aerofoil more sensitive, timely; (2) the utility model constituent elements is few, and is simple in structure, can realize the lockmaking release and the lock function of aerofoil in limited short space, and reliable operation; (3) the utility model has solved the technical barrier that can't rotate loading after many lockmaking releases small-sized or the minute vehicle aerofoil lock with expansion; (4) the utility model aerofoil of also can be applicable to aerocrafts such as unmanned plane packs up and launches to lock occasion in housing.
Description of drawings
Fig. 1 is and the immediate prior art constructional drawing of the utility model;
Fig. 2 is a working state schematic representation of the present utility model;
Fig. 3 is the installation site scheme drawing of the utility model on aerofoil;
Fig. 4 is a lockmaking release gear constructional drawing in the utility model;
Fig. 5 is an expanding unit constructional drawing in the utility model;
Fig. 6 is locking device structure figure in the utility model.
Among the figure: 1-lockmaking release gear, 2-expanding unit, 3-blocking device, 4-aerofoil, 5-electromagnetism pin, the 6-supporting plate, 7-lock shaft, 8-torsion spring assembly, 9-torsion spring locating dowel pin, 10-wing axle, 11-aerofoil lock hole, the 12-lock pin, 13-locks spring, 14-limited cover, 15-motion S. A..
The specific embodiment
Form by the following examples, content of the present utility model is described in further detail, but the scope that should at this point not be interpreted as theme described in the utility model only limits to following embodiment, do not breaking away under the above-mentioned technological thought situation of the utility model, all various modifications, replacement and changes of making according to ordinary skill knowledge and customary means include in scope of the present utility model.
Fig. 2 and Fig. 3 are respectively working process scheme drawing of the present utility model and the installation site scheme drawing of the utility model on aerofoil, the utility model realizes that the aircraft aerofoil is by the release of collapsed state to deployed condition, its process is from locking state to motion process, arrive the process of lock-out state again, therefore the lockmaking release mechanism of aerofoil is the irreversible running gear of a cover, irreversibility and single function Characteristics in view of mechanism, design plan determines that mechanism work do not adopt initiatively propulsion source, like motor, hydraulic power etc., and employing accumulation of energy converting motion system, promptly when aerofoil is packed up, store certain energy in the mechanism, after the release, mechanism releases aerofoil and locking under the effect of interior energy, function difference according to the different piece realization, aircraft aerofoil lockmaking release mechanism comprises lockmaking release gear 1, expanding unit 2 and blocking device 3 three parts, its working process is: when flight control system is carried out lockmaking release unlock instruction, lockmaking release gear 1 is removed the locking constraint of aerofoil 4 collapsed state, aerofoil 4 launches under the effect of expanding unit 2, at this moment blocking device 3 work are locked in the state of organizing work with aerofoil 4 always when arriving its control position.
Fig. 4 is a lockmaking release gear constructional drawing in the utility model, and lockmaking release gear 1 of the present utility model is an automatically controlled releasing mechanism, and its function has two: the one, aerofoil 4 is locked in collapsed state; The 2nd, the releasing operation of execution aerofoil 4; Described lockmaking release gear 1 comprises electromagnetism pin 5, supporting plate 6 and lock shaft 7, one end of electromagnetism pin 5 is provided with supporting plate 6, supporting plate 6 middle parts are provided with through hole, and the bearing pin of electromagnetism pin 5 is connected by described through hole and lock shaft 7, and the other end of lock shaft 7 directly inserts in the lock hole of aerofoil 4 ends setting; Under state of nature, an end of lock shaft 7 and the bearing pin of electromagnetism pin 5 are connected, and other end straight cutting and under the torsional interaction of 8 pairs of aerofoil 4 roots of torsion spring assembly of expanding unit 2, makes the design attitude of aerofoil 4 lockmaking in the body of cabin in the lock hole of aerofoil 4 upper ends; Behind MISSILE LAUNCHING, the canister launcher that flies out, under the flicon programming control, the unlock instruction of aerofoil 4 drives the bearing pin of electromagnetism pin 5 and does the indentation action, and the lock shaft 7 and the lock hole of aerofoil 4 ends are broken away from, aerofoil 4 rotates the cabin body under the effect of torsion spring then, reaches the purpose that discharges aerofoil 4.
Fig. 5 is an expanding unit constructional drawing in the utility model, the main effect of expanding unit 2 provides the power of aerofoil or aerofoil 4 expansion motions, it is a torsion spring energy-storage system, in the extremely short time, make the potential energy of torsion spring be converted into aerofoil 4 dead axle rotational kinetic energies during work, to satisfy the expenditure of energy in the motion process, described expanding unit 2 comprises torsion spring assembly 8 and torsion spring locating dowel pin 9, torsion spring assembly 8 is identical by two performances, the torsion spring that rotation direction is opposite is formed, the relative journal stirrup of two torsion springs links to each other and is supported on the root edge place of aerofoil, two journal stirrups are socketed on the torsion spring alignment pin 9 that is connected with wing axle 10 in addition, two torsion springs can be made by same steel wire, connect as one again after also can completing by two steel wires respectively, the journal stirrup of torsion spring and 9 sockets of torsion spring alignment pin can be made into crotch shape, annular arrangement or other shape are as long as can realize overlapping connection function.
Fig. 6 is locking device structure figure in the utility model, the effect of blocking device 3 is to be locked in working order after aerofoil 4 launches, adopt spring detent formula technical scheme, described blocking device comprises aerofoil lock hole 11, lock pin 12, locking spring 13 and limited cover 14, one end of wing axle 10 is provided with fork groove, aerofoil 4 in the fork groove is provided with lock hole 11, lock pin 12 inserts in the lock hole 11, locking spring 13 is in fork groove between lock pin 12 and the limited cover 14, aerofoil 4 is center rotation with motion S. A. 15 after release, when near the design expanded position, lock pin 12 slides near the lock pin slideway the lock hole 11, slide and enter lock hole 11 behind the segment distance, aerofoil 4 expansion this moment put in place and lock, rotate with wing axle 10 then, in order to reduce the resistance that lock pin 12 pours slideway, designed the inclined-plane of reasonably taking part in Taoism at lock pin 12 heads and slideway entrance, adopt 20 ° of cone angle matching design between lock pin 12 and the lock hole 11, so both can guarantee that lock pin 12 inserts lock hole 11 smoothly, can also reduce tolerance clearance simultaneously.
Claims (7)
1. lockmaking release mechanism that is used for the aircraft aerofoil, form by lockmaking release gear (1), expanding unit (2) and blocking device (3), it is characterized in that: described expanding unit (2) comprises torsion spring assembly (8) and torsion spring locating dowel pin (9), torsion spring assembly (8) is made up of two torsion springs that performance is identical, rotation direction is opposite, the relative journal stirrup of two torsion springs links to each other and is supported on the root edge place of aerofoil, and two journal stirrups are socketed on the torsion spring alignment pin (9) that is connected with wing axle in addition.
2. a kind of lockmaking release mechanism that is used for the aircraft aerofoil according to claim 1 is characterized in that: two torsion springs of described torsion spring assembly (8) are made by same steel wire.
3. a kind of lockmaking release mechanism that is used for the aircraft aerofoil according to claim 1 is characterized in that: two torsion springs of described torsion spring assembly (8) connect as one after being completed by two steel wires respectively again.
4. a kind of lockmaking release mechanism that is used for the aircraft aerofoil according to claim 1 is characterized in that: two torsion springs of described torsion spring assembly (8) and the journal stirrup of torsion spring alignment pin (9) socket can be made into crotch shape or annular arrangement.
5. according to each described a kind of lockmaking release mechanism that is used for the aircraft aerofoil in the claim 1 to 4, it is characterized in that: described lockmaking release gear (1) comprises electromagnetism pin (5), supporting plate (6) and lock shaft (7), one end of electromagnetism pin (5) is provided with supporting plate (6), supporting plate (6) middle part is provided with through hole, the bearing pin of electromagnetism pin (5) is connected by described through hole and lock shaft (7), and the other end of lock shaft (7) directly inserts in the lock hole of aerofoil (4) end setting.
6. according to each described a kind of lockmaking release mechanism that is used for the aircraft aerofoil in the claim 1 to 4, it is characterized in that: described blocking device (3) comprises aerofoil lock hole (11), lock pin (12), locking spring (13) and limited cover (14), one end of wing axle (10) is a fork groove, aerofoil in the fork groove (4) is provided with lock hole (11), lock pin (12) inserts in the lock hole (11), and locking spring (13) is positioned between fork groove lock pin (12) and the limited cover (14).
7. a kind of lockmaking release mechanism that is used for the aircraft aerofoil according to claim 6 is characterized in that: adopt 20 ° of cone angle matching design between described lock hole (11) and the lock pin (12).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010205468208U CN201895770U (en) | 2010-09-29 | 2010-09-29 | Locking and unlocking mechanism for aircraft airfoil |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010205468208U CN201895770U (en) | 2010-09-29 | 2010-09-29 | Locking and unlocking mechanism for aircraft airfoil |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201895770U true CN201895770U (en) | 2011-07-13 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010205468208U Expired - Lifetime CN201895770U (en) | 2010-09-29 | 2010-09-29 | Locking and unlocking mechanism for aircraft airfoil |
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| Country | Link |
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| CN (1) | CN201895770U (en) |
Cited By (21)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102530239A (en) * | 2011-12-30 | 2012-07-04 | 北京理工大学 | Double torsional spring folding-type maneuverable empennage mechanism |
| CN102556337A (en) * | 2011-12-30 | 2012-07-11 | 北京理工大学 | Bevel gear guiding type wing unfolding mechanism |
| CN102602529A (en) * | 2011-12-30 | 2012-07-25 | 北京理工大学 | Folding full-motion horizontal tail mechanism |
| CN103010453A (en) * | 2012-12-27 | 2013-04-03 | 北京理工大学 | Unmanned plane folded wing unfolding and locking device |
| CN103322868A (en) * | 2013-06-28 | 2013-09-25 | 上海新跃仪表厂 | Small combined spring type quick unfolding mechanism |
| CN103389010A (en) * | 2012-05-07 | 2013-11-13 | 刘应杰 | Rocket projectile with vanes fixed in gapless manner and unstressed lug hinge pins on tail section |
| CN104802978A (en) * | 2015-04-29 | 2015-07-29 | 北京威标至远科技发展有限公司 | Folding wing device of aircraft |
| CN105035321A (en) * | 2015-07-08 | 2015-11-11 | 中国电子科技集团公司第二十七研究所 | Miniature cylindrical launched unmanned plane and launcher |
| CN105667761A (en) * | 2016-03-02 | 2016-06-15 | 同济大学 | Foldable connecting joined wing unmanned aerial vehicle |
| CN107776870A (en) * | 2017-10-27 | 2018-03-09 | 成都云鼎智控科技有限公司 | A kind of wing-folding locked component and unmanned plane |
| CN109000521A (en) * | 2018-07-24 | 2018-12-14 | 湖北泰和电气有限公司 | Rudder wingfold device, micro missile and rudder wingfold method |
| CN109405643A (en) * | 2018-12-17 | 2019-03-01 | 江南机电设计研究所 | A kind of laterally folded formula aerofoil of high rigidity |
| CN109502009A (en) * | 2018-12-11 | 2019-03-22 | 湖北航天飞行器研究所 | A kind of aircraft folding wings locking mechanism |
| CN109631686A (en) * | 2018-12-11 | 2019-04-16 | 彩虹无人机科技有限公司 | A kind of scout missile folding wing mechanism |
| CN110155307A (en) * | 2018-04-02 | 2019-08-23 | 北京机电工程研究所 | An inertial unlocking rudder surface pop-up device |
| CN110230955A (en) * | 2019-06-28 | 2019-09-13 | 浙江理工大学 | Retaining mechanism and its expansion locking method is unfolded in submersible folding wings synchronous horizontal |
| 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 |
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| CN113401331A (en) * | 2020-06-16 | 2021-09-17 | 中北大学 | Tail wing unfolding device |
| CN114802708A (en) * | 2022-06-28 | 2022-07-29 | 北京理工大学 | Novel automatic unfolding structure of aircraft fixed wing and rudder wing |
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2010
- 2010-09-29 CN CN2010205468208U patent/CN201895770U/en not_active Expired - Lifetime
Cited By (30)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102530239B (en) * | 2011-12-30 | 2014-02-19 | 北京理工大学 | Double torsion spring foldable steerable tail mechanism |
| CN102556337A (en) * | 2011-12-30 | 2012-07-11 | 北京理工大学 | Bevel gear guiding type wing unfolding mechanism |
| CN102602529A (en) * | 2011-12-30 | 2012-07-25 | 北京理工大学 | Folding full-motion horizontal tail mechanism |
| CN102530239A (en) * | 2011-12-30 | 2012-07-04 | 北京理工大学 | Double torsional spring folding-type maneuverable empennage mechanism |
| CN103389010B (en) * | 2012-05-07 | 2015-07-22 | 刘应杰 | Rocket projectile with vanes fixed in gapless manner and unstressed lug hinge pins on tail section |
| CN103389010A (en) * | 2012-05-07 | 2013-11-13 | 刘应杰 | Rocket projectile with vanes fixed in gapless manner and unstressed lug hinge pins on tail section |
| CN103010453A (en) * | 2012-12-27 | 2013-04-03 | 北京理工大学 | Unmanned plane folded wing unfolding and locking device |
| CN103322868A (en) * | 2013-06-28 | 2013-09-25 | 上海新跃仪表厂 | Small combined spring type quick unfolding mechanism |
| CN103322868B (en) * | 2013-06-28 | 2015-09-30 | 上海新跃仪表厂 | A kind of packaged combination spring rapid unfolding mechanism |
| CN104802978A (en) * | 2015-04-29 | 2015-07-29 | 北京威标至远科技发展有限公司 | Folding wing device of aircraft |
| CN104802978B (en) * | 2015-04-29 | 2017-04-12 | 北京威标至远科技发展有限公司 | Folding wing device of aircraft |
| CN105035321A (en) * | 2015-07-08 | 2015-11-11 | 中国电子科技集团公司第二十七研究所 | Miniature cylindrical launched unmanned plane and launcher |
| CN105667761A (en) * | 2016-03-02 | 2016-06-15 | 同济大学 | Foldable connecting joined wing unmanned aerial vehicle |
| CN105667761B (en) * | 2016-03-02 | 2017-12-26 | 同济大学 | A kind of foldable connection wing layout unmanned plane |
| CN107776870A (en) * | 2017-10-27 | 2018-03-09 | 成都云鼎智控科技有限公司 | A kind of wing-folding locked component and unmanned plane |
| CN110155307B (en) * | 2018-04-02 | 2021-04-02 | 北京机电工程研究所 | An inertial unlocking rudder surface ejection device |
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| CN109000521A (en) * | 2018-07-24 | 2018-12-14 | 湖北泰和电气有限公司 | Rudder wingfold device, micro missile and rudder wingfold method |
| CN109502009A (en) * | 2018-12-11 | 2019-03-22 | 湖北航天飞行器研究所 | A kind of aircraft folding wings locking mechanism |
| CN109631686A (en) * | 2018-12-11 | 2019-04-16 | 彩虹无人机科技有限公司 | A kind of scout missile folding wing mechanism |
| CN109502009B (en) * | 2018-12-11 | 2022-06-07 | 湖北航天飞行器研究所 | Aircraft folding wing locking mechanism |
| CN109405643A (en) * | 2018-12-17 | 2019-03-01 | 江南机电设计研究所 | A kind of laterally folded formula aerofoil of high rigidity |
| CN110230955A (en) * | 2019-06-28 | 2019-09-13 | 浙江理工大学 | Retaining mechanism and its expansion locking method is unfolded in submersible folding wings synchronous horizontal |
| 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 |
| CN111306996A (en) * | 2020-01-23 | 2020-06-19 | 西安现代控制技术研究所 | Ammunition flight resistance device |
| CN111306996B (en) * | 2020-01-23 | 2022-07-05 | 西安现代控制技术研究所 | Ammunition flight resistance device |
| CN113401331A (en) * | 2020-06-16 | 2021-09-17 | 中北大学 | Tail wing unfolding device |
| CN112977805A (en) * | 2021-04-19 | 2021-06-18 | 北京航空航天大学 | Landing device for micro-miniature flapping-wing aircraft |
| CN114802708A (en) * | 2022-06-28 | 2022-07-29 | 北京理工大学 | Novel automatic unfolding structure of aircraft fixed wing and rudder wing |
| CN114802708B (en) * | 2022-06-28 | 2022-09-09 | 北京理工大学 | Novel automatic unfolding structure of aircraft fixed wing and rudder wing |
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| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20110713 |
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| DD01 | Delivery of document by public notice |
Addressee: Gu Qinghong Document name: Notice of expiration of patent right |