CN106828867A - Noise-proofing formula unmanned plane - Google Patents
Noise-proofing formula unmanned plane Download PDFInfo
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- CN106828867A CN106828867A CN201611262896.6A CN201611262896A CN106828867A CN 106828867 A CN106828867 A CN 106828867A CN 201611262896 A CN201611262896 A CN 201611262896A CN 106828867 A CN106828867 A CN 106828867A
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- supporting leg
- unmanned plane
- installing plate
- noise
- fuselage
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- 229920003023 plastic Polymers 0.000 claims description 3
- 238000009434 installation Methods 0.000 claims description 2
- 239000007787 solid Substances 0.000 claims 2
- 230000007613 environmental effect Effects 0.000 abstract description 3
- 230000009467 reduction Effects 0.000 abstract description 2
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- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 4
- 229910052744 lithium Inorganic materials 0.000 description 4
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- 230000009471 action Effects 0.000 description 1
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Classifications
-
- 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
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/40—Sound or heat insulation, e.g. using insulation blankets
-
- 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
-
- 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
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
- B64C27/14—Direct drive between power plant and rotor hub
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/37—Rotors having articulated joints
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
- B64U2101/30—UAVs specially adapted for particular uses or applications for imaging, photography or videography
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
- Casings For Electric Apparatus (AREA)
Abstract
The present invention relates to noise-proofing formula unmanned plane, including：Fuselage, horn, double-support foot stand, casing and puigging.One end of horn is hinged with the installing plate of fuselage bottom, and the other end is connected with rotor drive component；Double-support foot stand includes：Two supports for being symmetricly set on fuselage both sides and two driver parts being connected with support；Support includes：One end may be reversed the first supporting leg for being connected, the second supporting leg that one end is hinged with installing plate, parallel mounting plates and the first bottom bar being fixedly connected with the other end of the first supporting leg and the other end of the second supporting leg simultaneously with installing plate；Casing includes：Drain pan and docked with drain pan it is fixed after wrap up the upper casing of fuselage；Drain pan includes：Base plate and the first enclosing being bent to form by the outer of base plate；Upper casing includes：Upper cover plate and the second enclosing being bent to form by the outer of upper cover plate；Puigging is arranged on the junction of the first enclosing and the second enclosing.Noise in the unmanned function reduction unmanned plane operation of the noise-proofing formula, reduces environmental noise pollution.
Description
Technical field
The present invention relates to unmanned air vehicle technique field, more particularly to noise-proofing formula 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 stool, so as to
In unmanned plane when landing, can be by its foot stool to aircraft standing support.The conventional foot stool of unmanned plane in the prior art
Stability of strutting system is poor, particularly when unmanned plane suspension relatively large load is landed, there is foot stool itself mechanism caused by large impact
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, existing unmanned plane operation noise is big, is not suitable with noise pollution requirement environment higher.
The content of the invention
The noise-proofing formula unmanned plane that the application is provided, solves or partly solves the support of conventional foot stool in the prior art
Less stable, the big technical problem of fuselage operation noise, realizes enhancing foot stool stability of strutting system, ensures that unmanned plane steadily drops
Fall, it is ensured that unmanned plane can smoothly obtain omnidirectional image information in flight course, reduce noise in unmanned plane operation, reduce ring
The technique effect of border noise pollution.
This application provides a kind of noise-proofing formula unmanned plane, the noise-proofing formula unmanned plane includes：Rotor, rotor shaft, rotation
Wing drive component, gondola and flight control system, the rotor are fixedly connected with the rotor shaft；The rotor drive component with
The rotor shaft is fixedly connected, to drive the rotor shaft and the rotor wing rotation to provide lift as the unmanned plane；It is described anti-
Noise formula 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
Flight control system is stated 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 is connected；
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 docked 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 formed after arching upward 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；
Puigging, is arranged on the junction of first enclosing and second 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：The first sleeve matched with the first leg ends shape and confession 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：The second sleeve matched with the second leg ends shape and confession 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 sleeve 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 sleeve 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 sleeve is fastened with the carbon fiber pipe by screw；
The rotor drive component is fixed on the assembling block.
Preferably, the power supply part of the fuselage roof is located in first cavity volume；
The base plate each extends over to form the first flat board area and the second flat board area from the two ends of the fuselage；
The drain pan is formed positioned at second cavity volume in the first flat board area and positioned at described the after being docked with the upper casing
3rd cavity volume in two flat board areas；
Wherein, second cavity volume and the 3rd cavity volume load the expansion module for being applied to the unmanned plane.
Preferably, the upper cover plate sets 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 puigging selects soft plastic material；
The puigging is bonded on the edge of first enclosing；
The gondola is fixed by screws in the lower section of the installing plate；
Described image information shoots with video-corder part for the weight no more than video camera of 5kg.
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, and being mounted opposite plate by driver part driving arm overturns, 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 comprehensive image information.Drain pan top is arranged on by by puigging
The first enclosing and upper casing bottom the second enclosing junction, effectively reduce the noise in unmanned plane running.So, have
The stability of strutting system that effect solves conventional foot stool in the prior art is poor, the big technical problem of fuselage operation noise, realizes increasing
Strong foot stool stability of strutting system, ensures unmanned plane stable landing, it is ensured that unmanned plane can smoothly obtain comprehensive figure in flight course
As information, noise in unmanned plane operation is reduced, reduce the technique effect of environmental noise pollution.
Brief description of the drawings
Fig. 1 is the general assembly drawing of noise-proofing formula unmanned plane provided in an embodiment of the present invention；
Fig. 2 is casing and the structural front view of double-support foot stand assembling in Fig. 1；
Fig. 3 is casing and the structure left view of double-support foot stand assembling in Fig. 1；
Fig. 4 is casing and the structural representation of horn assembling 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 stool, 6 first supports, 7 second supports, 8 hasps, 9 puiggings, 201 upper cover plates, 203 second enclosings, 204 base plates, 205 second
Enclosing, 206 concave faces, 207 second cavity volumes, 208 the 3rd cavity volumes, 401 fixed seats, 402 pipe sleeves, 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 piece, 606 second flip pieces, 607 first connectors, 608 anti-skidding buffering sheaths, 609 first extension springs, 610 first drive divisions
Part, 710 second driver parts)
Specific embodiment
The noise-proofing formula unmanned plane that the embodiment of the present application is provided, solves or part solves conventional foot stool in the prior art
Stability of strutting system it is poor, the fuselage operation big technical problem of noise is symmetricly set on by being set in fuselage bottom by two
The double-support foot stand of the support composition of fuselage both sides；By the first enclosing and upper casing bottom that puigging is arranged on drain pan top
The second enclosing junction；Enhancing foot stool stability of strutting system is realized, unmanned plane stable landing is ensured, it is ensured that unmanned plane is flying
Omnidirectional image information can be smoothly obtained during row, the technique effect of noise in unmanned plane operation is reduced.
Referring to attached Fig. 1 and 2, this application provides a kind of noise-proofing formula unmanned plane, the casing fast disassembly type unmanned plane includes：Rotation
The wing 1, rotor shaft, rotor drive component 3, gondola and flight control system, rotor 1 are fixedly connected with rotor shaft；Rotor driving group
Part 3 is fixedly connected with rotor shaft, and lift is provided to drive rotor shaft and rotor 1 to rotate to be unmanned plane；The casing fast disassembly type nobody
Machine also includes：Fuselage, horn 4, double-support foot stand 5, casing 2 and puigging 9.
It is mounted with image information and shoots with video-corder the gondola of part and hang on the installing plate for being located at fuselage bottom, particularly：Gondola leads to
Cross the lower section that screw is fixed on installing plate；Image information shoots with video-corder part for the weight no more than video camera of 5kg.Flight control system
It 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；Double branch
Kickstand 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 driver parts being connected with support；Support includes：One end may be reversed the first supporting leg, one end and the peace being connected with installing plate
The second supporting leg, parallel mounting plates and the other end fixation with the other end and the second supporting leg of the first supporting leg simultaneously that dress plate is hinged connect
The first bottom bar for connecing.Casing 2 includes：The drain pan that is fixedly connected with installing plate and docked with drain pan it is fixed after wrap up the upper of fuselage
Shell.Drain pan includes：The base plate 204 that stretches out and formed from the surrounding of installing plate and it is bent to form by the outer of base plate 204
First enclosing 205；Upper casing includes：Top forms the upper cover plate 201 of the first cavity volume and is bent by the outer of upper cover plate 201 after arching upward
Formation can be with the first enclosing 205 with the second suitable enclosing 203；Puigging 9 is arranged on the first enclosing 205 and the second enclosing 203
Junction.
Wherein, puigging 9 is arranged on first enclosing 205 on drain pan top and the company of the second enclosing 203 of upper casing bottom
Place is met, drain pan can be filled up with the space of upper casing junction, in unmanned plane running, the operation element of fuselage interior is good
Be wrapped in casing 2, effectively intercept the noise that fuselage interior element produces and outwards propagated with the connection gap of drain pan from upper casing,
The noise in unmanned plane running is reduced, reduces the noise pollution of environment.
Further, the second enclosing 203 is connected by several hasps 8 with the first enclosing 205；Hasp 8 includes：If
Put the button on the second enclosing 203 and be arranged on the first enclosing 205 projection with button cooperation.Realized by hasp 8
Shell and the connection of drain pan, make the disassembling operations of casing 2 easy and can guarantee that to be connected firmly.As a kind of preferred embodiment, the
Two enclosings 203 are connected by 2 hasps 8 with the first enclosing 205；2 hasps 8 are symmetrically arranged at the both sides of casing 2,
Ensure 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 and installing plate for connecing are hinged and simultaneously 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
Overturn the 3rd supporting leg of connection, the 4th supporting leg that one end and installing plate are hinged, parallel mounting plates and simultaneously another with the 3rd supporting leg
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, are overturn with driving the first supporting leg 601 and first support 6 to be mounted opposite plate；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 overturn.
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 by the second driver part 710 and overturn, it is to avoid foot stool is blocked
Image information shoots with video-corder part, and then unmanned function is obtained comprehensive 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, then realize the upset of the first supporting leg 601 and first support 6；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, unmanned function is obtained comprehensive 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 then drives the second flip piece 606 and the first supporting leg 601 to dig downwards, until first
Leg 601 is located at the second station, and now, first support 6 can stablize the unmanned plane that support and will land.
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, can turn over first support 6
Stabilization is in the operating position after playing 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 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 is connected.
Further, the first supporting leg 601 is fixedly connected by the first connector 607 with the first bottom bar 603；First connector
607 include the first sleeve matched with the end shape of the first supporting leg 601 and the first through hole passed 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, the first supporting leg 601 can be followed to be mounted opposite plate and overturn.Second supporting leg 602 is by the second connector and the
One bottom bar 603 is fixedly connected；Second connector includes the second sleeve that is 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 be rotated 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 then drives the 3rd flip piece and the 3rd supporting leg to dig upwards, 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 be rotated backward around the 3rd flip piece and the pin joint of the second overturning seat, then drive the 3rd flip piece and the 3rd supporting leg downward
Dig, until the 3rd supporting leg is located at the second station, now, second support 7 can stablize the unmanned plane that support and will land.
Further, the 3rd supporting leg is fixedly connected by the 3rd connector with the second bottom bar；3rd connector includes and the
3rd sleeve that three leg ends shapes match 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 and overturn.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.By setting the knot of 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 sleeve 402 and the assembling block 404 that is fixedly connected with the other end of carbon fiber pipe 406；The end of pipe sleeve 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 sleeve 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 small,
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 and and motor being connected with the power supply part of fuselage roof
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 wire 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 stool 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 stool 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 and drives with rotor shaft
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, the power supply part of fuselage roof is located in the first cavity volume；Base plate 204 from fuselage two
End each extends over to form the first flat board area and the second flat board area；Drain pan forms second positioned at the first flat board area after being docked with upper casing
Cavity volume 207 and the 3rd cavity volume positioned at the second flat board area
208；Second cavity volume 207 and the 3rd cavity volume 208 load the expansion module for being applied to unmanned plane.Wherein, the second cavity volume
207 and the 3rd cavity volume 208 be used to loading the expansion module for being applied to unmanned plane, the effective spare space of extension unmanned plane is improved
The space availability ratio of unmanned plane, improves the adaptability and upgradability energy of unmanned plane.
Further, referring to accompanying drawing 6, upper cover plate 201 sets 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 be through concave face 206
Top directly drops to the lower section of louvre without flowing into louvre, 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, is respectively provided with louvre, and dissipate at two in the both sides of the power supply part of fuselage roof
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, the casing 2 is possessed 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 casing 2 heat dispersion.
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, the casing 2 is possessed good
Good radiating effect.
Further, puigging 9 selects soft plastic material；Puigging 9 is bonded on the edge of the first enclosing 205,
Puigging 9 is fixed by way of bonding, it is firm to connect, and install and change all more convenient.
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 stool 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 and overturns, 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 unmanned function is obtained comprehensive image information.Meanwhile, puigging 9 is arranged on drain pan
First enclosing 205 on top and the junction of the second enclosing 203 of upper casing bottom, effectively making an uproar in reduction unmanned plane running
Sound.So, the stability of strutting system for efficiently solving conventional foot stool in the prior art is poor, there is foot stool during landing because large impact is made
Risk is even damaged into itself deformation, the big technical problem of fuselage operation noise realizes enhancing foot stool stability of strutting system,
Ensure unmanned plane stable landing, it is ensured that unmanned plane can smoothly obtain omnidirectional image information in flight course, reduce unmanned plane
The technique effect of noise in operation.
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 and the foregoing is only specific embodiment of the invention, be not limited to this hair
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 noise-proofing formula unmanned plane, the noise-proofing formula 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 is fixed with the rotor shaft
Connection, to drive the rotor shaft and the rotor wing rotation to provide lift as the unmanned plane；Characterized in that, the noise-proofing
Formula 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 simultaneously 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 docked 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；
Puigging, is arranged on the junction of first enclosing and second enclosing.
2. noise-proofing formula 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. noise-proofing formula 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 be turned over around described first
Turn part to be rotated with the pin joint of first overturning seat.
4. noise-proofing formula 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：The first sleeve and confession first bottom bar matched with the first leg ends shape
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. noise-proofing formula 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, and the relatively described installing plate of first supporting leg can be followed to overturn；
Second supporting leg is fixedly connected by the second connector with first bottom bar；
Second connector includes：The second sleeve and confession first bottom bar matched with the second leg ends shape
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. noise-proofing formula 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. noise-proofing formula unmanned plane as claimed in claim 6, it is characterised in that
The horn includes：Hollow carbon fiber pipe, the pipe sleeve 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 sleeve 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 sleeve is fastened with the carbon fiber pipe by screw；
The rotor drive component is fixed on the assembling block.
8. noise-proofing formula unmanned plane as claimed in claim 1, it is characterised in that
The power supply part of the fuselage roof is located in first cavity volume；
The base plate each extends over to form the first flat board area and the second flat board area from the two ends of the fuselage；
The drain pan is formed positioned at second cavity volume in the first flat board area and flat positioned at described second after being docked with the upper casing
3rd cavity volume in plate area；
Wherein, second cavity volume and the 3rd cavity volume load the expansion module for being applied to the unmanned plane.
9. noise-proofing formula unmanned plane as claimed in claim 1, it is characterised in that
The upper cover plate sets 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. noise-proofing formula unmanned plane as claimed in claim 1, it is characterised in that
The puigging selects soft plastic material；
The puigging is bonded on the edge of first enclosing；
The gondola is fixed by screws in the lower section of the installing plate；
Described image information shoots with video-corder part for the weight no more than video camera of 5kg.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201611262896.6A CN106828867B (en) | 2016-12-30 | 2016-12-30 | Noise-proofing formula unmanned plane |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611262896.6A CN106828867B (en) | 2016-12-30 | 2016-12-30 | Noise-proofing formula unmanned plane |
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| Publication Number | Publication Date |
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| CN106828867A true CN106828867A (en) | 2017-06-13 |
| CN106828867B CN106828867B (en) | 2019-05-14 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201611262896.6A Expired - Fee Related CN106828867B (en) | 2016-12-30 | 2016-12-30 | Noise-proofing formula unmanned plane |
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| CN107487432A (en) * | 2017-09-22 | 2017-12-19 | 贵州信鸽科技有限公司 | Unmanned vehicle and flight instruments |
| CN108609163A (en) * | 2018-04-10 | 2018-10-02 | 清远市巨劲科技有限公司 | A kind of mapping unmanned plane lifting shock bracket |
| CN109319085A (en) * | 2017-08-01 | 2019-02-12 | 广州极飞科技有限公司 | Based shell, rack and unmanned plane |
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| CN103318405A (en) * | 2013-07-17 | 2013-09-25 | 国家电网公司 | Unmanned plane |
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| CN205589470U (en) * | 2016-04-27 | 2016-09-21 | 深圳市智美达科技股份有限公司 | Unmanned aerial vehicle |
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|---|---|---|---|---|
| CN103318405A (en) * | 2013-07-17 | 2013-09-25 | 国家电网公司 | Unmanned plane |
| CN103754355A (en) * | 2014-01-10 | 2014-04-30 | 江苏艾锐泰克无人飞行器科技有限公司 | Retractable landing gear and unmanned aerial vehicle |
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| CN109319085A (en) * | 2017-08-01 | 2019-02-12 | 广州极飞科技有限公司 | Based shell, rack and unmanned plane |
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|---|---|
| CN106828867B (en) | 2019-05-14 |
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