CN109383835A - A kind of vehicle-mounted unmanned aerial vehicle system - Google Patents
A kind of vehicle-mounted unmanned aerial vehicle system Download PDFInfo
- Publication number
- CN109383835A CN109383835A CN201710664447.2A CN201710664447A CN109383835A CN 109383835 A CN109383835 A CN 109383835A CN 201710664447 A CN201710664447 A CN 201710664447A CN 109383835 A CN109383835 A CN 109383835A
- Authority
- CN
- China
- Prior art keywords
- landing
- axis
- vehicle
- fuselage
- balance element
- 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.)
- Pending
Links
- 230000000087 stabilizing effect Effects 0.000 claims abstract description 28
- 230000006698 induction Effects 0.000 claims abstract description 27
- 238000009434 installation Methods 0.000 claims abstract description 17
- 230000005484 gravity Effects 0.000 claims description 9
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 3
- 239000002184 metal Substances 0.000 claims description 3
- 238000002347 injection Methods 0.000 claims 1
- 239000007924 injection Substances 0.000 claims 1
- 230000006641 stabilisation Effects 0.000 abstract description 5
- 238000011105 stabilization Methods 0.000 abstract description 5
- 230000037396 body weight Effects 0.000 abstract description 4
- 230000005611 electricity Effects 0.000 abstract description 4
- 238000000034 method Methods 0.000 abstract description 4
- RKTYLMNFRDHKIL-UHFFFAOYSA-N copper;5,10,15,20-tetraphenylporphyrin-22,24-diide Chemical group [Cu+2].C1=CC(C(=C2C=CC([N-]2)=C(C=2C=CC=CC=2)C=2C=CC(N=2)=C(C=2C=CC=CC=2)C2=CC=C3[N-]2)C=2C=CC=CC=2)=NC1=C3C1=CC=CC=C1 RKTYLMNFRDHKIL-UHFFFAOYSA-N 0.000 description 2
- 238000004026 adhesive bonding Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000001939 inductive effect Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000005303 weighing Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U80/00—Transport or storage specially adapted for UAVs
- B64U80/80—Transport or storage specially adapted for UAVs by vehicles
- B64U80/86—Land vehicles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
- B60L2200/00—Type of vehicles
- B60L2200/10—Air crafts
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Transportation (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of vehicle-mounted unmanned aerial vehicle systems, belong to air vehicle technique field, including vehicle-mounted unmanned aerial vehicle and take off and the force aid system that lands, it takes off and the force aid system that lands includes two taking off and the power assisting device that lands, taking off and land driving device and radio induction charging device, two take off and the both ends for the power assisting device that lands are respectively equipped with the stabilizing member that takes off and land；Vehicle-mounted unmanned aerial vehicle includes fuselage, four side axles, detachable carry axis and landing balance system, the front of fuselage is equipped with ultrasonic distance measuring module installing port, the top of fuselage is equipped with telecontrol antenna, and side axle is equipped with image capture module installing port and driving motor, and driving motor is equipped with multiple rotors.Cylinder block strength of the present invention is high, body weight is small, fuselage balance, at low cost and easy for installation, takeoff operational is simple, stabilization of taking off, and guarantees unmanned plane balance, realizes radio induction charging by radio induction charging device, guarantees unmanned plane electricity consumption.
Description
Technical field
The present invention relates to a kind of UAV system to belong to unmanned air vehicle technique more particularly to a kind of vehicle-mounted unmanned aerial vehicle system
Field.
Background technique
Unmanned plane is using the not manned aircraft of radio robot and the presetting apparatus provided for oneself manipulation, extensively
Be applied to dual-use field, unmanned plane it is many kinds of, mainly include fixed-wing unmanned plane, flapping wing unmanned plane and more rotation
Wing unmanned plane etc., due to manipulating simple, high reliablity, and do not need runway can VTOL, can be in sky after taking off
Middle hovering, therefore relative to fixed-wing unmanned plane and flapping wing unmanned plane, multi-rotor unmanned aerial vehicle has obtained extensively in every field
Using.
Multi-rotor unmanned aerial vehicle, generally include the body positioned at unmanned plane center, multiple horns for being connect with body with
And be set to the motor and rotor of each horn end, in the prior art, body is integrally in class cuboid, generally by upper cover, under
Bottom and the side plate three parts composition for being surrounded by body side, wherein mounting hole is opened up on side plate, by the way that horn is inserted into the installation
In hole, and using the connection of gluing realization horn and body between hole inner wall and horn periphery.
It for unmanned plane, on the one hand needs fuselage weight light as far as possible, on the other hand needs to guarantee that body is strong again
Degree, it is also necessary to be able to maintain balance, it is big that the body of above-mentioned class cuboid is from air power in flight course, in order to enhance machine
The intensity of body, it usually needs body is made using the metal material with certain degree of hardness, or is needed using the light of higher cost
Matter strong hardness material is difficult to mitigate fuselage weight simultaneously and reduces fuselage cost, thus, the body of above structure and shape exists
Mitigate fuselage weight and drop low cost aspect, has become the bottleneck of technology.
And for vehicle-mounted unmanned aerial vehicle, in the prior art, the mode of artificial help-fly is mostly used to take off greatly, this side
Formula is cumbersome, and unmanned plane takes off unstable, is easy to cause unmanned plane lateral deviation or failure of taking off, is unfavorable for takeoff operational
It carries out.
Summary of the invention
The main object of the present invention is to provide for a kind of vehicle-mounted unmanned aerial vehicle system, to solve cylinder block strength in the prior art
Low, body weight is big, fuselage is difficult to balance, at high cost and installation is inconvenient, takeoff operational is cumbersome, it is unstable to take off, easily leads to nothing
Man-machine lateral deviation or take off failure the problem of.
The purpose of the present invention can reach by using following technical solution:
A kind of vehicle-mounted unmanned aerial vehicle system, including vehicle-mounted unmanned aerial vehicle and take off and the force aid system that lands, it is described to take off and land
Force aid system include two be parallel to each other take off and the power assisting device that lands, it is described take off and land power assisting device be halfpace type, two
It is described take off and the power assisting device that lands between be equipped with two and take off and land driving device and a radio induction charging device, described in two
It takes off and the both ends for the power assisting device that lands is respectively equipped with the stabilizing member that takes off and land；The vehicle-mounted unmanned aerial vehicle includes fuselage, four sides
Axis, detachable carry axis and landing balance system, four side axles are symmetrically arranged on the fuselage, landing balance system
The two sides of two side axles are symmetrically arranged in system, and the lower section of the fuselage is arranged in the detachable carry axis, described removable
The lower section for unloading carry axis is equipped with 360 ° without dead angle video camera, and the front of the fuselage is equipped with ultrasonic distance measuring module installing port,
The top of the fuselage is equipped with telecontrol antenna, and installation part is equipped in four side axles, and the installation part is equipped with Image Acquisition
Module installing port, the installation part are equipped with connector, and driving motor and more is equipped on the installation part and the connector
A fixing piece, the driving motor are equipped with multiple rotors, and the rotor is equipped with rotor stabilizing member.
Further, the landing balance system includes landing stable equilibrium's axis and arc balance element, the arc balance
Slide slot is equipped in part, landing stable equilibrium's axis is arranged in the slide slot, and gravity sensing is equipped in the fuselage and is filled
It sets and balance control device, the gravity sensing device is described flat for incuding the landing stable equilibrium shaft balancing state
Weighing apparatus control device is in a vertical state for controlling landing stable equilibrium's axis, and the fuselage is made to keep equilibrium state.
Further, inner loop control unit and outer loop-control unit are equipped in the balance control device；The inner ring control
Unit processed is used to control the posture of landing stable equilibrium's axis and the arc balance element；The outer loop-control unit is for controlling
Make the angle of position and the arc balance element of the landing stable equilibrium's axis in the arc balance element.
Further, landing stable equilibrium's axis is metal shaft, and the end of landing stable equilibrium's axis is equipped with power-assist
Sliding structure, the power-assist sliding structure smoothly slide in the slide slot for the landing stable equilibrium axis.
Further, the end of landing stable equilibrium's axis and the junction of the slide slot are equipped with and slide locked knot
Structure, the locking structure that slides prevent described for being locked after fuselage balance to landing stable equilibrium's axis
Landing stable equilibrium's axis breaks away.
Further, the outside of the arc balance element is equipped with yielding rubber layer, and the yielding rubber layer is used at nobody
When machine lands, vibration is reduced, the outside both ends of the arc balance element are equipped with wireless induction localizing emission device, described wireless
Induction localizing emission device is connect with the gravity sensing device and the balance control device respectively.
Further, take off described in two and the power assisting device that lands in be equipped with sliding slot, it is described take off and land stabilizing member with
It is described to take off and driving device connection of landing, it is described take off and driving device of land control described in take off and the stabilizing member that lands is in institute
State sliding in sliding slot.
Further, it is described take off and the inside for the stabilizing member that lands be equipped with arc balance element card slot, the arc balance element
Card slot by the sliding slot slide clamping described in arc balance element, it is described take off and the stabilizing member that lands on be additionally provided with vehicle-mounted letter
Number reception device and wireless induction position receiver device, the cab signal reception device is for receiving vehicle-mounted instruction, and by vehicle
It carries instruction input to take off and driving device of land to described, the wireless induction position receiver device and wireless induction positioning
Emitter cooperation, for incuding described take off and land the distance between stabilizing member and the arc balance element.
Further, it is described take off and land arc balance element telescopic shaft and arc balance element axis are equipped in stabilizing member,
The arc balance element telescopic shaft is set on the arc balance element axis, and the arc balance element axis is flat in the arc
Weigh and stretch in part telescopic shaft, when arc balance element described in the arc balance element card slot clamping, the arc balance element axis and
The arc balance element telescopic shaft is put in the slide slot, described to take off and stabilization of landing when the vehicle-mounted unmanned aerial vehicle takes off
Part unclamps the arc balance element.
Further, the fuselage is tetragonal fuselage, and four angles of the quadrangle fuselage are equipped with intelligent radio sense
Inductive charging interface；It is described quadrangle fuselage four angles be equipped with memory, the memory for store unmanned plane instruction and
Flight control system data are also used to store position, speed and the posture of unmanned plane.
Advantageous effects of the invention: vehicle-mounted unmanned aerial vehicle system according to the invention, it is provided by the invention it is vehicle-mounted nobody
Machine system, solves in the prior art that cylinder block strength is low, body weight is big, fuselage is difficult to balance, at high cost and installation is inconvenient, rises
Fly it is cumbersome, take off it is unstable, easily lead to unmanned plane lateral deviation or take off failure the problem of, pass through landing stable equilibrium's axis
It can be good at guaranteeing the balance of unmanned plane with arc balance element, power assisting device can effectively keep nobody by taking off and landing
Take off balance and the landing stabilization of machine, guarantee unmanned plane safety, by radio induction charging device, can effectively ensure that unmanned plane
Radio induction charging in the non-use state, i.e. unmanned plane, which are once drop on the power assisting device that takes off and land, can be realized nothing
Line charge electricity, can effectively ensure that the normal electricity consumption of unmanned plane.
Detailed description of the invention
Fig. 1 is the stereoscopic schematic diagram of a preferred embodiment of vehicle-mounted unmanned aerial vehicle system according to the invention.
In figure: 1- takes off and lands power assisting device, 2- sliding slot, and 3- takes off and land stabilizing member, and 4- takes off and land driving
Device, 5- cab signal reception device, 6- arc balance element card slot, 7- arc balance element telescopic shaft, 8- arc balance element axis,
9- radio induction charging device, 10- wireless induction localizing emission device, 11- ultrasonic distance measuring module installing port, 12- image are adopted
Collection module installing port, 19- telecontrol antenna, 20- fuselage, 21- side axle, 22- wireless induction position receiver device, 23- installation part,
24- connector, 25- driving motor, 26- rotor stabilizing member, 27- rotor, 28- fixing piece, the detachable carry axis of 29-, 30-360 °
Without dead angle video camera, 31- landing stable equilibrium's axis, 32- arc balance element, 33- slide slot.
Specific embodiment
To make the more clear and clear technical solution of the present invention of those skilled in the art, below with reference to examples and drawings
The present invention is described in further detail, and embodiments of the present invention are not limited thereto.
As shown in Figure 1, a kind of vehicle-mounted unmanned aerial vehicle system provided in this embodiment, including vehicle-mounted unmanned aerial vehicle and takes off and land
Force aid system, it is described take off and the force aid system that lands include two be parallel to each other take off and the power assisting device 1 that lands, it is described take off and
Landing power assisting device 1 is halfpace type, take off described in two and the power assisting device 1 that land between take off and driving device 4 of landing equipped with two
With a radio induction charging device 9, takes off described in two and the both ends for the power assisting device 1 that lands are respectively equipped with the stabilizing member that takes off and land
3；The vehicle-mounted unmanned aerial vehicle includes fuselage 20, four side axles 21, detachable carry axis 29 and landing balance system, four side axles 21
Symmetrical to be arranged on the fuselage 20, the two sides of two side axles 21 are symmetrically arranged in the landing balance system, described
The lower section of the fuselage 20 is arranged in detachable carry axis 29, and the lower section of the detachable carry axis 29 is equipped with 360 ° and takes the photograph without dead angle
Camera 30, the front of the fuselage 20 are equipped with ultrasonic distance measuring module installing port 11, and the top of the fuselage 20 is equipped with remote control
Antenna 19, installation part 23 is equipped in four side axles 21, and the installation part 23 is equipped with image capture module installing port 12, institute
Installation part 23 is stated equipped with connector 24, driving motor 25 and multiple solid is equipped on the installation part 23 and the connector 24
Determine part 28, the driving motor 25 is equipped with multiple rotors 27, and the rotor 27 is equipped with rotor stabilizing member 26.
Further, in the present embodiment, as shown in Figure 1, the landing balance system includes landing stable equilibrium's axis 31
With arc balance element 32, the arc balance element 32 is interior to be equipped with slide slot 33, and the landing stable equilibrium axis 31 is arranged described
In slide slot 33, gravity sensing device and balance control device are equipped in the fuselage 20, the gravity sensing device is for feeling
The equilibrium state of landing stable equilibrium's axis 31 is answered, the balance control device is for controlling the landing stable equilibrium axis 31
It is in a vertical state, so that the fuselage 20 is kept equilibrium state, the balance control device is interior equipped with inner loop control unit and outer
Ring control unit；The inner loop control unit is used to control the appearance of landing stable equilibrium's axis 31 and the arc balance element 32
State；The outer loop-control unit is used to control position of the landing stable equilibrium's axis 31 in the arc balance element 32, and
The angle of the arc balance element 32.
Further, in the present embodiment, as shown in Figure 1, the landing stable equilibrium axis 31 is metal shaft, the landing
The end of stable equilibrium's axis 31 is equipped with power-assist sliding structure, and the power-assist sliding structure exists for the landing stable equilibrium axis 31
It is smoothly slided in the slide slot 33, the end of landing stable equilibrium's axis 31 and the junction of the slide slot 33 are equipped with and slide
Row locking structure, the locking structure that slides is for carrying out the landing stable equilibrium axis 31 after the fuselage 20 balance
It is locked, prevent the landing stable equilibrium axis 31 from breakking away.
Further, in the present embodiment, as shown in Figure 1, the outside of the arc balance element 32 is equipped with yielding rubber layer,
The yielding rubber layer is used in unmanned plane landing, reduces vibration, and the outside both ends of the arc balance element 32 are equipped with nothing
Line incudes localizing emission device 10, the wireless induction localizing emission device 10 respectively with the gravity sensing device and described flat
Weigh control device connection, take off described in two and the power assisting device 1 that land in be equipped with sliding slot 2, it is described take off and land stabilizing member 3 and
It is described to take off and the connection of driving device 4 of landing, it is described take off and driving device 4 of land control described in take off and the stabilizing member 3 that lands
It is slided in the sliding slot 2.
Further, in the present embodiment, as shown in Figure 1, described take off and the inside for the stabilizing member 3 that lands is flat equipped with arc
Weigh part card slot 6, the arc balance element card slot 6 by the sliding slot 2 slide clamping described in arc balance element 32, described
Cab signal reception device 5 and wireless induction position receiver device 22, the cab signal are additionally provided on winged and landing stabilizing member 3
Reception device 5 is taken off and driving device 4 of land for receiving vehicle-mounted instruction, and by vehicle-mounted instruction input to described, it is described wirelessly
Incude position receiver device 22 and the wireless induction localizing emission device 10 to cooperate, for incuding described take off and stabilization of landing
The distance between part 3 and the arc balance element 32, it is described take off and land arc balance element telescopic shaft 7 is equipped in stabilizing member 3
With arc balance element axis 8, the arc balance element telescopic shaft 7 is set on the arc balance element axis 8, and the arc is flat
The part axis 8 that weighs stretches in the arc balance element telescopic shaft 7, arc balance element described in 6 clamping of arc balance element card slot
When 32, the arc balance element axis 8 and the arc balance element telescopic shaft 7 are put in the slide slot 33, the vehicle-mounted nothing
It is man-machine when taking off, it is described to take off and the stabilizing member 3 that lands unclamps the arc balance element 32.
Further, in the present embodiment, as shown in Figure 1, the fuselage 20 is tetragonal fuselage, the quadrangle fuselage
Four angles be equipped with intelligent radio induction charging interface；Four angles of the quadrangle fuselage are equipped with memory, described to deposit
Reservoir is also used to store position, speed and the posture of unmanned plane for storing unmanned plane instruction and flight control system data.
In conclusion in the present embodiment, it is provided in this embodiment vehicle-mounted according to the vehicle-mounted unmanned aerial vehicle system of the present embodiment
UAV system, solve in the prior art cylinder block strength is low, body weight is big, fuselage is difficult to balance, at high cost and installation not
Just, takeoff operational is cumbersome, it is unstable to take off, easily lead to unmanned plane lateral deviation or take off failure the problem of, pass through landing stablize
Balance shaft and arc balance element can be good at guaranteeing the balance of unmanned plane, and by taking off and landing, power assisting device can be protected effectively
Take off balance and the landing stabilization for holding unmanned plane, guarantee unmanned plane safety, by radio induction charging device, can effectively ensure that
The radio induction charging of unmanned plane in the non-use state, i.e. unmanned plane, which are once drop to, to take off and lands on power assisting device
It realizes wireless charging, can effectively ensure that the normal electricity consumption of unmanned plane.
The above, further embodiment only of the present invention, but scope of protection of the present invention is not limited thereto, and it is any
Within the scope of the present disclosure, according to the technique and scheme of the present invention and its design adds those familiar with the art
With equivalent substitution or change, protection scope of the present invention is belonged to.
Claims (10)
1. a kind of vehicle-mounted unmanned aerial vehicle system, including vehicle-mounted unmanned aerial vehicle and take off and the force aid system that lands, it is characterised in that: described
Fly and landing force aid system include two be parallel to each other take off and the power assisting device that lands (1), it is described to take off and the power assisting device that lands
(1) be halfpace type, take off described in two and the power assisting device that land (1) between take off and driving device of landing (4) He Yiwu equipped with two
Line induction charging device (9), takes off described in two and the both ends of the power assisting device that lands (1) are respectively equipped with the stabilizing member that takes off and land
(3)；The vehicle-mounted unmanned aerial vehicle includes fuselage (20), four side axles (21), detachable carry axis (29) and landing balance system, four institutes
It states side axle (21) to be symmetrically arranged on the fuselage (20), two side axles are symmetrically arranged in the landing balance system
(21) two sides, the detachable carry axis (29) are arranged in the lower section of the fuselage (20), the detachable carry axis (29)
Lower section be equipped with 360 ° without dead angle video camera (30), the front of the fuselage (20) is equipped with ultrasonic distance measuring module installing port
(11), the top of the fuselage (20) is equipped with telecontrol antenna (19), is equipped with installation part (23) on four side axles (21), described
Installation part (23) is equipped with image capture module installing port (12), and the installation part (23) is equipped with connector (24), the peace
Driving motor (25) and multiple fixing pieces (28), the driving motor (25) are equipped in piece installing (23) and the connector (24)
It is equipped with multiple rotors (27), the rotor (27) is equipped with rotor stabilizing member (26).
2. a kind of vehicle-mounted unmanned aerial vehicle system according to claim 1, it is characterised in that: the landing balance system includes drop
Stable equilibrium's axis (31) and arc balance element (32) are fallen, is equipped with slide slot (33) in the arc balance element (32), the landing
Stable equilibrium's axis (31) setting is equipped with gravity sensing device and balance control in the slide slot (33), in the fuselage (20)
Device, the gravity sensing device are used to incude the equilibrium state of landing stable equilibrium's axis (31), the balance control dress
Set it is in a vertical state for controlling the landing stable equilibrium axis (31), make the fuselage (20) keep equilibrium state.
3. a kind of vehicle-mounted unmanned aerial vehicle system according to claim 2, it is characterised in that: be equipped in the balance control device
Inner loop control unit and outer loop-control unit；The inner loop control unit is for controlling the landing stable equilibrium axis (31) and institute
State the posture of arc balance element (32)；The outer loop-control unit is for controlling the landing stable equilibrium axis (31) in the arc
The angle of position and the arc balance element (32) in shape balance element (32).
4. a kind of vehicle-mounted unmanned aerial vehicle system according to claim 2, it is characterised in that: the landing stable equilibrium axis (31)
For metal shaft, the end of landing stable equilibrium's axis (31) is equipped with power-assist sliding structure, and the power-assist sliding structure is used for institute
Landing stable equilibrium's axis (31) is stated smoothly to slide in the slide slot (33).
5. a kind of vehicle-mounted unmanned aerial vehicle system according to claim 4, it is characterised in that: the landing stable equilibrium axis (31)
End and the junction of the slide slot (33) be equipped with and slide locking structure, the locking structure that slides is in the fuselage
(20) after balancing, the landing stable equilibrium axis (31) is locked, prevents the landing stable equilibrium axis (31) from side occurs
It is sliding.
6. a kind of vehicle-mounted unmanned aerial vehicle system according to claim 2, it is characterised in that: outside the arc balance element (32)
Side is equipped with yielding rubber layer, and the yielding rubber layer is used to reduce vibration, the arc balance element (32) in unmanned plane landing
Outside both ends be equipped with wireless induction localizing emission device (10), the wireless induction localizing emission device (10) respectively with institute
Gravity sensing device is stated to connect with the balance control device.
7. a kind of vehicle-mounted unmanned aerial vehicle system according to claim 6, it is characterised in that: take off described in two and power-assisted of landing fills
It sets and is equipped with sliding slot (2) in (1), it is described to take off and the stabilizing member that lands (3) takes off and driving device of landing (4) is connect with described,
It is described take off and driving device of landing (4) control described in take off and the stabilizing member that land (3) slides in the sliding slot (2).
8. a kind of vehicle-mounted unmanned aerial vehicle system according to claim 7, it is characterised in that: described to take off and the stabilizing member that lands
(3) inside is equipped with arc balance element card slot (6), and the arc balance element card slot (6) passes through the sliding card in the sliding slot (2)
The tight arc balance element (32), it is described take off and the stabilizing member that land (3) on be additionally provided with cab signal reception device (5) and wirelessly
Incude position receiver device (22), the cab signal reception device (5) is for receiving vehicle-mounted instruction, and by vehicle-mounted instruction input
It takes off described in and driving device of landing (4), the wireless induction position receiver device (22) and wireless induction positioning is sent out
Injection device (10) cooperation, for incuding described take off and the distance between the stabilizing member that lands (3) and the arc balance element (32).
9. a kind of vehicle-mounted unmanned aerial vehicle system according to claim 8, it is characterised in that: described to take off and the stabilizing member that lands
(3) arc balance element telescopic shaft (7) and arc balance element axis (8) are equipped in, the arc balance element telescopic shaft (7) is set in
On the arc balance element axis (8), the arc balance element axis (8) is stretched in the arc balance element telescopic shaft (7),
When arc balance element (32) described in arc balance element card slot (6) clamping, the arc balance element axis (8) and the arc
Balance element telescopic shaft (7) is put in the slide slot (33), described to take off and the stabilizing member that lands when the vehicle-mounted unmanned aerial vehicle takes off
(3) the arc balance element (32) is unclamped.
10. a kind of vehicle-mounted unmanned aerial vehicle system according to claim 1, it is characterised in that: the fuselage (20) is quadrangle
Four angles of fuselage, the quadrangle fuselage are equipped with intelligent radio induction charging interface；Four angles of the quadrangle fuselage
It is equipped with memory, the memory is also used to store unmanned plane for storing unmanned plane instruction and flight control system data
Position, speed and posture.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710664447.2A CN109383835A (en) | 2017-08-04 | 2017-08-04 | A kind of vehicle-mounted unmanned aerial vehicle system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710664447.2A CN109383835A (en) | 2017-08-04 | 2017-08-04 | A kind of vehicle-mounted unmanned aerial vehicle system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109383835A true CN109383835A (en) | 2019-02-26 |
Family
ID=65413160
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710664447.2A Pending CN109383835A (en) | 2017-08-04 | 2017-08-04 | A kind of vehicle-mounted unmanned aerial vehicle system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109383835A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110001988A (en) * | 2019-04-03 | 2019-07-12 | 南京利剑无人机科技有限公司 | A kind of vehicle-mounted multi-rotor unmanned aerial vehicle landing platform |
| US20210094687A1 (en) * | 2019-09-30 | 2021-04-01 | Ford Global Technologies, Llc | Landing apparatuses for unmanned aerial vehicles |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20160214713A1 (en) * | 2014-12-19 | 2016-07-28 | Brandon Cragg | Unmanned aerial vehicle with lights, audio and video |
| KR101650136B1 (en) * | 2016-02-05 | 2016-08-25 | 김석준 | The apparatus of smart drone |
| CN205891232U (en) * | 2016-07-08 | 2017-01-18 | 上海工程技术大学 | Urgent safe launching appliance of four rotor unmanned aerial vehicle |
| CN206218239U (en) * | 2016-12-05 | 2017-06-06 | 深圳市道通智能航空技术有限公司 | Unmanned vehicle |
| CN207089678U (en) * | 2017-08-04 | 2018-03-13 | 上海裕芮信息技术有限公司 | A kind of vehicle-mounted unmanned aerial vehicle system |
-
2017
- 2017-08-04 CN CN201710664447.2A patent/CN109383835A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20160214713A1 (en) * | 2014-12-19 | 2016-07-28 | Brandon Cragg | Unmanned aerial vehicle with lights, audio and video |
| KR101650136B1 (en) * | 2016-02-05 | 2016-08-25 | 김석준 | The apparatus of smart drone |
| CN205891232U (en) * | 2016-07-08 | 2017-01-18 | 上海工程技术大学 | Urgent safe launching appliance of four rotor unmanned aerial vehicle |
| CN206218239U (en) * | 2016-12-05 | 2017-06-06 | 深圳市道通智能航空技术有限公司 | Unmanned vehicle |
| CN207089678U (en) * | 2017-08-04 | 2018-03-13 | 上海裕芮信息技术有限公司 | A kind of vehicle-mounted unmanned aerial vehicle system |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110001988A (en) * | 2019-04-03 | 2019-07-12 | 南京利剑无人机科技有限公司 | A kind of vehicle-mounted multi-rotor unmanned aerial vehicle landing platform |
| US20210094687A1 (en) * | 2019-09-30 | 2021-04-01 | Ford Global Technologies, Llc | Landing apparatuses for unmanned aerial vehicles |
| US11794894B2 (en) * | 2019-09-30 | 2023-10-24 | Ford Global Technologies, Llc | Landing apparatuses for unmanned aerial vehicles |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US20180327093A1 (en) | Aircraft-retrieval system | |
| CN208585509U (en) | aerodynamic shipping package | |
| US11524797B2 (en) | Aircraft-retrieval system | |
| CN202080435U (en) | Ranked dual-rotor vertically-lifted unmanned aerial vehicle (UAV) | |
| CN203528816U (en) | Aerial photo unmanned plane | |
| CN106394895B (en) | A kind of polymorphic unmanned plane and its flight control method | |
| CN105346709B (en) | A kind of multi-rotor aerocraft of deformable combination | |
| CN205554623U (en) | Optical zoom nacelle | |
| FI127407B (en) | Interface for connecting functional modules and aerial vehicles, related module and aerial vehicle | |
| CN110262561A (en) | A kind of unmanned plane automatic obstacle-avoiding method | |
| CN109733598A (en) | Aircraft duct and culvert type aircraft | |
| CN207089656U (en) | A kind of vehicle-mounted police UAS | |
| CN109383835A (en) | A kind of vehicle-mounted unmanned aerial vehicle system | |
| CN208248488U (en) | Modularized micro unmanned plane | |
| WO2019073417A1 (en) | Aerial system including foldable frame architecture | |
| CN108423153A (en) | Modularized micro unmanned plane | |
| CN210526849U (en) | Fixed wing unmanned aerial vehicle of tilting-rotating force | |
| AU2019101129A4 (en) | Coaxial Reverse Rotary Wing Mini UAV | |
| CN107942348A (en) | A kind of road enforcement system based on unmanned plane and robot technology | |
| CN208000379U (en) | A kind of road enforcement system based on unmanned plane and robot technology | |
| CN207089678U (en) | A kind of vehicle-mounted unmanned aerial vehicle system | |
| CN207173952U (en) | A kind of rotor wing unmanned aerial vehicle and its control system for flying control plate based on APM | |
| CN210455176U (en) | Folding horn and unmanned vehicles | |
| CN109383777B (en) | Unmanned aerial vehicle organism | |
| CN207232765U (en) | One kind combination collaboration load-carrying aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |