CN204871593U - Electronic undercarriage of aircraft - Google Patents
Electronic undercarriage of aircraft Download PDFInfo
- Publication number
- CN204871593U CN204871593U CN201520342232.5U CN201520342232U CN204871593U CN 204871593 U CN204871593 U CN 204871593U CN 201520342232 U CN201520342232 U CN 201520342232U CN 204871593 U CN204871593 U CN 204871593U
- Authority
- CN
- China
- Prior art keywords
- axle
- sleeve
- box body
- electronic
- connection block
- 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.)
- Expired - Fee Related
Links
- 230000007246 mechanism Effects 0.000 claims abstract description 10
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims abstract description 9
- 229910052802 copper Inorganic materials 0.000 claims abstract description 9
- 239000010949 copper Substances 0.000 claims abstract description 9
- 230000008878 coupling Effects 0.000 claims description 18
- 238000010168 coupling process Methods 0.000 claims description 18
- 238000005859 coupling reaction Methods 0.000 claims description 18
- 238000013016 damping Methods 0.000 claims description 15
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 12
- 238000005452 bending Methods 0.000 claims description 12
- 241000209094 Oryza Species 0.000 claims description 6
- 235000007164 Oryza sativa Nutrition 0.000 claims description 6
- 229910052742 iron Inorganic materials 0.000 claims description 6
- 235000009566 rice Nutrition 0.000 claims description 6
- 238000007789 sealing Methods 0.000 claims description 6
- 230000035939 shock Effects 0.000 abstract 3
- 230000000694 effects Effects 0.000 description 3
- 230000035945 sensitivity Effects 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000012856 packing Methods 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 230000001629 suppression Effects 0.000 description 1
Landscapes
- Transmission Devices (AREA)
Abstract
The utility model discloses an electronic undercarriage of aircraft, which comprises a drive mechanism, shock -absorbing foot frame and pulley, actuating mechanism includes main box body, be semi -enclosed inner chamber in the main box body, the upper portion of inner chamber is equipped with a lead screw, the bottom of lead screw is equipped with the bolt head, the cover is equipped with the stroke nut on the lead screw, the top cover of lead screw is equipped with first plane thrust ball bearing, the lower part of inner chamber is equipped with a motor, the output shaft of motor has the reducing gear box, the output shaft of reducing gear box has second plane thrust ball bearing, the bolt headgear is located in the thrust ball bearing of second plane, be connected with the connecting seat on the stroke nut, the connecting seat is located between the shaft hole of seting up on the main box body, the shock -absorbing foot frame is connected in the connecting seat bottom, the copper sheathing that the connecting seat bottom was located including the cover to the shock -absorbing foot frame encircles, cup joints a center pin in the copper sheathing ring, and well spindle connection turns to the ring, turns to the ring and has cup jointed the sleeve, and the sleeve endotheca is equipped with interior axle, is equipped with the spring in the interior axle, and interior bottom is connected with oblique frame, is connected with the pulley to one side on the frame.
Description
Technical field
The utility model relates to a kind of compact conformation, stable, and take up room little, quality of integral structure is light, sensitivity and the high electronic alighting gear of aircraft of reliability.
Background technology
The Chinese Patent Application No. of utility model people earlier application: 201420591156.7, disclose a kind of Multi-axis aircraft automatic deploying and retracting alighting gear, comprise left shell and the right shell body of left and right fastening, the side of left shell and right shell body all has pilot hole and fixed orifice, a driving head is provided with between left shell and right shell body, driving head side is in " 7 " font, driving head front end has pin-and-hole, connecting pin is provided with in pin-and-hole, driving head bottom has locating notch, the axis of guide is provided with in locating notch, the left end of the axis of guide, right-hand member is arranged at left shell respectively, in the pilot hole of right shell body, driving head front end is connected with connection tube head by connecting pin.
