CN207943165U - A kind of unmanned vehicle and its ascending, descending frame - Google Patents
A kind of unmanned vehicle and its ascending, descending frame Download PDFInfo
- Publication number
- CN207943165U CN207943165U CN201721415959.7U CN201721415959U CN207943165U CN 207943165 U CN207943165 U CN 207943165U CN 201721415959 U CN201721415959 U CN 201721415959U CN 207943165 U CN207943165 U CN 207943165U
- Authority
- CN
- China
- Prior art keywords
- ascending
- wing plate
- landing gear
- descending frame
- unmanned vehicle
- 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
- 230000001174 ascending effect Effects 0.000 title claims abstract description 52
- 239000003381 stabilizer Substances 0.000 claims description 6
- 238000004064 recycling Methods 0.000 claims description 5
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 4
- 229910052799 carbon Inorganic materials 0.000 claims description 4
- 239000000835 fiber Substances 0.000 claims description 4
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 2
- 239000004917 carbon fiber Substances 0.000 claims description 2
- 230000009187 flying Effects 0.000 claims description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 2
- 230000000694 effects Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000010276 construction Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/10—Wings
- B64U30/12—Variable or detachable wings, e.g. wings with adjustable sweep
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/12—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/66—Convertible alighting gear; Combinations of different kinds of ground or like engaging elements
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Handcart (AREA)
- Toys (AREA)
Abstract
The utility model is related to a kind of ascending, descending framves of unmanned vehicle, landing gear including wing plate and for being contacted with ground, one end of the wing plate is connected with the landing gear, the other end with aircraft body for being connected, when the ascending, descending frame rises, the wing plate is used to improve the lift of aircraft as fixed-wing.The unmanned vehicle undercarriage can promote aircraft cruise economy；Entire unmanned vehicle can also be made compact-sized simultaneously, weight is kept low.The utility model further relates to a kind of unmanned vehicle using above-mentioned unmanned vehicle undercarriage.
Description
Technical field
The utility model is related to unmanned vehicle technical field, more particularly to a kind of unmanned vehicle and unmanned vehicle
Ascending, descending frame.
Background technology
The lift and drag characteristic of fixed-wing are that efficiency is highest in current unmanned vehicle, best cruising condition lower aerofoil
Several times of even decades of times, the typical full machine lift resistance ratios of small-sized Fixed Wing AirVehicle that the lift of generation can reach resistance can reach 7
~20；Therefore, for current more rotors or other VTOL (vertical take-off and landing, VTOL)
For unmanned vehicle, it is exactly to increase fixed wing to improve one of cruise economy the most effective means.
But the overall dimensions of aircraft can not only be significantly increased by increasing fixed wing directly in aircraft body, and
And the overall weight of aircraft body can be also obviously increased, the problem for causing the loading coefficient of aircraft smaller occurs.
Utility model content
In order to effectively improve the cruise of aircraft under the premise of not significantly increasing unmanned vehicle size and weight
Economy, the utility model provide a kind of ascending, descending frame of unmanned vehicle, including wing plate and for being contacted with ground
Landing gear, one end of the wing plate are connected with the landing gear, and the other end works as institute for being connected with aircraft body
When stating the rise of ascending, descending frame, the wing plate is used to improve the lift of aircraft as fixed-wing.
Preferably, one end of the wing plate is directly connected with the landing gear.
Preferably, the other end of the wing plate is provided with rotating junction, for being rotationally connected with the aircraft body
On.
Preferably, the ascending, descending frame further includes landing gear leg, one end of the landing gear leg directly with it is described
Landing gear is connected, and the wing plate is set on the landing gear leg.
Preferably, the other end of the landing gear leg is provided with rotating junction, for being rotationally connected with the flight
In device main body.
Preferably, the landing gear leg is carbon fibre member bar.
Preferably, the landing gear is the longitudinally disposed rod piece for being parallel to the aircraft body.
Preferably, the axis of the plane where the wing chord of the wing plate and the landing gear has default angle.
Preferably, the landing gear is fixedly connected with the landing gear leg；Or the landing gear is foldable
It is connected on the landing gear leg, when aircraft is stored, the landing gear is foldable to and the landing gear leg
Parallel position.
Preferably, the wing plate of carbon fiber by being made.
Preferably, further include the lift trimmer being rotatably arranged on the wing plate.
Preferably, the inside of the wing plate is hollow-core construction.
The utility model additionally provides a kind of unmanned vehicle, including aircraft body and setting in the aircraft body
On at least a pair of of ascending, descending frame, which is the ascending, descending frame disclosed in above-mentioned any one, described
When ascending, descending frame is in raised configuration, the wing plate is in running order；When the ascending, descending frame is in landing state,
The wing plate is in recycling state.
Preferably, the unmanned vehicle is multi-rotor aerocraft.
It as can be seen from the above technical solutions, will in the ascending, descending frame of unmanned vehicle disclosed in the utility model
Undercarriage is combined into one with the wing plate for playing lift-rising and is designed, and undercarriage not only has the routine risen and fallen for aircraft
Function, and when aircraft is cruised, undercarriage also has the function of that lift-rising wing plate, unmanned vehicle at this time can be by imitating
The higher wing plate of rate provides part or all of lift, to promote aircraft cruise economy；Wing plate setting is risen in aircraft
It falls on frame, the separately installed lift-rising wing in conventional design can be saved and lift is transmitted to the structure of fuselage, therefore compared to
It is arranged for the traditional approach of the lift-rising wing directly in aircraft body, the utility model not only makes entire unmanned flight
Device is compact-sized, but also the weight of entire unmanned vehicle is made to be kept low.
Unmanned vehicle disclosed in the utility model, as a result of above-mentioned ascending, descending frame, therefore nobody fly this
The ascending, descending frame of row device not only has the conventional func risen and fallen for aircraft, but also cruises in unmanned vehicle
When, undercarriage also has the function of that lift-rising wing plate, unmanned vehicle can be provided part or complete by more efficient wing plate at this time
Portion's lift, to promote aircraft cruise economy；Entire unmanned vehicle is compact-sized simultaneously, and weight has been maintained at relatively low water
It is flat.
Description of the drawings
Fig. 1 is structural schematic diagram of the aircraft disclosed in an embodiment of the present invention when landing；
Fig. 2 is structural schematic diagram of the aircraft disclosed in an embodiment of the present invention in flight.
Wherein, 1 is aircraft body, and 21 be landing gear leg, and 22 be landing gear, and 3 be wing plate, and 4 be horn, and 5 are
Motor.
Specific implementation mode
One of core of the utility model is to provide a kind of ascending, descending frame of unmanned vehicle, not significantly increase
Under the premise of aircraft size and weight, the cruise economy of aircraft is effectively improved.
Another core of the utility model is to provide a kind of unmanned vehicle using above-mentioned ascending, descending frame.
The ascending, descending frame of unmanned vehicle disclosed in an embodiment of the present invention, including wing plate 3 and undercarriage branch
Foot 22, the effect of wherein landing gear 22 are that support aircraft, one end of wing plate 3 and undercarriage are contacted and stablized with ground
Stabilizer blade 22 is connected, and for being connected with aircraft body 1, there is undercarriage the other end raised configuration and landing state, undercarriage to exist
When raised configuration, unmanned vehicle is in normal flight operations, and when landing state, unmanned vehicle will land undercarriage
Or completed to land, in the present embodiment, when ascending, descending frame rises, wing plate 3 flies as fixed-wing for improving
The lift of device.
It can be found that in the above-described embodiments, undercarriage is combined into one with the wing plate 3 for playing lift-rising, and undercarriage is not only
With the conventional func risen and fallen for aircraft, and when unmanned vehicle is cruised, undercarriage also has the lift-rising wing
The function of plate 3, unmanned vehicle can provide part or all of lift by more efficient wing plate 3 at this time, to promote nobody
Aircraft cruise economy；By wing plate 3 be arranged on aircraft landing gear, not only can keep aircraft VTOL and
It hovers function, and the separately installed lift-rising wing in conventional design can be saved and lift is transmitted to the structure of fuselage, therefore
For the traditional approach of the lift-rising wing is arranged directly in aircraft body 1, the utility model not only makes entirely
Unmanned vehicle is compact-sized, but also the weight of entire unmanned vehicle is made to be kept low.
In order to make those skilled in the art more fully understand the utility model, below in conjunction with the accompanying drawings and it is embodied
The utility model is described in further detail for mode.
It please refers to Fig.1 and Fig. 2, in a kind of embodiment of the utility model, ascending, descending frame is in addition to wing plate 3 and rises and falls
Further include landing gear leg 21 outside frame stabilizer blade 22, one end of landing gear leg 21 is directly connected with landing gear 22, and wing plate 3 is set
It sets on landing gear leg 21, the wing plate 3 in the embodiment is indirectly coupled to undercarriage essentially by landing gear leg 21
On stabilizer blade 22, landing gear leg 21 is located at wing plate 3 and lifts immediate vicinity, when the state of ascending, descending frame changes, undercarriage
Supporting leg 21 drives wing plate 3 to act, to realize opening and the recycling of wing plate 3, referring to FIG. 1, when ascending, descending frame is in landing
When state, wing plate 3 is not playing the effect for increasing lift just at recycling state, at this time wing plate 3；Referring to FIG. 2, when lifting
When undercarriage is in raised configuration, unmanned vehicle is in regular flight condition or cruising condition at this time, wing plate 3 just at
Opening state, wing plate 3 play the effect for increasing aircraft lift, the lift and drag characteristic of fixed-wing at this time so that using should
The cruise economy of the aircraft of wing plate 3 significantly improves.
Connection type between landing gear leg 21 and landing gear 22 is not limited to one kind, for example, landing gear leg 21 with
May be used flexible connection or the mode that is fixedly connected between landing gear 22, flexible connection can be bolted or
The modes such as person is hinged are realized, are fixedly connected may be used and be realized including the mode in welding and being bonded in.
When being connected using articulated manner between landing gear leg 21 and landing gear 22, landing gear 22 can also be into
One step is designed as folding mode, and when unmanned vehicle is stored, landing gear 22 can rotate to and landing gear leg 21
On parallel position, to effectively reduce the size of entire aircraft, facility is provided to store or transporting；When unmanned vehicle needs
When being worked, it is only necessary to rotate landing gear 22 to operating position, more preferably mode is landing gear leg
Position lockable mechanism is additionally provided between 21 and landing gear 22, which can be by being arranged in undercarriage branch
The lock pin of leg 21 and landing gear 22 on any one, and the locking hole being arranged in other one are constituted.
One end that landing gear leg 21 is used to be connected with aircraft body 1 is provided with rotating junction, the rotating junction
Can be rotation axis, correspondingly, being provided with the axis hole being adapted to the rotation axis in aircraft body 1；Certainly, the rotating junction
May be axis hole, correspondingly, being provided with rotation axis corresponding with the axis hole in aircraft body 1.
In order to improve the course continuation mileage of unmanned vehicle, need effectively to reduce under the premise of ensureing ascending, descending frame intensity
The weight of ascending, descending frame, for this purpose, the landing gear leg 21 in the present embodiment is carbon fibre member bar, certainly, landing gear 22
And wing plate 3 also contemplates for being made of carbon fibre material, wing plate 3 can also use hollow-core construction, this can be further decreased
The weight of undercarriage.
It please refers to Fig.1 and Fig. 2, landing gear 22 is specially to be parallel to the longitudinally disposed rod piece of aircraft body 1, wing plate
There is default angle, to ensure to rise in ascending, descending frame between plane where 3 wing chord and the axis of landing gear 22
When, wing plate 3 can reach best angle.Need to illustrate, default angle can according to the specific size of unmanned vehicle,
State after the expansion of ascending, descending frame carries out adaptability design, according to actual conditions difference, presets the actual angle of angle not
Uniquely.
In another embodiment of the utility model, one end of wing plate 3 is directly connected with landing gear 22, wing plate 3 in addition to
Except the fixed-wing for improving aircraft lift, the supporting leg of ascending, descending frame is also also served as, in order to make wing plate 3 be rotatably coupled
In aircraft body 1, one end that wing plate 3 is used to be connected with unmanned vehicle is additionally provided with rotating junction, similarly, the rotation
Interconnecting piece can be rotation axis, correspondingly, being provided with the axis hole being adapted to the rotation axis in aircraft body 1；Certainly, the rotation
Interconnecting piece may be axis hole, correspondingly, being provided with rotation axis corresponding with the axis hole in aircraft body 1.
Further, lift trimmer is additionally provided on wing plate 3, lift trimmer is spindle rotationally arranged on wing plate 3,
The lift and pitching moment of wing plate 3 are adjusted with auxiliary.
In addition to this, a kind of unmanned vehicle is also disclosed in the utility model embodiment, which includes flying
Row device main body 1 and at least a pair of of the ascending, descending frame being arranged in aircraft body 1, ascending, descending frame is above-mentioned any one implementation
The ascending, descending frame of unmanned vehicle disclosed in example, ascending, descending frame are driven by steering engine or other driving devices,
For the ascending, descending frame when in raised configuration, wing plate 3 is in running order as fixed-wing, which is in landing
When state, wing plate 3 is in recycling state.The unmanned vehicle includes but not limited to multi-rotor aerocraft, such as institute in Fig. 1 and Fig. 2
The unmanned vehicle shown is quadrotor, and the motor 5 being used to provide power is mounted on by horn 4 in aircraft body 1.
Unmanned vehicle in above-described embodiment, as a result of above-mentioned ascending, descending frame, therefore the unmanned vehicle
Ascending, descending frame not only has the conventional func risen and fallen for aircraft, but also when aircraft is cruised, undercarriage is also
Have the function of that lift-rising wing plate 3, unmanned vehicle can provide part or all of lift by more efficient wing plate 3 at this time, from
And promote aircraft cruise economy；Entire unmanned vehicle is compact-sized simultaneously, and weight has been maintained at reduced levels.
The ascending, descending frame of unmanned vehicle provided by the utility model and unmanned vehicle has been carried out in detail above
It introduces.Specific case used herein is expounded the principles of the present invention and embodiment, above example
Illustrate the method and its core concept for being merely used to help understand the utility model.It should be pointed out that for the general of the art
For logical technical staff, without departing from the principle of this utility model, several improvement can also be carried out to the utility model
And modification, modifications and modifications also fall within the protection scope of the claims of the utility model.
Claims (14)
1. a kind of ascending, descending frame of unmanned vehicle, which is characterized in that the undercarriage including wing plate and for being contacted with ground
Stabilizer blade, one end of the wing plate are connected with the landing gear, and the other end with aircraft body for being connected, when the lifting
When wheels-up, the wing plate is used to improve the lift of aircraft as fixed-wing.
2. ascending, descending frame according to claim 1, which is characterized in that one end of the wing plate directly with the undercarriage
Stabilizer blade is connected.
3. ascending, descending frame according to claim 2, which is characterized in that the other end of the wing plate is provided with rotation connection
Portion, for being rotationally connected with the aircraft body.
4. ascending, descending frame according to claim 1, which is characterized in that the ascending, descending frame further includes undercarriage branch
One end of leg, the landing gear leg is directly connected with the landing gear, and the wing plate is set to the undercarriage branch
On leg.
5. ascending, descending frame according to claim 4, which is characterized in that the other end of the landing gear leg, which is provided with, to be turned
Rotation connection, for being rotationally connected with the aircraft body.
6. ascending, descending frame according to claim 4, which is characterized in that the landing gear leg is carbon fibre member bar.
7. ascending, descending frame according to claim 1, which is characterized in that the landing gear is to be parallel to the flight
The longitudinally disposed rod piece of device main body.
8. ascending, descending frame according to claim 7, which is characterized in that plane where the wing chord of the wing plate with it is described
The axis of landing gear has default angle.
9. ascending, descending frame according to claim 4, which is characterized in that the landing gear and the landing gear leg
It is fixedly connected；Or the landing gear is foldable is connected on the landing gear leg, it is described to rise and fall when aircraft is stored
Frame stabilizer blade is foldable to the position parallel with the landing gear leg.
10. ascending, descending frame according to claim 1, which is characterized in that the wing plate of carbon fiber by being made.
11. according to the ascending, descending frame described in claim 1-10 any one, which is characterized in that further include rotatably arranged with
Lift trimmer on the wing plate.
12. according to the ascending, descending frame described in claim 1-10 any one, which is characterized in that the inside of the wing plate is sky
Core structure.
13. a kind of unmanned vehicle, including aircraft body are lifted at least a pair being arranged in the aircraft body
Fall frame, which is characterized in that the ascending, descending frame is the ascending, descending of the aircraft as described in claim 1-12 any one
Frame, and when the ascending, descending frame is in raised configuration, the wing plate is in running order；It is in the ascending, descending frame
When landing state, the wing plate is in recycling state.
14. unmanned vehicle according to claim 13, which is characterized in that the unmanned vehicle is more rotor flyings
Device.
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721415959.7U CN207943165U (en) | 2017-10-30 | 2017-10-30 | A kind of unmanned vehicle and its ascending, descending frame |
| PCT/CN2017/114992 WO2019085148A1 (en) | 2017-10-30 | 2017-12-07 | Unmanned aerial vehicle and lifting and landing gear thereof |
| CN201780065063.7A CN110418753A (en) | 2017-10-30 | 2017-12-07 | A kind of unmanned vehicle and its ascending, descending frame |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721415959.7U CN207943165U (en) | 2017-10-30 | 2017-10-30 | A kind of unmanned vehicle and its ascending, descending frame |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207943165U true CN207943165U (en) | 2018-10-09 |
Family
ID=63703380
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721415959.7U Expired - Fee Related CN207943165U (en) | 2017-10-30 | 2017-10-30 | A kind of unmanned vehicle and its ascending, descending frame |
| CN201780065063.7A Pending CN110418753A (en) | 2017-10-30 | 2017-12-07 | A kind of unmanned vehicle and its ascending, descending frame |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201780065063.7A Pending CN110418753A (en) | 2017-10-30 | 2017-12-07 | A kind of unmanned vehicle and its ascending, descending frame |
Country Status (2)
| Country | Link |
|---|---|
| CN (2) | CN207943165U (en) |
| WO (1) | WO2019085148A1 (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109677591A (en) * | 2019-01-27 | 2019-04-26 | 陕西智翔航空科技发展有限公司 | A kind of aircraft landing gear folding and unfolding method and structure |
| CN110418753A (en) * | 2017-10-30 | 2019-11-05 | 深圳市大疆创新科技有限公司 | A kind of unmanned vehicle and its ascending, descending frame |
| EP3736213A1 (en) * | 2019-05-07 | 2020-11-11 | International Aviation Supply I.A.S. S.R.L. | Hybrid unmanned aerial vehicle |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3050385B1 (en) * | 2016-04-26 | 2018-04-06 | Airbus Helicopters | DRONE COMPRISING AT LEAST THREE ROTORS OF SUSTENTATION AND PROPULSION |
| KR102225256B1 (en) * | 2019-09-30 | 2021-03-10 | 선문대학교 산학협력단 | Drone with Variable Propulsion Units |
| JP7044413B1 (en) * | 2020-11-10 | 2022-03-30 | 株式会社石川エナジーリサーチ | Flight equipment |
| JP7029838B1 (en) | 2021-07-28 | 2022-03-04 | 株式会社Acsl | Unmanned aerial vehicle |
| JP7048131B1 (en) * | 2021-07-28 | 2022-04-05 | 株式会社Acsl | Unmanned aerial vehicle |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7137589B2 (en) * | 2005-01-28 | 2006-11-21 | Northrop Grumman Corporation | Compound helicopter with combined wings and landing struts |
| CN103754357A (en) * | 2014-01-10 | 2014-04-30 | 江苏艾锐泰克无人飞行器科技有限公司 | Horizontal pipe of undercarriage and undercarriage using same |
| CN103979105B (en) * | 2014-05-23 | 2015-11-18 | 深圳市艾特航空科技股份有限公司 | A kind of vertical takeoff and landing adjustable wing aircraft |
| CN105314105B (en) * | 2015-11-13 | 2017-07-11 | 辽宁通用航空研究院 | Can folding and unfolding wing combined type multi-rotor aerocraft |
| CN205396520U (en) * | 2015-12-31 | 2016-07-27 | 零度智控（北京）智能科技有限公司 | Undercarriage installation component , undercarriage subassembly and aircraft |
| CN106347657B (en) * | 2016-09-30 | 2019-02-19 | 扬州锐德飞科技有限公司 | A kind of unmanned plane and its working method for geography information exploration |
| CN206068138U (en) * | 2016-09-30 | 2017-04-05 | 扬州锐德飞科技有限公司 | The undercarriage of unmanned plane |
| CN106428524B (en) * | 2016-11-25 | 2019-09-13 | 南京柯尔航空科技有限公司 | A kind of multi-rotor aerocraft with the free wing |
| CN107161323B (en) * | 2017-05-19 | 2019-07-19 | 刘勇 | A kind of four axis aircraft of adjustable wing |
| CN107585300A (en) * | 2017-08-28 | 2018-01-16 | 天峋（常州）智能科技有限公司 | A kind of undercarriage has the multi-rotor unmanned aerial vehicle of lift aerofoil profile |
| CN207943165U (en) * | 2017-10-30 | 2018-10-09 | 深圳市大疆创新科技有限公司 | A kind of unmanned vehicle and its ascending, descending frame |
-
2017
- 2017-10-30 CN CN201721415959.7U patent/CN207943165U/en not_active Expired - Fee Related
- 2017-12-07 WO PCT/CN2017/114992 patent/WO2019085148A1/en active Application Filing
- 2017-12-07 CN CN201780065063.7A patent/CN110418753A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110418753A (en) * | 2017-10-30 | 2019-11-05 | 深圳市大疆创新科技有限公司 | A kind of unmanned vehicle and its ascending, descending frame |
| CN109677591A (en) * | 2019-01-27 | 2019-04-26 | 陕西智翔航空科技发展有限公司 | A kind of aircraft landing gear folding and unfolding method and structure |
| EP3736213A1 (en) * | 2019-05-07 | 2020-11-11 | International Aviation Supply I.A.S. S.R.L. | Hybrid unmanned aerial vehicle |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110418753A (en) | 2019-11-05 |
| WO2019085148A1 (en) | 2019-05-09 |
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