CN205256673U - Amphibious aircraft receive and releases landing gear - Google Patents
Amphibious aircraft receive and releases landing gear Download PDFInfo
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- CN205256673U CN205256673U CN201520995785.0U CN201520995785U CN205256673U CN 205256673 U CN205256673 U CN 205256673U CN 201520995785 U CN201520995785 U CN 201520995785U CN 205256673 U CN205256673 U CN 205256673U
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- wheel
- fuselage
- jack
- support
- retraction jack
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Abstract
The utility model relates to an amphibious aircraft receive and releases landing gear, including nose -gear jack and back wheel -retracting gear, the nose -gear jack include preceding wheel, preceding supporting component, preceding retraction jack before and the wheel take in the cabin, preceding supporting component is established in the front the wheel and is taken in the under -deck to simultaneously with preceding wheel before and the retraction jack articulated, preceding retraction jack before the wheel stretches out before through the drive of preceding supporting component the wheel take in cabin or shrink get back to before the wheel take in the cabin, back wheel -retracting gear includes left wheel, right wheel, back supporting component and back retraction jack, and back supporting component is established in the fuselage to it is articulated with left wheel, right wheel and back retraction jack simultaneously, back retraction jack stretches out or shrinks back left flotation pontoon through the back left wheel of supporting component drive, drives right wheel and stretches out or shrink back right flotation pontoon. Compared with the prior art, the utility model has the advantages of the structure sets up simply, receive and releases the flexibility, occupation space is little, safety and stability nature high.
Description
Technical field
The utility model relates to a kind of undercarriage, especially relates to a kind of amphibious aircraft folding and unfolding dress that rises and fallsPut.
Background technology
The research of amphibious aircraft is at present more and more, and aeroboat is because build is small and exquisite, operatesThe plurality of advantages such as convenient and be subject to larger welcome. And undercarriage function singleness and the exposure of some aeroboatsOutside fuselage, in hydroplaning process because gear tyre exposes, easily by pasture and water or rope class barrierCatch on, have a strong impact on flight safety. Simultaneously because undercarriage exposes the increase that brings flight resistance.
Chinese patent CN211924819U has introduced a kind of individual three-purpose vehicle, comprise body, passenger cabin andLamellar body, is provided with nose-gear and nose-gear draw off gear in the front bottom end of described lamellar body, after described bodyEnd is provided with rear undercarriage and rear undercarriage control device. But this patent with regard to how carrying out undercarriage control is not carried outFurther set forth.
Chinese patent CN215507247U has announced a kind of freedom retractable undercarriage, comprise steering wheel, right backplate andLeft backplate, steering wheel connects left backplate, and right backplate is all connected pedestal with left backplate top, and below connects by straight pin,On described left backplate, be also provided with the first chute, U-shaped pipe clamp seat, there is corresponding wearing of arranging on the U-shaped top of pipe clamp seatHole, the second chute is established in perforation below, pillar, its one end slides on the second chute, the other end through another secondChute is placed on and slides on the first chute, tube connector clamp on pipe clamp seat, and main shaft and spring, spring is placed in twoBetween perforation, main shaft through a side perforation and in be through at spring and pass from opposite side again, the connection of main shaft two ends everyOverlap and after bearing, be connected left and right backplate, connecting rod and metal steering wheel, metal steering wheel one end is connected with steering wheel output,The other end connects small end, and circular hole is established in the lower end of connecting rod, and described pillar fixes connecting rod through circular hole, its structureReliably, load ability is strong, noise and rub little when folding and unfolding. But this draw off gear structure is comparatively complicated, and zeroParts are larger, take up room larger.
Chinese patent CN215297071U has announced the warning of a kind of amphibious aircraft wheel-retracting gear positionDevice, but not open for the structure of amphibious aircraft wheel-retracting gear.
Utility model content
The purpose of this utility model is exactly to provide a kind of structure to establish in order to overcome the defect that above-mentioned prior art existsPut simple, folding and unfolding flexibly, take up room amphibious aircraft folding and unfolding take-off and landing device little, security and stability is high.
The purpose of this utility model can be achieved through the following technical solutions:
A kind of amphibious aircraft folding and unfolding take-off and landing device, described amphibious aircraft comprises fuselage, is positioned at a fuselage left sideThe left floating drum of right both sides and right floating drum, be positioned at the nose-gear jack in fuselage front, and be positioned at fuselage with leftThe rear wheel-retracting gear of floating drum, right floating drum junction,
Described nose-gear jack comprises front wheel, front support assembly, front retraction jack and front wheel receiptsReceive cabin, described front support assembly is located in front wheel storage cabin, and simultaneously and front wheel and front retraction jack hingeConnect, described front retraction jack by front support Component driver before wheel stretch out front wheel storage cabin or contraction is got back toFront wheel storage cabin;
Described rear wheel-retracting gear comprises left wheel, right wheel, rear support assembly and rear retraction jack,Described rear support assembly is located in fuselage, and simultaneously hinged with left wheel, right wheel and rear retraction jack; InstituteThe rear retraction jack of stating is stretched out or is shunk back left floating drum by the left wheel of rear support Component driver, drives right wheel to stretchGo out or shrink back right floating drum.
Described front support assembly comprises bearing diagonal, shock-absorbing support and driving rocking arm, and described bearing diagonal one end is hingedIn mmi machine wheel storage cabin, the other end is connected with front wheel, described shock-absorbing support front end be hinged on bearing diagonal inPortion, rear end is hinged with driving rocking arm front end, and described driving rocking arm rear end is hinged in front wheel storage cabin, described inFront retraction jack be located in fuselage, and be connected with driving the rear end of rocking arm;
When current retraction jack stretches out, promote to drive rocking arm to rotate, drive rocking arm to drive shock-absorbing support and bearing diagonalStretch out, make front wheel stretch out front wheel and receive out of my cabin, when current retraction jack shrinks, promote to drive rocking arm reverseRotate, drive rocking arm to drive shock-absorbing support and bearing diagonal to regain, before driving, wheel is recovered in front wheel storage cabin.
Described driving rocking arm is the integrative-structure that comprises long rocking arm and short rocker arm|, and shape between long rocking arm and short rocker arm|Become a knuckle, the end of described long rocking arm is hinged on the rear end of vibration reduction support, the end of described short rocker arm| and frontRetraction jack connects, and the position between long rocking arm and short rocker arm| is rotatably connected in front wheel storage cabin.
When described front wheel stretches out front wheel storage cabin, the long rocking arm of described shock-absorbing support and driving rocking arm is sameOn straight line, make bearing diagonal in a kind of fixing locked state, ensure the security of aircraft landing.
Described front wheel storage cabin is provided with hatchcover, this hatchcover and the interlock of front retraction jack, current folding and unfolding actionWhen cylinder stretches out, hatchcover is opened, and current retraction jack shrinks, and after making front wheel be recovered in front wheel storage cabin,Hatchcover closure.
Described rear support assembly comprise drive shaking tray, left connecting rod, right connecting rod, left vibration reduction support, right vibration reduction support,Left Connection Block and right Connection Block, described driving shaking tray is T character form structure, the middle part of described driving shaking tray turnsBe automatically connected in fuselage, the two ends of described driving shaking tray length direction are hinged left connecting rod and right connecting rod respectively, described inThe end of driving shaking tray short transverse be connected with rear retraction jack, described left connecting rod and left Connection Block are hinged,Described left Connection Block is rotatably connected in fuselage, and described left vibration reduction support is connected on left Connection Block, describedLeft wheel is connected on left vibration reduction support, and described right connecting rod and right Connection Block are hinged, and described right Connection Block rotatesBe connected in fuselage, described right vibration reduction support is connected on right Connection Block, and described right wheel is connected to right vibration dampingIn support;
Rear retraction jack stretches out to drive and drives shaking tray, drives shaking tray rotation to pull left connecting rod and right connecting rod, left connecting rodDrive left vibration reduction support and right vibration reduction support to make left wheel and right wheel be retracted into respectively left floating drum with right connecting rod simultaneouslyOr in right floating drum, when rear retraction jack shrinks, drive left wheel and right wheel to stretch out from left floating drum or right floating drum.
Described left vibration reduction support and right vibration reduction support are curved handle structure.
The position that described left vibration reduction support and right vibration reduction support stretch out fuselage is respectively equipped with left sealing shroud and right sealingCover.
Described left sealing shroud and right sealing shroud are rubber sealing boot.
In described left floating drum and right floating drum, offer respectively the cavity or the groove that hold left wheel and right wheel.
Described front retraction jack and rear retraction jack are screw mandrel stepper motor.
The utility model is set tricycle landing gear position by airplane design requirement, and left and right sides undercarriage is outsidePack up and enter in left floating drum or right floating drum, pack up the horizontal floating drum lower space of rear utilization and hide wheel and undercarriage supportStructure. Nose-gear is wheel storage cabin before head bottom independently arranges, and is provided with hatchcover, for waterproof, receivesReceive nose undercarriage, increase nose-gear hatchcover link gear simultaneously. Undercarriage driving is screw mandrel stepper motor and drivesMoving, before being connected by sychronisation when nose undercarriage is packed up, the hatchcover in wheel storage cabin, drives hatchcover to close, simultaneouslyWater surface resistance while preventing from sliding. After the support that rises and falls upwards dig both sides to the left and right, be hidden in fuselage side floating drum grooveIn, to prevent that water grass and rope class barrier from hindering aircraft taxi and bringing harm. Because gear tyre is in flightIn be hidden in body and left and right sides in floating drum, greatly reduced aircraft aerodynamic drag, improved flight efficiency. FallWhile falling, screw mandrel stepper motor by the reverse work of screw mandrel, transfers undercarriage, in landing gear support structure with fromMoving locking mechanism, the load that when locking mechanism carrying is greater than aircraft landing, undercarriage bears, thus ensure that aircraft existsThe landing on land. Simultaneously at left and right sides undercarriage and fuselage connection opening place, with water proof rubber and flexible protectionCover, to prevent that undercarriage water in water surface folding and unfolding process is penetrated into the possibility in cabin.
Compared with prior art, the utlity model has following advantage and beneficial effect:
1, the utility model adopts retractable undercarriage, wheel can be hidden in when the landing of the aircraft water surface on the waterIn body, thereby the hidden trouble of having avoided underwater obstacles to bring aircraft safety reduces flight resistance simultaneously,Improve flight efficiency.
2, the utility model adopts retractable undercarriage, can make left wheel and right wheel receive left floating drum or right floatingIn cylinder, not only save the space of fuselage interior, can also reduce the resistance that undercarriage produces in flight course, carryThe high pneumatic efficiency of aircraft.
3, the utility model is very easily demolition and maintenance for the design of undercarriage, for example, and for rear support assembly, between shock-absorbing support and connecting rod, there is a Connection Block, adopt metal parts, Connection Block and fuselage are hinged on oneRise, as the strong point of shock-absorbing support. If shock-absorbing support has been detected damage, only need to changes damping and prop upSupport can complete the maintenance of whole undercarriage.
Brief description of the drawings
Fig. 1 is nose-gear jack structural representation;
Fig. 2 is rear wheel-retracting gear structural representation.
Number in the figure: 1 is front wheel, 2 is bearing diagonal, and 3 is shock-absorbing support, and 4 for driving rocking arm, and 5 is fuselage,6 is front retraction jack, and 7 is front wheel storage cabin, and 8 is left floating drum, and 9 is right floating drum, and 10 is left wheel,11 is right wheel, and 12 is rear retraction jack, and 13 for driving shaking tray, and 14 is left connecting rod, and 15 is right connecting rod,16 is left vibration reduction support, and 17 is right vibration reduction support, and 18 is left Connection Block, and 19 is right Connection Block, and 20 is left closeBig envelope, 21 is right sealing shroud.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, the utility model is elaborated.
Embodiment
With reference to figure 1, Fig. 2, a kind of amphibious aircraft folding and unfolding take-off and landing device, amphibious aircraft comprise fuselage 5,Be positioned at the left floating drum 8 and right floating drum 9 of fuselage 5 left and right sides, be positioned at the nose-gear jack in fuselage 5 fronts,And be positioned at the rear wheel-retracting gear of fuselage 5 and left floating drum 8, right floating drum 9 junctions.
As shown in Figure 1, dotted portion in Fig. 1, is the collapsed state of undercarriage. Now undercarriage all entersIn fuselage, and will close sealing with the undercarriage door of undercarriage interlock. Nose-gear jack comprises front machineWheel 1, front support assembly, front retraction jack 6 and front wheel storage cabin 7, front support assembly is located at front wheel and receivesReceive in cabin 7, and simultaneously hinged with front wheel 1 and front retraction jack 6, and front retraction jack 6 passes through front supportBefore Component driver, wheel 1 stretches out front wheel storage cabin 7 or shrinks and get back to front wheel storage cabin 7;
Particularly, front support assembly comprises bearing diagonal 2, shock-absorbing support 3 and drives Rocker arm 4, bearing diagonal 2 oneEnd is hinged in front wheel storage cabin 7, and the other end is connected with front wheel 1, and shock-absorbing support 3 front ends are hinged on tiltedly and prop upSupport 2 middle part, driving Rocker arm 4 is the integrative-structure that comprises long rocking arm and short rocker arm|, and long rocking arm and short rocker arm| itBetween form a knuckle, the end of long rocking arm is hinged on the rear end of vibration reduction support 3, the end of short rocker arm| and front folding and unfolding are movingMake cylinder 6 and connect, the position between long rocking arm and short rocker arm| is rotatably connected in front wheel storage cabin 7. Current folding and unfoldingWhen ACTUATOR 6 stretches out, promote to drive Rocker arm 4 to rotate, drive Rocker arm 4 to drive shock-absorbing support 3 and bearing diagonal 2Stretch out, front wheel 1 is stretched out outside front wheel storage cabin 7, when current retraction jack 6 shrinks, promote to drive and shakeArm 4 rotates backward, and drives Rocker arm 4 to drive shock-absorbing support 3 and bearing diagonal 2 to regain, and before driving, wheel 1 is recovered toIn front wheel storage cabin 7.
When front wheel 1 stretches out front wheel storage cabin 7, the long rocking arm of shock-absorbing support 3 and driving Rocker arm 4 is at sameOn straight line, make bearing diagonal 2 in a kind of fixing locked state, ensure the security of aircraft landing.
Front wheel storage cabin 7 is provided with hatchcover, and this hatchcover and front retraction jack 6 link, current retraction jack6 when stretch out, and hatchcover is opened, and current retraction jack 6 shrinks, and make front wheel 1 be recovered to front wheel storage cabin7 interior after, hatchcover closure.
As shown in Figure 2, in Fig. 2, represented the two states of undercarriage: the state of emitting is as the solid line part in Fig. 2With collapsed state as the dotted portion in Fig. 2. Rear wheel-retracting gear comprise left wheel 10, right wheel 11,Rear support assembly and rear retraction jack 12, rear support assembly is located in fuselage 5, and simultaneously with left wheel 10,Right wheel 11 and rear retraction jack 12 are hinged; Rear retraction jack 12 is by the left wheel of rear support Component driver10 stretch out or shrink back left floating drum 8, drive right wheel 11 to stretch out or shrink back right floating drum 9.
Particularly, rear support assembly comprises driving shaking tray 13, left connecting rod 14, right connecting rod 15, left vibration reduction support16, right vibration reduction support 17, left Connection Block 18 and right Connection Block 19, driving shaking tray 13 is T character form structure, drivesThe middle part that shakes dish 13 is rotatably connected in fuselage 5, drives the two ends hinged left company respectively of shaking tray 13 length directionsBar 14 and right connecting rod 15, drive the end of shaking tray 13 short transverses to be connected with rear retraction jack 12, left connecting rod14 is hinged with left Connection Block 18, and left Connection Block 18 is rotatably connected in fuselage 5, and left vibration reduction support 16 is connected toOn left Connection Block 18, left wheel 10 is connected on left vibration reduction support 16, and right connecting rod 15 cuts with scissors with right Connection Block 19Connect, right Connection Block 19 is rotatably connected in fuselage 5, and right vibration reduction support 17 is connected on right Connection Block 19, the right sideWheel 11 is connected on right vibration reduction support 17; Left vibration reduction support 16 is curved handle structure with right vibration reduction support 17.Left vibration reduction support 16 is respectively equipped with left sealing shroud 20 and right sealing with the position that right vibration reduction support 17 stretches out fuselage 5Cover 21. Left sealing shroud 20 is rubber sealing boot with right sealing shroud 21.
Rear retraction jack 12 stretches out to drive and drives shaking tray 13, drives shaking tray 13 rotations to pull left connecting rod 14 with rightConnecting rod 15, left connecting rod 14 drives left vibration reduction support 16 to make left machine with right vibration reduction support 17 with right connecting rod 15 simultaneouslyWheel 10 is retracted into respectively in left floating drum 8 or right floating drum 9 with right wheel 11, when rear retraction jack 12 shrinks,Drive left wheel 10 to stretch out from left floating drum 8 or right floating drum 9 with right wheel 11.
Left floating drum 8 and the interior cavity or the groove that hold left wheel 10 and right wheel 11 of offering respectively of right floating drum 9.
In this device, front retraction jack 6 is screw mandrel stepper motor with rear retraction jack 12.
The utility model is set tricycle landing gear position by airplane design requirement, and left and right sides undercarriage is outsidePack up and enter in left floating drum or right floating drum, pack up the horizontal floating drum lower space of rear utilization and hide wheel and undercarriage supportStructure. Nose-gear is wheel storage cabin before head bottom independently arranges, and is provided with hatchcover, for waterproof, receivesReceive nose undercarriage, increase nose-gear hatchcover link gear simultaneously. Undercarriage driving is screw mandrel stepper motor and drivesMoving, before being connected by sychronisation when nose undercarriage is packed up, the hatchcover in wheel storage cabin, drives hatchcover to close, simultaneouslyWater surface resistance while preventing from sliding. After the support that rises and falls upwards dig both sides to the left and right, be hidden in fuselage side floating drum grooveIn, to prevent that water grass and rope class barrier from hindering aircraft taxi and bringing harm. Because gear tyre is in flightIn be hidden in body and left and right sides in floating drum, greatly reduced aircraft aerodynamic drag, improved flight efficiency. FallWhile falling, screw mandrel stepper motor by the reverse work of screw mandrel, transfers undercarriage, in landing gear support structure with fromMoving locking mechanism, the load that when locking mechanism carrying is greater than aircraft landing, undercarriage bears, thus ensure that aircraft existsThe landing on land. Simultaneously at left and right sides undercarriage and fuselage connection opening place, with water proof rubber and flexible protectionCover, to prevent that undercarriage water in water surface folding and unfolding process is penetrated into the possibility in cabin.
The above-mentioned description to embodiment is can understand and use in fact for ease of those skilled in the artWith novel. Person skilled in the art obviously can easily make various amendments to these embodiment, andGeneral Principle described herein is applied in other embodiment and needn't passes through performing creative labour. Therefore, this practicalityThe novel above-described embodiment that is not limited to, those skilled in the art, according to announcement of the present utility model, do not depart from this practicality newlyThe improvement that type category is made and amendment all should be within protection domains of the present utility model.
Claims (10)
1. an amphibious aircraft folding and unfolding take-off and landing device, described amphibious aircraft comprises fuselage (5), positionIn the left floating drum (8) of fuselage (5) left and right sides and right floating drum (9), be positioned at fuselage (5) front before rise and fallFrame jack, and the rear undercarriage that is positioned at fuselage (5) and left floating drum (8), right floating drum (9) junction is receivedLaying mechanism, is characterized in that,
Described nose-gear jack comprises front wheel (1), front support assembly, front retraction jack (6)And front wheel storage cabin (7), described front support assembly is located in front wheel storage cabin (7), and simultaneously with frontWheel (1) and front retraction jack (6) are hinged, and described front retraction jack (6) is by front support assemblyBefore driving, wheel (1) stretches out front wheel storage cabin (7) or shrinks and get back to front wheel storage cabin (7);
Described rear wheel-retracting gear comprises left wheel (10), right wheel (11), rear support assembly and rear receiptsPut ACTUATOR (12), described rear support assembly is located in fuselage (5), and while and left wheel (10), the right sideWheel (11) and rear retraction jack (12) are hinged; Described rear retraction jack (12) is by rear support groupPart drives left wheel (10) to stretch out or shrinks back left floating drum (8), drives right wheel (11) to stretch out or shrinks back the right sideFloating drum (9).
2. a kind of amphibious aircraft folding and unfolding take-off and landing device according to claim 1, is characterized in that instituteThe front support assembly of stating comprises bearing diagonal (2), shock-absorbing support (3) and drives rocking arm (4), described bearing diagonal(2) one end is hinged in front wheel storage cabin (7), and the other end is connected with front wheel (1), described dampingSupport the middle part that (3) front end is hinged on bearing diagonal (2), rear end is hinged with driving rocking arm (4) front end, described inDriving rocking arm (4) rear end be hinged in front wheel storage cabin (7), described front retraction jack (6) is establishedIn fuselage (5), and be connected with the rear end that drives rocking arm (4).
3. a kind of amphibious aircraft folding and unfolding take-off and landing device according to claim 2, is characterized in that instituteThe driving rocking arm (4) of stating is the integrative-structure that comprises long rocking arm and short rocker arm|, and shape between long rocking arm and short rocker arm|Become a knuckle, the end of described long rocking arm is hinged on the rear end of vibration reduction support (3), the end of described short rocker arm|Portion is connected with front retraction jack (6), and the position between long rocking arm and short rocker arm| is rotatably connected on front wheel storageIn cabin (7).
4. a kind of amphibious aircraft folding and unfolding take-off and landing device according to claim 3, is characterized in that instituteWhen the front wheel (1) of stating stretches out front wheel storage cabin (7), described shock-absorbing support (3) and driving rocking arm (4)Long rocking arm on same straight line, make bearing diagonal (2) in a kind of fixing locked state.
5. a kind of amphibious aircraft folding and unfolding take-off and landing device according to claim 2, is characterized in that instituteThe front wheel storage cabin (7) of stating is provided with hatchcover, this hatchcover and front retraction jack (6) interlock, current folding and unfoldingWhen ACTUATOR (6) stretches out, hatchcover is opened, and current retraction jack (6) shrinks, and front wheel (1) is receivedAfter getting back in front wheel storage cabin (7), hatchcover closure.
6. a kind of amphibious aircraft folding and unfolding take-off and landing device according to claim 1, is characterized in that instituteThe rear support assembly of stating comprise drive shaking tray (13), left connecting rod (14), right connecting rod (15), left vibration reduction support (16),Right vibration reduction support (17), left Connection Block (18) and right Connection Block (19), described driving shaking tray (13) is TCharacter form structure, the middle part of described driving shaking tray (13) is rotatably connected in fuselage (5), and described driving is shakenThe two ends of dish (13) length direction hinged left connecting rod (14) and right connecting rod (15) respectively, described driving shaking tray(13) end of short transverse is connected with rear retraction jack (12), and described left connecting rod (14) is connected with leftSeat (18) is hinged, and described left Connection Block (18) is rotatably connected in fuselage (5), and described left vibration damping props upIt is upper that support (16) is connected to left Connection Block (18), and described left wheel (10) is connected to left vibration reduction support (16)Upper, described right connecting rod (15) is hinged with right Connection Block (19), and described right Connection Block (19) is rotationally connectedIn fuselage (5), it is upper that described right vibration reduction support (17) is connected to right Connection Block (19), described right machineWheel (11) is connected on right vibration reduction support (17).
7. a kind of amphibious aircraft folding and unfolding take-off and landing device according to claim 6, is characterized in that instituteThe left vibration reduction support (16) of stating is curved handle structure with right vibration reduction support (17).
8. a kind of amphibious aircraft folding and unfolding take-off and landing device according to claim 6, is characterized in that instituteThe left vibration reduction support (16) of stating is respectively equipped with left sealing with the position that right vibration reduction support (17) stretches out fuselage (5)Cover (20) and right sealing shroud (21).
9. a kind of amphibious aircraft folding and unfolding take-off and landing device according to claim 8, is characterized in that instituteThe left sealing shroud (20) of stating is rubber sealing boot with right sealing shroud (21).
10. a kind of amphibious aircraft folding and unfolding take-off and landing device according to claim 1, is characterized in that instituteThe front retraction jack (6) of stating is screw mandrel stepper motor with rear retraction jack (12).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520995785.0U CN205256673U (en) | 2015-12-03 | 2015-12-03 | Amphibious aircraft receive and releases landing gear |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201520995785.0U CN205256673U (en) | 2015-12-03 | 2015-12-03 | Amphibious aircraft receive and releases landing gear |
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| CN205256673U true CN205256673U (en) | 2016-05-25 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201520995785.0U Expired - Fee Related CN205256673U (en) | 2015-12-03 | 2015-12-03 | Amphibious aircraft receive and releases landing gear |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105383695A (en) * | 2015-12-03 | 2016-03-09 | 上海奥科赛飞机有限公司 | Retractable landing gear of amphibious aircraft |
| CN108839790A (en) * | 2018-06-19 | 2018-11-20 | 中航飞机起落架有限责任公司 | A kind of collapsible folding structure of undercarriage and its folding and unfolding method |
| CN110104162A (en) * | 2019-04-28 | 2019-08-09 | 厦门大学 | A kind of solar energy flying wing with a variety of landing modes |
| CN110758723A (en) * | 2019-12-06 | 2020-02-07 | 湖南浩天翼航空技术有限公司 | Unmanned aerial vehicle convenient to receive and release undercarriage |
| CN111086628A (en) * | 2020-01-17 | 2020-05-01 | 河南大学 | Hidden foot rest of unmanned aerial vehicle |
| CN111336253A (en) * | 2020-03-12 | 2020-06-26 | 中航飞机起落架有限责任公司 | Movable hinged sealing structure for aircraft landing gear |
| CN115195998A (en) * | 2022-09-16 | 2022-10-18 | 成都纵横大鹏无人机科技有限公司 | Undercarriage winding and unwinding devices and aircraft |
-
2015
- 2015-12-03 CN CN201520995785.0U patent/CN205256673U/en not_active Expired - Fee Related
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105383695A (en) * | 2015-12-03 | 2016-03-09 | 上海奥科赛飞机有限公司 | Retractable landing gear of amphibious aircraft |
| CN108839790A (en) * | 2018-06-19 | 2018-11-20 | 中航飞机起落架有限责任公司 | A kind of collapsible folding structure of undercarriage and its folding and unfolding method |
| CN110104162A (en) * | 2019-04-28 | 2019-08-09 | 厦门大学 | A kind of solar energy flying wing with a variety of landing modes |
| CN110758723A (en) * | 2019-12-06 | 2020-02-07 | 湖南浩天翼航空技术有限公司 | Unmanned aerial vehicle convenient to receive and release undercarriage |
| CN111086628A (en) * | 2020-01-17 | 2020-05-01 | 河南大学 | Hidden foot rest of unmanned aerial vehicle |
| CN111336253A (en) * | 2020-03-12 | 2020-06-26 | 中航飞机起落架有限责任公司 | Movable hinged sealing structure for aircraft landing gear |
| CN111336253B (en) * | 2020-03-12 | 2022-04-12 | 中航飞机起落架有限责任公司 | Movable hinged sealing structure for aircraft landing gear |
| CN115195998A (en) * | 2022-09-16 | 2022-10-18 | 成都纵横大鹏无人机科技有限公司 | Undercarriage winding and unwinding devices and aircraft |
| CN115195998B (en) * | 2022-09-16 | 2022-12-23 | 成都纵横大鹏无人机科技有限公司 | Undercarriage winding and unwinding devices and aircraft |
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Effective date of registration: 20190202 Address after: 201308 Four Blocks in Zone C of Xinxing Industrial Park, No. 1500 Lailin Road, Lingang Industrial Zone, Pudong New Area, Shanghai Patentee after: Shanghai Olympic Games General Aviation Co., Ltd. Address before: 201707 Shanghai Qingpu District Beiqing Highway No. 8228, three District 8, 3, 1 B area 177 room. Patentee before: SHANGHAI AOKESAI AIRCRAFT CO., LTD. |
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Granted publication date: 20160525 Termination date: 20191203 |