Chinese Patent Application No.: 201380010864.5, discloses a kind of alighting gear of aircraft, and this alighting gear comprises and is connected to aircraft and the main accessory of movement between collapsed state and deployed condition and be connected to the trailing arm of this main accessory movably.Torque spring is connected to this trailing arm, makes the movement of this trailing arm that this torque spring can be made to produce torque load.This torque spring is included in and keeps in assembly, this maintenance assembly has the first state and the second state, in this first state, this torque spring is set to react on its axial load, this main accessory is so made to remain on this deployed condition, in this second state, this torque spring is configured such that this main accessory moves between this collapsed state and this deployed condition.
Above-mentioned utility model creates complex structure, control accuracy and effectiveness in vibration suppression poor.
Utility model content
The purpose of this utility model is, overcomes the above-mentioned defect of prior art, provides a kind of compact conformation, stable, and take up room little, quality of integral structure is light, sensitivity and the high electronic alighting gear of aircraft of reliability.
For achieving the above object, the technical scheme that the utility model provides is as follows: the electronic alighting gear of a kind of aircraft, comprise driver train, damping foot rest and pulley, driver train comprises main cartridge, be semienclosed inner chamber in main cartridge, the top of inner chamber is provided with actuating mechanism storage tank, a screw mandrel is provided with in actuating mechanism storage tank, the bottom of screw mandrel is provided with bolt cap, screw mandrel is arranged with stroke nut, the top of screw mandrel is arranged with the first thrust ball bearing with flat seat, the bottom of inner chamber is provided with actuating unit storage tank, a motor is provided with in actuating unit storage tank, the output shaft of motor is connected with drop-gear box, the output shaft of drop-gear box is connected with the second thrust ball bearing with flat seat, bolt cap is sheathed in the second thrust ball bearing with flat seat, stroke nut is connected with Connection Block, Connection Block is located at the left side wall of main cartridge, between the axis hole that right side wall is offered, damping foot rest is connected to Connection Block bottom, damping foot rest comprises the copper sheathing ring being sheathed on Connection Block bottom, a center shaft is socketed in copper sheathing ring, center shaft is connected with steering ring, steering ring is socketed with sleeve, is arranged with interior axle in sleeve, and interior axle has puts cavity volume, put in cavity volume and be provided with spring, this spring extends the top of putting cavity volume and interior axle, and interior axle bottom is connected with oblique frame, and oblique frame is connected with pulley.
The screw of stroke nut is sheathed on screw mandrel, and the left part of stroke nut, right part are respectively left limit axle, right limit axle, left limit axle, right limit axle be set in respectively main cartridge is offered the first spacing hole, in the second spacing hole.
One end of Connection Block is left limit portion in claw-like, right limit portion, left limit portion is sheathed on the left limit axle of stroke nut, right limit portion is sheathed on the right limit axle of stroke nut, left fixed shaft, right fixed shaft is respectively equipped with below the left limit portion of the left side of Connection Block, below the right limit portion of right side, left fixed shaft, right fixed shaft be set in respectively be arranged at main cartridge left axle sleeve, on right axle sleeve, left axle sleeve, right axle sleeve are located in the axis hole of main cartridge respectively.
Main cartridge is made up of left box body and right box body, and the first spacing hole is located on left box body, and the second spacing hole is located on right box body, and left box body and right box body all have axis hole, and left axle sleeve is located in the axis hole of left box body, and right axle sleeve is located in the axis hole of right box body.
Oil sealing is provided with between sleeve and interior axle, this oil-sealing sleeve is located on interior axle, the bottom of interior axle is provided with the first public coupling link, screw is had on sleeve top, in screw, arrange machine-processed rice screw is fixed in sleeve by interior axle, steering ring is sheathed on the periphery on the top of sleeve, and the bottom of sleeve is provided with the second public coupling link.
Oblique frame one end is provided with bending frame, the other end is provided with axle block, bending frame is connected with oblique frame by socket bolt, bending frame is provided with female coupling link, oblique frame is also provided with oblique seat, first public coupling link of interior axle and oblique seat are connected, and it is fastening by socket bolt, second male coupling link of sleeve and female coupling link of bending frame are connected, and it is fastening by socket bolt, pulley is connected to axle block side, pulley is connected with the axle block on oblique frame by a wheel shaft, and the link slot offered by machine-processed rice screw abutting wheel shaft close end is fastening.
Be provided with steering wheel fixed plate between Connection Block and sleeve, steering wheel fixed plate is provided with steering wheel, and steering wheel is provided with half arm rudder plate, between half arm rudder plate and steering ring, be connected with stepped iron wire.
Usefulness of the present utility model is: underspeeded through drop-gear box by electric machine rotation, increase torsion, drop-gear box connection wire rod is rotated, and screw mandrel drives stroke nut to move around, damping foot rest is followed it with Connection Block and is moved on stroke nut, reaches the effect that alighting gear is opened and drawn in; Driven the rotation of steering ring by the rotation of half arm rudder plate of steering wheel, thus reach steering-effecting; Compact conformation, operating accuracy is high, and opening of alighting gear runs steadily smooth and easy with gathering action, and practicality and load-carrying capacity are strong, integral structure take up room little, quality light, sensitivity and reliability high, applied range.
Accompanying drawing explanation
Fig. 1 is the block diagram of the electronic alighting gear embodiment one of aircraft described in the utility model;
Fig. 2 is the exploded view of the electronic alighting gear embodiment one of aircraft described in the utility model;
Fig. 3 is the section-drawing of the electronic alighting gear embodiment one of aircraft described in the utility model;
Fig. 4 is the partial exploded view of the electronic alighting gear embodiment one of aircraft described in the utility model;
Fig. 5 is the block diagram of the electronic alighting gear embodiment two of aircraft described in the utility model;
Fig. 6 is the section-drawing of the electronic alighting gear embodiment two of aircraft described in the utility model;
Fig. 7 is the driver train exploded view described in the electronic alighting gear embodiment two of aircraft described in the utility model;
Fig. 8 is the pulley exploded view described in the electronic alighting gear embodiment two of aircraft described in the utility model.
Detailed description of the invention
Be further described with regard to the technical solution of the utility model below in conjunction with accompanying drawing and preferred embodiment.
As Figure 1-Figure 4, the electronic alighting gear embodiment one of a kind of aircraft described in the utility model, comprise steering wheel 46, driver train 100, damping foot rest 200 and pulley 300, driver train 100 comprises the left box body 28 covered mutually, right box body 27, left box body 28, semienclosed inner chamber 101 is formed in inside after right box body 27 covers mutually, the top of inner chamber 101 is provided with actuating mechanism storage tank 51, a screw mandrel 36 is provided with in actuating mechanism storage tank 51, the bottom of screw mandrel 36 is provided with bolt cap 361, screw mandrel 36 is arranged with stroke nut 37, the top of screw mandrel 36 is arranged with the first thrust ball bearing with flat seat 39, the bottom of inner chamber 101 is provided with actuating unit storage tank 52, a motor 32 is provided with in actuating unit storage tank 52, the output shaft of motor 32 is connected with drop-gear box 34, the output shaft of drop-gear box 34 is connected with the second thrust ball bearing with flat seat 38, bolt cap 361 is sheathed in the second thrust ball bearing with flat seat 38, stroke nut 37 is connected with Connection Block 40, Connection Block 40 is located at left box body 28, between the axis hole (accompanying drawing does not mark) that right box body 27 is offered.
Concrete, the screw of stroke nut 37 is sheathed on screw mandrel 36, the left part of stroke nut 37, right part are respectively left limit axle (accompanying drawing does not mark), right limit axle (accompanying drawing does not mark), left limit axle, right limit axle are set in the first spacing hole 271 of spacing hole 281, second that left box body 28, right box body 27 are offered respectively, stroke nut 37 in working order time can do round straight-line motion in the first spacing hole 271 of spacing hole 281, second.
