CN106628151A - Unmanned aerial vehicle with fast detachable shell - Google Patents
Unmanned aerial vehicle with fast detachable shell Download PDFInfo
- Publication number
- CN106628151A CN106628151A CN201611269864.9A CN201611269864A CN106628151A CN 106628151 A CN106628151 A CN 106628151A CN 201611269864 A CN201611269864 A CN 201611269864A CN 106628151 A CN106628151 A CN 106628151A
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- China
- Prior art keywords
- supporting leg
- casing
- unmanned plane
- installing plate
- hinged
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- 229920000049 Carbon (fiber) Polymers 0.000 claims description 17
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- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 17
- 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 11
- 238000009434 installation Methods 0.000 claims description 7
- 230000007306 turnover Effects 0.000 claims description 6
- 239000007787 solid Substances 0.000 claims description 3
- 238000005452 bending Methods 0.000 abstract 2
- 210000001503 joint Anatomy 0.000 abstract 1
- 230000000694 effects Effects 0.000 description 10
- 238000000034 method Methods 0.000 description 6
- 229910000838 Al alloy Inorganic materials 0.000 description 4
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 4
- 230000002708 enhancing effect Effects 0.000 description 4
- 229910052744 lithium Inorganic materials 0.000 description 4
- 239000000203 mixture Substances 0.000 description 4
- 230000003139 buffering effect Effects 0.000 description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 230000005611 electricity Effects 0.000 description 2
- 229920002457 flexible plastic Polymers 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000002457 bidirectional effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/04—Arrangement or disposition on aircraft
-
- 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
-
- 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
- B64C25/18—Operating mechanisms
- B64C25/20—Operating mechanisms mechanical
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
- B64D47/08—Arrangements of cameras
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention relates to an unmanned aerial vehicle with a fast detachable shell. The unmanned aerial vehicle comprises a vehicle body, an arm, double support foot stands and a shell, wherein one end of the arm is hinged to a mounting plate at the bottom of the vehicle body, and the other end of the arm is connected with a rotor wing driving assembly; the double support foot stands comprise two brackets which are symmetrically arranged on both sides of the vehicle body and two driving components which are connected with the brackets; each bracket comprises a first support leg of which one end is reversibly connected with the mounting plate, a second support leg of which one end is hinged to the mounting plate, and a first bottom rod which is parallel to the mounting plate and is fixedly connected with the other end of the first support leg and the other end of the second support leg at the same time; the shell comprises a bottom shell and an upper shell which wraps the vehicle body after being fixed to the bottom shell in a butt joint way; the bottom shell comprises a bottom plate and a first enclosure formed by bending the outer edge of the bottom plate; the upper shell comprises an upper cover plate and a second enclosure which is formed by bending the outer edge of the upper cover plate and can be matched with the first enclosure. By adopting the unmanned aerial vehicle with the fast detachable shell, the foot stand support stability can be enhanced, stable landing of the unmanned aerial vehicle is ensured, and the shell can be assembled and detached rapidly.
Description
Technical field
The present invention relates to unmanned air vehicle technique field, more particularly to casing fast disassembly type unmanned plane.
Background technology
UAV referred to as " unmanned plane ", is manipulated using radio robot and the presetting apparatus provided for oneself
Not manned aircraft.Because its action is flexible, landing environmental requirement is relatively low, and with good operating characteristics etc., it is widely used in
The numerous areas such as take photo by plane, monitor, investigating, searching and rescuing.Without driving cabin on unmanned plane, but automatic pilot, programme-control dress are installed
Put, the equipment such as information collecting device.On ground, naval vessels or machine tool remote control station personnel are by the equipment such as radar, it is tracked,
Positioning, remote control, remote measurement and Digital Transmission.
Unmanned plane generally using downhill race and is vertically moved up or down both flying methods, is generally provided with foot rest, so as to
In unmanned plane when landing, can be by its foot rest to aircraft standing support.The conventional foot rest of unmanned plane in prior art
Stability of strutting system is poor, particularly when unmanned plane hangs relatively large load to land, there is foot rest because large impact causes itself mechanism
The deformation even risk of damage, cause whole unmanned plane landing place sideslip or fuselage to be tumbled and damage the thing of internal body part
Therefore.Meanwhile, the casing structure of existing unmanned plane is difficult the quick operating efficiency realized installation and removal, affect unmanned plane.
The content of the invention
The casing fast disassembly type unmanned plane that the application is provided, solve or part solve in prior art conventional foot rest
, there is foot rest because large impact causes itself deformation or even damages risk in support less stable, casing structure is difficult during landing
The quick technical problem for realizing installation and removal, realizes enhancing foot rest stability of strutting system, ensures unmanned plane stable landing, it is ensured that
Unmanned plane can smoothly obtain omnidirectional image information, the technique effect of casing energy fast assembling-disassembling in flight course.
This application provides a kind of casing fast disassembly type unmanned plane, the casing fast disassembly type unmanned plane includes：Rotor, rotor
Axle, rotor drive component, gondola and flight control system, the rotor is fixedly connected with the rotor shaft；The rotor drives
Component is fixedly connected with the rotor shaft, to drive the rotor shaft and the rotor wing rotation to provide lift as the unmanned plane；
The casing fast disassembly type unmanned plane also includes：
Fuselage；It is mounted with image information and shoots with video-corder the gondola of part and hangs and be located on the installing plate of the fuselage bottom；Institute
State flight control system to be arranged on the fuselage；
Horn；One end of the horn is hinged with the installing plate of the fuselage bottom, the other end and the rotor driving group
Part connects；
Double-support foot stand, is arranged on the installing plate of the fuselage bottom；The double-support foot stand includes：Two symmetrically set
Put the support and two driver parts being connected with the support in the fuselage both sides；The support includes：One end with it is described
Installing plate may be reversed the first supporting leg of connection, one end and the second supporting leg that the installing plate is hinged, the parallel installing plate and same
When the first bottom bar for being fixedly connected with the other end of first supporting leg and the other end of second supporting leg；
Casing；The casing includes：The drain pan that is fixedly connected with the installing plate and dock with the drain pan it is fixed after wrap
Wrap up in the upper casing of the fuselage；The drain pan includes：The base plate that stretches out and formed from the surrounding of the installing plate and by described
The first enclosing that the outer of base plate is bent to form；The upper casing includes：Top arch upward after formed the first cavity volume upper cover plate and by
What the outer of the upper cover plate was bent to form can be with first enclosing with the second suitable enclosing；It is arranged on the fuselage roof
Power supply part is located in first cavity volume；Second enclosing is connected by several hasps with first enclosing.
Preferably, first supporting leg is hinged by the first overturning seat with the installing plate；
First overturning seat is fixed on the installing plate outer lower section；
One end of first supporting leg is hinged by rotating shaft with first overturning seat；
First overturning seat is hinged with the first flip piece；
First flip piece is hinged with the second flip piece；
Second flip piece is hinged with first supporting leg；
Wherein, the pin joint of second flip piece and first supporting leg be located at first supporting leg two-end-point it
Between.
Preferably, the driver part is arranged on first overturning seat；
The output end of the driver part is connected with first flip piece, to drive first flip piece around described
One flip piece is rotated with the pin joint of first overturning seat.
Preferably, first supporting leg is fixedly connected by the first connector with first bottom bar；
First connector includes：With the first leg ends matching form fit the first sleeve and for described first
The first through hole that bottom bar is passed through；
The first set jacket casing is located at the end of first supporting leg and is fixedly connected by screw；
First bottom bar is located in the first through hole of first connector and is connected with described first by screw
Part is fixed.
Preferably, second supporting leg be arranged in parallel with first supporting leg；
One end of second supporting leg is hinged with the installing plate, and the relatively described installing plate of first supporting leg can be followed to turn over
Turn；
Second supporting leg is fixedly connected by the second connector with first bottom bar；
Second connector includes：With the second leg ends matching form fit second sleeve and for described first
The second through hole that bottom bar is passed through；
The second sleeve is set in the end of second supporting leg and is fixedly connected by screw；
First bottom bar is located in the second through hole of second connector and is connected with described second by screw
Part is fixed.
Preferably, the casing opens up the pilot hole being connected with the installing plate for the horn；
The fixed seat being fixedly connected with the installing plate is set in the pilot hole；
The end of the horn is hinged by rotating shaft with the fixed seat；
The end of the horn is connected with positioning wedged block；
Wherein, the horn is flipped up to after operating position, and the positioning wedged block coordinates with the fixed seat will be described
Horn is limited to the operating position；Now, plate face of the rotation axis of the rotor perpendicular to the installing plate.
Preferably, the horn includes：Hollow carbon fiber pipe, the pipe box for being socketed in described carbon fiber pipe one end and with
The assembling block that the carbon fiber pipe other end is fixedly connected；
The end of the pipe box is connected with articulated slab；
The articulated slab is hinged by the rotating shaft with the fixed seat；
The positioning wedged block is fixed on the articulated slab；
The pipe box is fastened with the carbon fiber pipe by screw；
The rotor drive component is fixed on the assembling block.
Preferably, the hasp includes：The button that is arranged on second enclosing and it is arranged on first enclosing
On with the button coordinate projection；
Second enclosing is connected by 2 hasps with first enclosing；
2 hasps are separately positioned on the both sides of the casing.
Preferably, the upper cover plate arranges the concave face that the oriented fuselage interior is drawn close；
The concave face opens up louvre；
The casing also includes：Heat sink；
The heat sink is detachably arranged in the louvre.
Preferably, the quantity of the concave face is two, respectively the first concave face and the second concave face；
First concave face and second concave face are respectively positioned at the both sides of the upper cover plate；
The casing includes two blocks of heat sinks, respectively the first heat sink and the second heat sink；
First concave face opens up the first louvre of accommodating first heat sink；
Second concave face opens up the second louvre of accommodating second heat sink；
First louvre is arranged on the side of the power supply part of the fuselage roof；
Second louvre is arranged on the opposite side of the power supply part of the fuselage roof.
One or more technical schemes provided herein, at least have the following technical effect that or advantage：
As a result of the double-support foot stand that the support that fuselage both sides are symmetricly set on by two is constituted, strengthen foot rest structure
Stability of strutting system, the large impact power that produces when heavy load unmanned plane lands can be resisted, ensure unmanned plane landing stationarity and
Positional accuracy；In flight course, the image information hung in the gondola being located on fuselage bottom installing plate shoots with video-corder portion to unmanned plane
Part obtains image information, is mounted opposite plate upset by driver part driving arm, it is to avoid the support Occlusion Map of double-support foot stand
As information shoots with video-corder part, and then unmanned function is set to obtain omnibearing image information.Docked by drain pan and with drain pan by arranging
The casing of the upper casing composition of fuselage is wrapped up after fixation, drain pan and upper casing are fixed by hasp connection, facilitate casing fast assembling-disassembling.This
Sample, the stability of strutting system for efficiently solving conventional foot rest in prior art is poor, there is foot rest during landing because large impact is caused certainly
Body deformation even damages risk, and casing structure is difficult the quick technical problem for realizing installation and removal, realizes enhancing pin
Frame stability of strutting system, ensures unmanned plane stable landing, it is ensured that unmanned plane can smoothly obtain omnidirectional images letter in flight course
Breath, the technique effect of casing energy fast assembling-disassembling.
Description of the drawings
Fig. 1 is the general assembly drawing of casing fast disassembly type unmanned plane provided in an embodiment of the present invention；
Fig. 2 is the structural front view that casing is assembled with double-support foot stand in Fig. 1；
Fig. 3 is the structure left view that casing is assembled with double-support foot stand in Fig. 1；
Fig. 4 is the structural representation that casing is assembled with horn in Fig. 1；
Fig. 5 is the partial enlarged drawing of horn in Fig. 1；
Fig. 6 is the partial enlarged drawing of casing in Fig. 1.
(part that each label is represented in diagram is followed successively by：1 rotor, 2 casings, 3 rotor drive components, 4 horns, 5 dual-grippers
Foot rest, 6 first supports, 7 second supports, 8 hasps, 201 upper cover plates, 203 second enclosings, 204 base plates, 205 second enclosings, 206
Concave face, 401 fixed seats, 402 pipe boxes, 403 motors, 404 assembling blocks, 405 electric tune, 406 carbon fiber pipes, 601 first supporting legs,
602 second supporting legs, 603 first bottom bars, 604 first overturning seats, 605 first flip pieces, 606 second flip pieces, 607 first connections
Part, 608 anti-skidding buffering sheaths, 609 first extension springs, 610 first driver parts, 710 second driver parts)
Specific embodiment
The casing fast disassembly type unmanned plane that the embodiment of the present application is provided, solves or part solves conventional pin in prior art
The stability of strutting system of frame is poor, there is foot rest during landing because large impact causes itself deformation or even damages risk, casing knot
Structure is difficult the quick technical problem for realizing installation and removal, and fuselage both sides are symmetricly set on by two by arranging in fuselage bottom
Support composition double-support foot stand；Drain pan and upper casing are fixed by hasp connection；Enhancing foot rest stability of strutting system is realized, is protected
Barrier unmanned plane stable landing, it is ensured that unmanned plane can smoothly obtain omnidirectional image information in flight course, and casing can quickly be torn open
The technique effect of dress.
Referring to attached Fig. 1 and 2, this application provides a kind of casing fast disassembly type unmanned plane, the casing fast disassembly type unmanned plane includes：
Rotor 1, rotor shaft, rotor drive component 3, gondola and flight control system, rotor 1 is fixedly connected with rotor shaft；Rotor drives
Component 3 is fixedly connected with rotor shaft, and to drive rotor shaft and rotor 1 to rotate to be unmanned plane lift is provided；The casing fast disassembly type without
It is man-machine also to include：Fuselage, horn 4, double-support foot stand 5 and casing 2.
It is mounted with image information and shoots with video-corder the gondola of part and hangs on the installing plate for being located at fuselage bottom；Flight control system is arranged
On fuselage；One end of horn 4 is hinged with the installing plate of fuselage bottom, and the other end is connected with rotor drive component 3；Dual-gripper pin
Frame 5 is arranged on the installing plate of fuselage bottom；Double-support foot stand 5 includes：Two supports for being symmetricly set on fuselage both sides and two
The individual driver part being connected with support；Support includes：One end may be reversed the first supporting leg, one end and the installing plate being connected with installing plate
The second supporting leg for being hinged, parallel mounting plates and while it is fixedly connected with the other end of the first supporting leg and the other end of the second supporting leg
First bottom bar.Casing 2 includes：The drain pan being fixedly connected with installing plate and the upper casing that parcel fuselage after fixation is docked with drain pan.Bottom
Shell includes：The base plate 204 that stretches out and formed from the surrounding of installing plate and first enclosed by what the outer of base plate 204 was bent to form
Gear 205；Upper casing includes：Upper cover plate 201 and by the outer of upper cover plate 201 be bent to form can be with the first enclosing 205 with suitable the
Two enclosings 203；First cavity volume is formed after arching upward on the top of upper cover plate 201；The power supply part of fuselage roof is located in the first cavity volume,
By the shape for rationally arranging upper cover plate 201, it is allowed to be adapted with the power supply part position of fuselage roof.
Wherein, the second enclosing 203 is connected by several hasps 8 with the first enclosing 205；Hasp 8 includes：It is arranged on
Button on second enclosing 203 and the projection coordinated with button is arranged on the first enclosing 205.By hasp 8 realize upper casing with
The connection of drain pan, makes the disassembling operations of casing 2 easy and can guarantee that to be connected firmly.Used as a kind of preferred embodiment, second encloses
Gear 203 is connected by 2 hasps 8 with the first enclosing 205；2 hasps 8 are symmetrically arranged at the both sides of casing, it is ensured that
The integrally-built connection fixing of casing 2.
Referring to accompanying drawing 2 and 3, two supports of double-support foot stand 5 are respectively first support 6 and second support 7；Two drivings
Part is respectively the first driver part 610 and the second driver part 710.First support 6 includes：One end may be reversed with installing plate and connect
The second supporting leg 602, parallel mounting plates that the first supporting leg 601, one end for connecing and installing plate are hinged and while with the first supporting leg 601
The first bottom bar 603 that the other end of the other end and the second supporting leg 602 is fixedly connected；Second support 7 includes：One end can with installing plate
The 4th supporting leg, parallel mounting plates and while another with the 3rd supporting leg that 3rd supporting leg of upset connection, one end and installing plate are hinged
The second bottom bar that the other end of one end and the 4th supporting leg is fixedly connected；First supporting leg of the first driver part 610 and first support 6
601 connections, to drive the first supporting leg 601 and first support 6 to be mounted opposite plate upset；Second driver part 710 and second support 7
The 3rd supporting leg connection, with drive the 3rd supporting leg and second support 7 be mounted opposite plate upset.
Wherein, the double-support foot stand 5 of first support 6 and second support 7 composition of fuselage both sides is symmetricly set on, strengthens pin
The stability of strutting system of frame structure, can resist the large impact power produced when heavy load unmanned plane lands, and ensure the flat of unmanned plane landing
Stability and positional accuracy；Unmanned plane hangs the image information in the gondola being located on fuselage bottom installing plate in flight course
Component retrieval image information is shot with video-corder, drives the first supporting leg and first support 6 to be mounted opposite plate and turn over by the first driver part 610
Turn, meanwhile, drive the 3rd supporting leg and second support 7 to be mounted opposite plate upset by the second driver part 710, it is to avoid foot rest is blocked
Image information shoots with video-corder part, and then makes unmanned function obtain omnibearing image information.
Further, the first supporting leg 601 is hinged by the first overturning seat 604 with installing plate；First overturning seat 604 is fixed on
Installing plate outer lower section；One end of first supporting leg 601 is hinged by rotating shaft with the first overturning seat 604；First overturning seat 604 is hinged
There is the first flip piece 605；First flip piece 605 is hinged with the second flip piece 606；Second flip piece 606 cuts with scissors with the first supporting leg 601
Connect；Wherein, the pin joint of the second flip piece 606 and the first supporting leg 601 is located between the two-end-point of the first supporting leg 601.
Further, the first driver part 610 is arranged on the first overturning seat 604；The output end of the first driver part 610
It is connected with the first flip piece 605, to drive the first flip piece 605 around the first flip piece 605 and the pin joint of the first overturning seat 604
Rotate, the upset of the first supporting leg 601 and first support 6 is realized then；After unmanned plane takes off, flight control system control first is driven
Dynamic component 610 works, and the first flip piece 605 is rotated around the pin joint of the first flip piece 605 and the first overturning seat 604, then
The second flip piece 606 and the first supporting leg 601 is driven to dig upwards, until the first supporting leg 601 is located at the first station, now, first
Support 6 will not shielded image information shoot with video-corder part, make unmanned function obtain omnibearing image information.When unmanned plane lands, fly
Row control system controls the reverse operation of the first driver part 610, the first flip piece 605 is turned over first around the first flip piece 605
The pin joint of swivel base 604 is rotated backward, and drives the second flip piece 606 and the first supporting leg 601 to dig downwards then, until first
Leg 601 is located at the second station, and now, first support 6 stably can support the unmanned plane that will be landed.
Further, first support 6 also includes the first extension spring 609；One end of first extension spring 609 and the first overturning seat 604
It is fixedly connected, the other end is fixedly connected with the first supporting leg 601；Wherein, the tie point position of the first extension spring 609 and the first supporting leg 601
In near the position of the first bottom bar 603；When the first driver part 610 drives the first supporting leg 601 to dig upwards, the first extension spring
609 provide certain pulling force to the first supporting leg 601, reduce the load of the first driver part 610, meanwhile, turn over can first support 6
Play stable in the operating position after the first station of unmanned plane during flying.
Used as a kind of preferred embodiment, the first driver part 610 is the reducing motor of bidirectional rotation；Reducing motor and machine
Power supply part electrical connection in shell 2；Reducing motor is connected with flight control system；The output shaft of reducing motor is located in first and turns over
Turn the pin joint of part 605 and the first overturning seat 604 and be fixedly connected with the first flip piece 605.
Used as another kind of preferred embodiment, the first driver part 610 is hydraulic cylinder；The cylinder seat of hydraulic cylinder and the first upset
Seat 604 is hinged, and piston rod is hinged with the first flip piece 605；Hydraulic cylinder is electrically connected with the power supply part in casing 2；Hydraulic cylinder with
Flight control system connects.
Further, the first supporting leg 601 is fixedly connected by the first connector 607 with the first bottom bar 603；First connector
607 first through hole for including the first sleeve matched with the end shape of the first supporting leg 601 and passing through for the first bottom bar 603；The
A set of jacket casing is located at the end of the first supporting leg 601 and is fixedly connected by screw；First bottom bar 603 is located in the first connector
Fixed in 607 first through hole and with the first connector 607 by screw.
Further, the second supporting leg 602 of first support 6 be arranged in parallel with the first supporting leg 601；The one of second supporting leg 602
End is hinged with installing plate, and the first supporting leg 601 can be followed to be mounted opposite plate upset.Second supporting leg 602 is by the second connector and the
One bottom bar 603 is fixedly connected；Second connector includes the second sleeve matched with the end shape of the second supporting leg 602 and supplies first
The second through hole that bottom bar 603 is passed through；Second sleeve is set in the end of the second supporting leg 602 and is fixedly connected by screw；First
Bottom bar 603 is located in the second through hole of the second connector and is fixed with the second connector by screw.
Further, the 3rd supporting leg of second support 7 is hinged by the second overturning seat and installing plate；Second overturning seat is fixed
Below installing plate outer；One end of 3rd supporting leg is hinged by rotating shaft with the second overturning seat；Second overturning seat is hinged with the 3rd
Flip piece；3rd flip piece is hinged with the 4th flip piece；4th flip piece is hinged with the 3rd supporting leg；Wherein, the 4th flip piece with
The pin joint of the 3rd supporting leg is located between the two-end-point of the 3rd supporting leg.Second support 7 also includes the second extension spring；The one of second extension spring
End is fixedly connected with the second overturning seat, and the other end is fixedly connected with the 3rd supporting leg；Wherein, the second extension spring and the connection of the 3rd supporting leg
Point is located near the position of the second bottom bar.Second driver part 710 is arranged on the second overturning seat；Second driver part 710
Output end is connected with the 3rd flip piece, to drive the 3rd flip piece to rotate around the pin joint of the 3rd flip piece and the second overturning seat.
Wherein, after unmanned plane takes off, flight control system control the second driver part 710 work, make the 3rd flip piece around
The pin joint of the 3rd flip piece and the second overturning seat is rotated, and drives the 3rd flip piece and the 3rd supporting leg to dig upwards then, until
3rd supporting leg is located at the first station, now, second support 7 will not shielded image information shoot with video-corder part, obtain unmanned function complete
The image information in orientation.When unmanned plane lands, the flight control system control reverse operation of the second driver part 710 makes the 3rd to turn over
Turn part to rotate backward around the 3rd flip piece and the pin joint of the second overturning seat, drive the 3rd flip piece and the 3rd supporting leg downward then
Dig, until the 3rd supporting leg is located at the second station, now, second support 7 stably can support the unmanned plane that will be landed.
Further, the 3rd supporting leg is fixedly connected by the 3rd connector with the second bottom bar；3rd connector includes and
The suitable 3rd sleeve of three leg ends matching forms and the third through-hole passed through for the second bottom bar；3rd sleeve is set in the 3rd
The end of leg is simultaneously fixedly connected by screw；Second bottom bar is located in the third through-hole of the 3rd connector and passes through screw and the
Three connectors are fixed.
Further, the 4th supporting leg of second support 7 be arranged in parallel with the 3rd supporting leg；One end of 4th supporting leg and installing plate
It is hinged, the 3rd supporting leg can be followed to be mounted opposite plate upset.4th supporting leg is fixedly connected by the 4th connector with the second bottom bar；The
Four connectors include：The 4th sleeve matched with the end shape of the 4th supporting leg and the fourth hole passed through for the second bottom bar；
4th sleeve is set in the end of the 4th supporting leg and is fixedly connected by screw；Second bottom bar is located in the 4th of the 4th connector
Fixed in through hole and with the 4th connector by screw.
Further, the first supporting leg 601, the second supporting leg 602 and the first bottom bar 603 are hollow carbon fiber pipe；3rd
Leg, the 4th supporting leg and the second bottom bar are hollow carbon fiber pipe.The two ends of the first bottom bar 603 are arranged the anti-skidding slow of flexible plastic material
Rush sheath 608；The two ends of the second bottom bar are arranged the anti-skidding buffering sheath of flexible plastic material.On the one hand anti-skidding buffering sheath 608 increases
Big support and the frictional force on ground, it is ensured that the accuracy of unmanned plane landing place, ensure the stability after UAV Landing, another
Aspect plays certain cushioning effect to support, it is to avoid large impact when unmanned plane lands causes the damage of fuselage.
Further, referring to attached Figure 4 and 5, casing 2 opens up the pilot hole being connected with installing plate for horn 4.Set in pilot hole
Put the fixed seat 401 being fixedly connected with installing plate；The end of horn 4 is hinged by rotating shaft with fixed seat 401；The end of horn 4
It is connected with positioning wedged block；Wherein, horn 4 is flipped up to after operating position, and positioning wedged block coordinates horn 4 with fixed seat 401
It is limited to operating position；Now, plate face of the rotation axis of rotor 1 perpendicular to installing plate.Tied by arranging turnover horn 4
Structure, when the unmanned plane is transported, horn 4 is turned down to the direction of installing plate, on the one hand reduces taking up room for the unmanned plane, is reduced
Transport difficulty, on the other hand protects the rotor drive component 3 and rotor 1 of the end of horn 4, it is to avoid rotor driving group in transportation
Part and rotor are damaged by collision or even horn 4 fractures.
Further, referring to accompanying drawing 5, horn 4 includes：Hollow carbon fiber pipe 406, it is socketed in the one end of carbon fiber pipe 406
Pipe box 402 and the assembling block 404 that is fixedly connected with the other end of carbon fiber pipe 406；The end of pipe box 402 is connected with articulated slab；
Articulated slab is hinged by rotating shaft with fixed seat 401；Positioning wedged block is fixed on articulated slab；Pipe box 402 passes through with carbon fiber pipe 406
Screw is fastened；Rotor drive component 3 is fixed on assembling block 404.The sound construction of horn 4 being made up of said structure, weight is little,
Installation and removal are very convenient, each component low cost of manufacture and are convenient for changing accessory.
Further, rotor drive component 3 includes：The motor 403 being connected with the power supply part of fuselage roof and and motor
The electricity of 403 connections adjusts 405；Motor 403 is fixed on the top or bottom of assembling block 404；Motor 403 is by being located in carbon fiber pipe
Electric wire inside 406 is connected with the power supply part of fuselage roof；Electricity adjusts 405 electric wires by being located in inside carbon fiber pipe 406
It is connected with the flight control system in casing.The tie point of horn 4 and installing plate is relative to foot rest 5 and the tie point edge of installing plate
The edge arranged for interval of installing plate；The space that the space of the upset of horn 4 overturns with foot rest 5 does not overlap.
Further, unmanned plane is provided with several horns 4；Several horns 4 are respectively symmetrically the both sides for being arranged in fuselage
Position.The end of each horn 4 is connected with two rotor drive components 3；Each rotor drive component 3 is connected with rotor shaft and drives
Dynamic rotor shaft is rotated；Each rotor shaft is connected with rotor 1；Wherein, two rotors 1 of the end of same horn 4 are arranged on around phase
Same rotation axis rotation.
Further, referring to accompanying drawing 6, upper cover plate 201 arranges the concave face 206 that oriented fuselage interior is drawn close；Concave face 206
Open up louvre.Wherein, when unmanned plane works in rainwater environment, the rainwater slid from the top of upper casing can Jing concave faces 206
Top directly drops to the lower section of louvre and enters louvre without stream, and when unmanned plane advances, the rainwater of upper casing can be straight from top
Connect and bypass concave face 206 and be slipped to the bottom of casing 2, be prevented effectively from rainwater and entered in the inside of casing 2 infringement fuselage by louvre
Part, significantly improve the water resistance of unmanned plane.
Casing 2 also includes：Heat sink 202；Heat sink 202 is detachably arranged in louvre.Upper cover plate 201 opens up accommodating
The louvre of heat sink 202, particularly, in the both sides of the power supply part of fuselage roof louvre is respectively provided with, and is dissipated at two
Heat sink 202 is set in hot hole；Power supply part is rectangular block lithium battery, and in flight course, rectangular block lithium battery exists unmanned plane
The heat produced in first cavity volume is distributed by two heat sinks 202 of upper cover plate 201, makes the casing 2 possess good
Radiating effect.Heat sink 202 is the aluminium alloy web plate for opening up multiple passages；Aluminium alloy web plate is detachably mounted to louvre
Interior, used as a kind of preferred embodiment, aluminium alloy web plate coordinates with the louvre inner wall tightening of upper cover plate 201 to be realized fixing, peace
Assembly and disassembly are convenient and swift.Aluminium alloy web plate has lightweight, the characteristics of heat-conductive characteristic is excellent, on the one hand reduces unmanned plane entirety
Weight, on the other hand improve the heat dispersion of casing 2.
Further, the quantity of concave face 206 is two, respectively the first concave face and the second concave face；First depression
Face and the second concave face are respectively positioned at the both sides of upper cover plate 201；Casing 2 includes two blocks of heat sinks 202, respectively the first heat sink
And second heat sink；First concave face opens up the first louvre of accommodating first heat sink；Second concave face opens up accommodating second
Second louvre of heat sink.First louvre is arranged on the side of the power supply part of fuselage roof；Second louvre is arranged on
The opposite side of the power supply part of fuselage roof, power supply part be rectangular block lithium battery, unmanned plane in flight course, rectangular block lithium
The heat that battery is produced in the first cavity volume is distributed by the first heat sink and the second heat sink, makes the casing 2 possess good
Good radiating effect.
One or more technical schemes provided herein, at least have the following technical effect that or advantage：
As a result of the double-support foot stand 5 that the support that fuselage both sides are symmetricly set on by two is constituted, strengthen foot rest knot
The stability of strutting system of structure, can resist the large impact power produced when heavy load unmanned plane lands, and ensure the stationarity of unmanned plane landing
And positional accuracy；Unmanned plane in flight course, shoot with video-corder by the image information hung in the gondola being located on fuselage bottom installing plate
Component retrieval image information, is mounted opposite plate upset, it is to avoid the support of double-support foot stand 5 is blocked by driver part driving arm
Image information shoots with video-corder part, and then makes unmanned function obtain omnibearing image information.Meanwhile, dock by drain pan and with drain pan solid
The casing 2 of the upper casing composition of fuselage is wrapped up after fixed, drain pan and upper casing are fixed by hasp connection, facilitate casing fast assembling-disassembling.On
Shell is included after top is arched upward and forms the upper cover plate 201 of the first cavity volume, and arranges what oriented fuselage interior was drawn close in upper cover plate 201
Concave face 206, concave face 206 opens up louvre, when unmanned plane works in rainwater environment, slides from the top of upper cover plate 201
Rainwater can enter the top of concave face 206 and directly drop to the lower section of louvre and enters louvre without stream, when unmanned plane advances, upper lid
The rainwater of plate 201 can be slipped to the bottom of casing 2 from the top of upper cover plate 201 directly around concave face 206, be prevented effectively from rainwater and lead to
Louvre is crossed into the part in the inside of casing 2 infringement fuselage, the water resistance of unmanned plane is significantly improved.The shape of upper cover plate 201
Into the first cavity volume position it is corresponding with the power supply part position of fuselage roof, be respectively provided with the position of power supply part both sides
One heat sink and the second heat sink, significantly enhance the radiating effect of unmanned plane casing 2.So, prior art is efficiently solved
The stability of strutting system of middle conventional foot rest is poor, there is foot rest during landing because large impact causes itself deformation or even damages wind
Danger, casing structure is difficult the quick technical problem for realizing installation and removal, realizes enhancing foot rest stability of strutting system, ensures nobody
Machine stable landing, it is ensured that unmanned plane can smoothly obtain omnidirectional image information in flight course, casing energy fast assembling-disassembling is lifted
Unmanned plane water resistance, it is to avoid produce the technique effect of fuselage immersion failure.
Above-described specific embodiment, has been carried out further to the purpose of the present invention, technical scheme and beneficial effect
Describe in detail, should be understood that the specific embodiment that the foregoing is only the present invention, be not limited to this
Bright, all any modification, equivalent substitution and improvements within the spirit and principles in the present invention, done etc. should be included in the present invention
Protection domain within.
Claims (10)
1. a kind of casing fast disassembly type unmanned plane, the casing fast disassembly type unmanned plane includes：Rotor, rotor shaft, rotor drive component,
Gondola and flight control system, the rotor is fixedly connected with the rotor shaft；The rotor drive component and the rotor shaft
It is fixedly connected, to drive the rotor shaft and the rotor wing rotation to provide lift as the unmanned plane；Characterized in that, the machine
Shell fast disassembly type unmanned plane also includes：
Fuselage；It is mounted with image information and shoots with video-corder the gondola of part and hangs and be located on the installing plate of the fuselage bottom；It is described to fly
Row set-up of control system is on the fuselage；
Horn；One end of the horn is hinged with the installing plate of the fuselage bottom, and the other end connects with the rotor drive component
Connect；
Double-support foot stand, is arranged on the installing plate of the fuselage bottom；The double-support foot stand includes：Two are symmetricly set on
The support of the fuselage both sides and two driver parts being connected with the support；The support includes：One end and the installation
Plate may be reversed the first supporting leg of connection, one end and the second supporting leg that the installing plate is hinged, the parallel installing plate and while with
The first bottom bar that the other end of the other end of first supporting leg and second supporting leg is fixedly connected；
Casing；The casing includes：The drain pan that is fixedly connected with the installing plate and dock with the drain pan it is fixed after wrap up institute
State the upper casing of fuselage；The drain pan includes：The base plate that stretches out and formed from the surrounding of the installing plate and by the base plate
The first enclosing for being bent to form of outer；The upper casing includes：Top forms the upper cover plate of the first cavity volume and by described after arching upward
What the outer of upper cover plate was bent to form can be with first enclosing with the second suitable enclosing；It is arranged on the power supply of the fuselage roof
Part is located in first cavity volume；Second enclosing is connected by several hasps with first enclosing.
2. casing fast disassembly type unmanned plane as claimed in claim 1, it is characterised in that
First supporting leg is hinged by the first overturning seat with the installing plate；
First overturning seat is fixed on the installing plate outer lower section；
One end of first supporting leg is hinged by rotating shaft with first overturning seat；
First overturning seat is hinged with the first flip piece；
First flip piece is hinged with the second flip piece；
Second flip piece is hinged with first supporting leg；
Wherein, the pin joint of second flip piece and first supporting leg is located between the two-end-point of first supporting leg.
3. casing fast disassembly type unmanned plane as claimed in claim 2, it is characterised in that
The driver part is arranged on first overturning seat；
The output end of the driver part is connected with first flip piece, to drive first flip piece to turn over around described first
Turn part to rotate with the pin joint of first overturning seat.
4. casing fast disassembly type unmanned plane as claimed in claim 1, it is characterised in that
First supporting leg is fixedly connected by the first connector with first bottom bar；
First connector includes：With the first leg ends matching form fit the first sleeve and for first bottom bar
The first through hole for passing through；
The first set jacket casing is located at the end of first supporting leg and is fixedly connected by screw；
First bottom bar is located in the first through hole of first connector and solid with first connector by screw
It is fixed.
5. casing fast disassembly type unmanned plane as claimed in claim 1, it is characterised in that
Second supporting leg be arranged in parallel with first supporting leg；
One end of second supporting leg is hinged with the installing plate, can follow the relatively described installing plate upset of first supporting leg；
Second supporting leg is fixedly connected by the second connector with first bottom bar；
Second connector includes：With the second leg ends matching form fit second sleeve and for first bottom bar
The second through hole for passing through；
The second sleeve is set in the end of second supporting leg and is fixedly connected by screw；
First bottom bar is located in the second through hole of second connector and solid with second connector by screw
It is fixed.
6. casing fast disassembly type unmanned plane as claimed in claim 1, it is characterised in that
The casing opens up the pilot hole being connected with the installing plate for the horn；
The fixed seat being fixedly connected with the installing plate is set in the pilot hole；
The end of the horn is hinged by rotating shaft with the fixed seat；
The end of the horn is connected with positioning wedged block；
Wherein, the horn is flipped up to after operating position, and the positioning wedged block coordinates the horn with the fixed seat
It is limited to the operating position；Now, plate face of the rotation axis of the rotor perpendicular to the installing plate.
7. casing fast disassembly type unmanned plane as claimed in claim 6, it is characterised in that
The horn includes：Hollow carbon fiber pipe, the pipe box for being socketed in described carbon fiber pipe one end and with the carbon fiber pipe
The assembling block that the other end is fixedly connected；
The end of the pipe box is connected with articulated slab；
The articulated slab is hinged by the rotating shaft with the fixed seat；
The positioning wedged block is fixed on the articulated slab；
The pipe box is fastened with the carbon fiber pipe by screw；
The rotor drive component is fixed on the assembling block.
8. casing fast disassembly type unmanned plane as claimed in claim 1, it is characterised in that
The hasp includes：The button that is arranged on second enclosing and being arranged on first enclosing is matched somebody with somebody with the button
The projection of conjunction；
Second enclosing is connected by 2 hasps with first enclosing；
2 hasps are separately positioned on the both sides of the casing.
9. casing fast disassembly type unmanned plane as claimed in claim 1, it is characterised in that
The upper cover plate arranges the concave face that the oriented fuselage interior is drawn close；
The concave face opens up louvre；
The casing also includes：Heat sink；
The heat sink is detachably arranged in the louvre.
10. casing fast disassembly type unmanned plane as claimed in claim 9, it is characterised in that
The quantity of the concave face is two, respectively the first concave face and the second concave face；
First concave face and second concave face are respectively positioned at the both sides of the upper cover plate；
The casing includes two blocks of heat sinks, respectively the first heat sink and the second heat sink；
First concave face opens up the first louvre of accommodating first heat sink；
Second concave face opens up the second louvre of accommodating second heat sink；
First louvre is arranged on the side of the power supply part of the fuselage roof；
Second louvre is arranged on the opposite side of the power supply part of the fuselage roof.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611269864.9A CN106628151B (en) | 2016-12-30 | 2016-12-30 | Casing fast disassembly type unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611269864.9A CN106628151B (en) | 2016-12-30 | 2016-12-30 | Casing fast disassembly type unmanned plane |
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| Publication Number | Publication Date |
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| CN106628151A true CN106628151A (en) | 2017-05-10 |
| CN106628151B CN106628151B (en) | 2019-11-19 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201611269864.9A Expired - Fee Related CN106628151B (en) | 2016-12-30 | 2016-12-30 | Casing fast disassembly type unmanned plane |
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Cited By (3)
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| CN109407684A (en) * | 2017-08-18 | 2019-03-01 | 昊翔电能运动科技(昆山)有限公司 | Rotor wing unmanned aerial vehicle attitude control method and system |
| WO2021196138A1 (en) * | 2020-03-31 | 2021-10-07 | 南京达索航空科技有限公司 | Heat dissipation device for cabin of unmanned aerial vehicle |
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|---|---|
| CN106628151B (en) | 2019-11-19 |
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