Concrete, one end of Connection Block 40 is the left limit portion 401 in claw-like, right limit portion 402, left limit portion 401 is sheathed on the left limit axle of stroke nut 37, right limit portion cover 402 is located on the right limit axle of stroke nut 37, below the left limit portion 401 of the left side of Connection Block 40, left fixed shaft (accompanying drawing does not mark) is respectively equipped with below the right limit portion 402 of right side, right fixed shaft (accompanying drawing does not mark), left fixed shaft, right fixed shaft is set in the left axle sleeve 291 be arranged on left box body 28 respectively, on right axle sleeve 29 on right box body 27, left axle sleeve 291, right axle sleeve 29 is located at left box body 28 respectively, in the axis hole of right box body 27.
Further, damping foot rest 200 is connected to Connection Block 40 bottom, damping foot rest 200 comprises the copper sheathing ring 23 being sheathed on Connection Block 40 bottom, copper sheathing ring 23 top is the threaded connector of tool (accompanying drawing does not mark), connector is arranged with jump ring 24, a center shaft 21 is socketed in copper sheathing ring 23, center shaft 21 is connected with steering ring 25, packing ring 22 is provided with between center shaft 21 and steering ring 25, steering ring 25 is socketed with sleeve 17, interior axle 15 is arranged with in sleeve 17, interior axle 15 has puts cavity volume (accompanying drawing does not mark), put in cavity volume and be provided with spring 16, this spring 16 extends the top of putting cavity volume and interior axle 15, interior axle 15 bottom is connected with oblique frame 8, oblique frame 8 is connected with pulley 300.
Concrete, oil sealing 18 is provided with between sleeve 17 and interior axle 15, this oil sealing 18 is sheathed on interior axle 15, the bottom of interior axle 15 is provided with the first public coupling link 151, screw (accompanying drawing does not mark) is had on sleeve 17 top, in screw, arrange one group of sleeve machine-processed rice screw 171 is fixed in sleeve 17 by interior axle 15, and steering ring 25 is sheathed on the periphery on the top of sleeve 17, and the bottom of sleeve 17 is provided with the second public coupling link 152.
Concrete, oblique frame 8 one end is provided with bending frame 11, the other end is provided with axle block 811, bending frame 11 is connected with oblique frame 8 by the first socket bolt 12, bending frame 11 is provided with female coupling link 111, oblique frame 8 is also provided with oblique seat 9, oblique seat 9 is fixing with on oblique frame 8 by coiled hair machine screws 10, first public coupling link 151 of interior axle 15 is connected with oblique seat 9, and it is fastening by the second socket bolt 19, second male coupling link 152 of sleeve 17 is connected with female coupling link 111 of bending frame 11, and it is fastening by the 3rd socket bolt 14, pulley 300 is connected to axle block 811 side, pulley 300 is connected with the axle block 811 on oblique frame 8 by a wheel shaft 6, and it is fastening to abut by one group of pulley machine-processed rice screw 810 link slot 61 that wheel shaft 6 close end offers.
Concrete, pulley comprises left wheel hub 3 and right wheel hub 2, left wheel hub 3 and a sheathed tire 1 on right wheel hub 2, left wheel hub 3 is fastening by some pan-headed screws 5 with right wheel hub 2, in the axle hole (accompanying drawing does not mark) of left wheel hub 3 and right wheel hub 2, be provided with deep groove ball bearing 4, wheel shaft 6 is located in deep groove ball bearing 4.
Further, steering wheel fixed plate 44 is provided with between Connection Block 40 and sleeve 17, steering wheel 46 is arranged on steering wheel fixed plate 44, and it is fastening by some chiastron pad machine tooth screws 47, half arm rudder plate 48 is also provided with in steering wheel 46, half arm rudder plate 48 is anchored on steering wheel fixed plate 44 by crossed pan head machine screws 49, between half arm rudder plate 48 and steering ring 25, be connected with stepped iron wire 50.
Above, motor 32 rotates and underspeeds through drop-gear box 34, increase torsion, drop-gear box 34 connection wire rod 36 is rotated, screw mandrel 36 drives stroke nut 37 to move around, and damping foot rest 200 is followed it with Connection Block 40 and moved on stroke nut 37, reaches the effect that alighting gear is opened and drawn in, half arm rudder plate 48 of steering wheel 46 rotate through stepped iron wire 50 to drive the rotation of steering ring 25, thus reach steering-effecting.
As viewed in figures 5-8, the electronic alighting gear embodiment two of a kind of aircraft described in the utility model, comprise driver train 400, damping foot rest 200 and pulley 500, driver train 400 comprises main cartridge 71, it is semienclosed inner chamber (accompanying drawing does not mark) in main cartridge 71, the top of inner chamber is provided with actuating mechanism storage tank (accompanying drawing does not mark), a screw mandrel 36 is provided with in actuating mechanism storage tank (accompanying drawing does not mark), the bottom of screw mandrel 36 is provided with bolt cap 361, bolt cap 361 is socketed with the second thrust ball bearing with flat seat 38, screw mandrel 36 is arranged with stroke nut 37, the top of screw mandrel 36 is arranged with nut 72, steel ball 73 is provided with in nut 72, the bottom of inner chamber is provided with actuating unit storage tank (accompanying drawing does not mark), a motor 32 is provided with in actuating unit storage tank, the output shaft of motor 32 is connected with drop-gear box 34, the output shaft of drop-gear box 34 is connected with thrust ball bearing with flat seat 74, drop-gear box 34 and motor 32 are sheathed on the motor front cabinet 75 that covers mutually with in motor back box 76, crossed countersunk head screw 77 is provided with between motor front cabinet 75 and drop-gear box 34, this crossed countersunk head screw 77 is fixed on the front end of drop-gear box 34, line cover 70 is provided with in the rear end of motor back box 75, stroke nut 37 is connected with Connection Block 40, Connection Block 40 is located at by a rotating shaft 78 on axis hole (accompanying drawing does not mark) that the left side wall of main cartridge, right side wall are offered, and be arranged with axle sleeve 79 in axis hole, two close ends of rotating shaft 78 are located on axle sleeve 79, damping foot rest 200 is connected to Connection Block 40 bottom, damping foot rest 200 is connected with pulley 500, pulley 500 comprises the left wheel hub 81 of left and right connection and right wheel hub 82, round iron dish 83, magnet ring 84, ring gear disk 85 and ring gear cover 86 is provided with from right to left successively in right wheel hub 82, the housing of right wheel hub 82 is provided with tire 87, deep groove ball bearing 88 is equipped with in the axle hole of left wheel hub 81 and right wheel hub 82, by a wheel shaft 89, left wheel hub 81 is connected with right wheel hub 82 again, and is locked by some pan-headed screws 80 and locking countersunk head screw 801.
Above, rotated by motor 32 and underspeed through drop-gear box 34, increase torsion, drop-gear box 34 connection wire rod 36 is rotated, and screw mandrel 36 drives stroke nut 37 to move around, and damping foot rest 200 is followed it with Connection Block 40 and moved on stroke nut 37, reach the effect that alighting gear is opened and drawn in, magnet ring 84 produces magnetic field after being energized, and holds round iron dish 83, thus plays braking action.
Above-described is only principle of the present utility model and preferred embodiment.It should be pointed out that to those skilled in the art, under the prerequisite not departing from the utility model principle, some modification and improvement can also be made, also should be considered as belonging to protection domain of the present utility model.
Claims (7)
1. the electronic alighting gear of aircraft, comprise driver train, damping foot rest and pulley, it is characterized in that: described driver train comprises main cartridge, be semienclosed inner chamber in main cartridge, the top of inner chamber is provided with actuating mechanism storage tank, a screw mandrel is provided with in actuating mechanism storage tank, the bottom of screw mandrel is provided with bolt cap, screw mandrel is arranged with stroke nut, the top of screw mandrel is arranged with the first thrust ball bearing with flat seat, the bottom of inner chamber is provided with actuating unit storage tank, a motor is provided with in actuating unit storage tank, the output shaft of motor is connected with drop-gear box, the output shaft of drop-gear box is connected with the second thrust ball bearing with flat seat, bolt cap is sheathed in the second thrust ball bearing with flat seat, stroke nut is connected with Connection Block, Connection Block is located at the left side wall of main cartridge, between the axis hole that right side wall is offered, damping foot rest is connected to Connection Block bottom, damping foot rest comprises the copper sheathing ring being sheathed on Connection Block bottom, a center shaft is socketed in copper sheathing ring, center shaft is connected with steering ring, steering ring is socketed with sleeve, is arranged with interior axle in sleeve, and interior axle has puts cavity volume, put in cavity volume and be provided with spring, this spring extends the top of putting cavity volume and interior axle, and interior axle bottom is connected with oblique frame, and oblique frame is connected with pulley.
2. the electronic alighting gear of aircraft according to claim 1, it is characterized in that: the screw of described stroke nut is sheathed on screw mandrel, the left part of stroke nut, right part are respectively left limit axle, right limit axle, left limit axle, right limit axle be set in respectively main cartridge is offered the first spacing hole, in the second spacing hole.
3. the electronic alighting gear of aircraft according to claim 1 and 2, it is characterized in that: one end of described Connection Block is the left limit portion in claw-like, right limit portion, left limit portion is sheathed on the left limit axle of stroke nut, right limit portion is sheathed on the right limit axle of stroke nut, below the left limit portion of the left side of Connection Block, left fixed shaft is respectively equipped with below the right limit portion of right side, right fixed shaft, left fixed shaft, right fixed shaft is set in the left axle sleeve being arranged at main cartridge respectively, on right axle sleeve, left axle sleeve, right axle sleeve is located in the axis hole of main cartridge respectively.
4. the electronic alighting gear of aircraft according to claim 3, it is characterized in that: described main cartridge is made up of left box body and right box body, first spacing hole is located on left box body, second spacing hole is located on right box body, left box body and right box body all have axis hole, left axle sleeve is located in the axis hole of left box body, and right axle sleeve is located in the axis hole of right box body.
5. the electronic alighting gear of aircraft according to claim 1, it is characterized in that: between described sleeve and interior axle, be provided with oil sealing, this oil-sealing sleeve is located on interior axle, the bottom of interior axle is provided with the first public coupling link, screw is had on sleeve top, in screw, arrange machine-processed rice screw is fixed in sleeve by interior axle, and steering ring is sheathed on the periphery on the top of sleeve, and the bottom of sleeve is provided with the second public coupling link.
6. the electronic alighting gear of aircraft according to claim 1 or 5, it is characterized in that: described oblique frame one end is provided with bending frame, the other end is provided with axle block, bending frame is connected with oblique frame by socket bolt, bending frame is provided with female coupling link, oblique frame is also provided with oblique seat, first public coupling link of interior axle and oblique seat are connected, and it is fastening by socket bolt, second male coupling link of sleeve and female coupling link of bending frame are connected, and it is fastening by socket bolt, pulley is connected to axle block side, pulley is connected with the axle block on oblique frame by a wheel shaft, and it is fastening to abut by machine-processed rice screw the link slot that wheel shaft close end offers.
7. the electronic alighting gear of aircraft according to claim 1, it is characterized in that: between described Connection Block and sleeve, be provided with steering wheel fixed plate, steering wheel fixed plate is provided with steering wheel, and steering wheel is provided with half arm rudder plate, between half arm rudder plate and steering ring, be connected with stepped iron wire.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520342232.5U CN204871593U (en) | 2015-05-25 | 2015-05-25 | Electronic undercarriage of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520342232.5U CN204871593U (en) | 2015-05-25 | 2015-05-25 | Electronic undercarriage of aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204871593U true CN204871593U (en) | 2015-12-16 |
Family
ID=54815998
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520342232.5U Expired - Fee Related CN204871593U (en) | 2015-05-25 | 2015-05-25 | Electronic undercarriage of aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204871593U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105818967A (en) * | 2016-05-19 | 2016-08-03 | 安翔泰岳（镇江）航空科技有限公司 | Undercarriage lifting device |
| CN106143881A (en) * | 2016-07-29 | 2016-11-23 | 江西核工业测绘院 | A kind of unmanned plane deceleration damping undercarriage |
| CN106882362A (en) * | 2017-03-10 | 2017-06-23 | 佛山市神风航空科技有限公司 | A kind of undercarriage that can be flown and its working method |
| CN108820191A (en) * | 2018-07-20 | 2018-11-16 | 中国科学院工程热物理研究所 | Undercarriage cushioning structure and undercarriage near space solar energy unmanned plane |
| CN109107188A (en) * | 2018-09-21 | 2019-01-01 | 德施普科技发展温州有限公司 | A kind of undercarriage for the model of an airplane |
-
2015
- 2015-05-25 CN CN201520342232.5U patent/CN204871593U/en not_active Expired - Fee Related
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105818967A (en) * | 2016-05-19 | 2016-08-03 | 安翔泰岳（镇江）航空科技有限公司 | Undercarriage lifting device |
| CN106143881A (en) * | 2016-07-29 | 2016-11-23 | 江西核工业测绘院 | A kind of unmanned plane deceleration damping undercarriage |
| CN106143881B (en) * | 2016-07-29 | 2018-09-14 | 江西核工业测绘院 | A kind of unmanned plane deceleration damping undercarriage |
| CN106882362A (en) * | 2017-03-10 | 2017-06-23 | 佛山市神风航空科技有限公司 | A kind of undercarriage that can be flown and its working method |
| CN108820191A (en) * | 2018-07-20 | 2018-11-16 | 中国科学院工程热物理研究所 | Undercarriage cushioning structure and undercarriage near space solar energy unmanned plane |
| CN108820191B (en) * | 2018-07-20 | 2024-05-07 | 中国科学院工程热物理研究所 | Landing gear shock absorption structure for solar unmanned aerial vehicle in near space and landing gear |
| CN109107188A (en) * | 2018-09-21 | 2019-01-01 | 德施普科技发展温州有限公司 | A kind of undercarriage for the model of an airplane |
| CN109107188B (en) * | 2018-09-21 | 2020-11-24 | 五河县纬立农业科技有限公司 | Undercarriage for model airplane |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN204871593U (en) | Electronic undercarriage of aircraft | |
| CN106737825B (en) | A kind of shock resistance flexible joint suitable for mechanical arm | |
| CN107104544B (en) | A kind of integrated electromechanical servo acting device of high power to weight ratio | |
| CN104196929B (en) | Worm and inclined-worm-gear-disc type electronic parking brake | |
| CN105946451B (en) | Omni-mobile platform and its steering wheel and driving wheel | |
| JP2012511465A (en) | Especially steering device for rear wheel steering system | |
| CN204871590U (en) | Multiaxis undercarriage | |
| CN113650466A (en) | Automatic vehicle height adjusting device | |
| CN109572977B (en) | Oil lubrication electric steering engine with position locking function | |
| CN207382117U (en) | A kind of fast disassembly type wheel hub motor | |
| CN203420533U (en) | Clutch control device for door lock | |
| CN207015153U (en) | A kind of driving wheel and Segway Human Transporter | |
| CN107902004A (en) | Two-wheeled self-balancing transformable robot | |
| CN209972427U (en) | Vehicle electronic parking braking power device and vehicle electronic parking braking system | |
| CN207770235U (en) | A kind of mobile phone key glue-dropping tool easy to operation | |
| CN107425635A (en) | Integral type brake motor | |
| KR101452438B1 (en) | joint drive device for robot | |
| CN105961366A (en) | Garden weeding robot | |
| CN208117837U (en) | A kind of human synovial power assisting device | |
| CN105667488A (en) | Auxiliary installation device of automobile wheel speed sensor | |
| CN208881899U (en) | A kind of knuckle of automobile steering roller, transfer and automobile | |
| CN113043303A (en) | Underwater manipulator paw driving device capable of realizing compound motion | |
| CN207683332U (en) | Motor rear axle drives buffer with motor | |
| CN201808051U (en) | Power output mechanism for electric power tool | |
| CN205417602U (en) | Supplementary installation device of fast sensor of car wheel |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20151216 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |