CN105501440B - A kind of unmanned plane - Google Patents

A kind of unmanned plane Download PDF

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Publication number
CN105501440B
CN105501440B CN201510978186.2A CN201510978186A CN105501440B CN 105501440 B CN105501440 B CN 105501440B CN 201510978186 A CN201510978186 A CN 201510978186A CN 105501440 B CN105501440 B CN 105501440B
Authority
CN
China
Prior art keywords
fuselage
wheel
electric pushrod
installs case
rotor
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
CN201510978186.2A
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Chinese (zh)
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CN105501440A (en
Inventor
尤凯涛
孙需要
宁振雷
李清
李天水
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Beijing union Taida Technology Co., Ltd.
Beijing Research Institute of Precise Mechatronic Controls
Original Assignee
Beijing Union Taida Technology Co Ltd
Beijing Research Institute of Precise Mechatronic Controls
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Beijing Union Taida Technology Co Ltd, Beijing Research Institute of Precise Mechatronic Controls filed Critical Beijing Union Taida Technology Co Ltd
Priority to CN201510978186.2A priority Critical patent/CN105501440B/en
Publication of CN105501440A publication Critical patent/CN105501440A/en
Application granted granted Critical
Publication of CN105501440B publication Critical patent/CN105501440B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C27/00Rotorcraft; Rotors peculiar thereto
    • B64C27/22Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
    • B64C27/26Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C27/00Rotorcraft; Rotors peculiar thereto
    • B64C27/22Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
    • B64C27/28Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C25/00Alighting gear
    • B64C25/02Undercarriages
    • B64C25/08Undercarriages non-fixed, e.g. jettisonable
    • B64C25/10Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
    • B64C25/18Operating mechanisms
    • B64C25/24Operating mechanisms electric
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C2201/00Unmanned aerial vehicles; Equipment therefor
    • B64C2201/02Unmanned aerial vehicles; Equipment therefor characterized by type of aircraft
    • B64C2201/021Airplanes, i.e. having wings and tail planes
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C2201/00Unmanned aerial vehicles; Equipment therefor
    • B64C2201/04Unmanned aerial vehicles; Equipment therefor characterised by type of power plant
    • B64C2201/042Unmanned aerial vehicles; Equipment therefor characterised by type of power plant by electric motors; Electric power sources therefor, e.g. fuel cells, solar panels or batteries
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C2201/00Unmanned aerial vehicles; Equipment therefor
    • B64C2201/10Unmanned aerial vehicles; Equipment therefor characterised by the lift producing means
    • B64C2201/108Unmanned aerial vehicles; Equipment therefor characterised by the lift producing means using rotors, or propellers
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C2201/00Unmanned aerial vehicles; Equipment therefor
    • B64C2201/12Unmanned aerial vehicles; Equipment therefor adapted for particular use
    • B64C2201/127Unmanned aerial vehicles; Equipment therefor adapted for particular use for photography, or video recording, e.g. by using cameras

Abstract

The present invention discloses a kind of unmanned plane, including head, fuselage, tail, two flanks, it is characterised in that:Described head is fixedly mounted on fuselage end, and described tail is fixedly mounted on afterbody, and head, fuselage, the length direction of tail are located on the same line;Two described flanks are respectively and fixedly installed to fuselage both sides;Waist is provided with installs case, fuselage installs case internal-internal described in control system is installed inside installs case battery is installed, described installs case electric pushrod, front-wheel rise and fall electric pushrod, preceding rotor motor, middle rotor motor, rear rotor motor, side rotor motor of electric pushrod, trailing wheel of rising and falling are connected by circuit with the control system inside fuselage installs case and battery respectively.The present invention can smoothly be run, and can be adjusted rise and fall electric pushrod, trailing wheel of front-wheel in real time and be risen and fallen the stroke of electric pushrod, can adapt to different landform.

Description

A kind of unmanned plane
Technical field
The present invention relates to aircraft, and in particular to a kind of unmanned plane, belongs to flight mechanical equipment technical field.
Background technology
With the continuous development of scientific technology, in recent years, unmanned air vehicle technique is greatly improved, and many intelligence occurs The unmanned vehicle of energyization, multifunction, but unmanned air vehicle technique still has some problems, such as flight course is unstable, The process of rising and falling, which is also easy to produce, rocks.
The content of the invention
In view of the above-mentioned problems, the present invention provides a kind of unmanned plane, its by before, during and after setting, left and right symmetrical expression power Source, realize the purpose to be operated steadily under unmanned plane high-speed flight.
The technical scheme that the present invention takes is:A kind of unmanned plane, including head, fuselage, tail, two flanks, its feature It is:Described head is fixedly mounted on fuselage end, and described tail is fixedly mounted on afterbody, head, fuselage, tail Length direction be located on the same line;Two described flanks are respectively and fixedly installed to fuselage both sides;Before described fuselage Portion and rear portion are respectively arranged with is arranged on fore-body with the orthogonal mounting hole in fuselage length direction, described preceding rotor In mounting hole, axis and the mounting hole centerline collineation of preceding rotor, preceding mast are fixedly and coaxially connected with preceding rotor motor;Institute The middle rotor stated is arranged in the mounting hole of fuselage afterbody, axis and the mounting hole centerline collineation of middle rotor, middle mast It is fixedly and coaxially connected with middle rotor motor;Waist is provided with installs case, and control system, installs case are provided with inside installs case Top is provided with installation case lid, described installation case lid downside and the be hinged installation in top of installs case electric pushrod, described peace The bottom of vanning electric pushrod is hingedly mounted on installs case bottom;It is respectively arranged with and shoulder length side on two described flanks To orthogonal mounting hole, the sidespin wing, the axis and mounting hole of the sidespin wing are separately installed with the mounting hole on two flanks Centerline collineation, side mast are fixedly connected with sidespin wing motor coaxle;Two flanks have been respectively arranged below two front-wheels Mounting bracket, it is hinged on front-wheel mounting bracket and front wheel carrier is installed, front-drive is arranged on front wheel carrier, and described front-wheel rises and falls electronic The bottom of push rod is hingedly mounted on front-wheel mounting bracket, and front-wheel rises and falls and is hingedly mounted on front wheel carrier at the top of electric pushrod;Institute The underbelly stated is provided with trailing wheel mounting bracket, is hinged on trailing wheel mounting bracket and is provided with rear wheel frame, rear wheel is arranged on trailing wheel On frame, the rise and fall bottom of electric pushrod of described trailing wheel is hingedly mounted on trailing wheel mounting bracket, and trailing wheel rises and falls the top of electric pushrod Portion is hingedly mounted on rear wheel frame;Described tail is cyclic structure, rotor after being symmetrically arranged with two in tail, after described The axis of rotor is parallel to each other with fuselage length direction, and rear mast is fixedly and coaxially connected with rear rotor motor.
Battery is installed inside described fuselage installs case, described installs case electric pushrod, front-wheel rise and fall electric pushrod, Trailing wheel rises and falls electric pushrod, preceding rotor motor, middle rotor motor, rear rotor motor, side rotor motor respectively by circuit and machine Control system inside body installs case is connected with battery.
Further, described head bottom is provided with camera.
Further, the angle between the described length direction of two flanks and the length direction of fuselage is 60 degree ~ 80 Degree.
Further, rise and fall electric pushrod, trailing wheel of described front-wheel rises and falls and is provided with pressure sensor on electric pushrod, can To monitor the contact between front wheels and rear wheels and ground in real time.
There is advantages below because present invention employs above-mentioned technical proposal, the present invention:(1)Before the present invention is by being provided with Rotor motor, middle rotor motor, rear rotor motor, side rotor motor, the symmetrical power source equalization setting of unmanned plane is realized, so as to Can smoothly it run;(2)Risen and fallen electric pushrod by being provided with rise and fall electric pushrod, trailing wheel of front-wheel, it is installed above Pressure sensor can monitor the contact between front-wheel, trailing wheel and ground in time, so as to which adjustment front-wheel rises in real time respectively Fall electric pushrod, trailing wheel rises and falls the stroke of electric pushrod, i.e., sensed well by monitoring technology and solve unmanned plane and rise and fall The problem of unstable, different landform can be adapted to.
Brief description of the drawings
Fig. 1 is the overall assembling dimensional structure diagram of the present invention.
Fig. 2 is the overall assembling dimensional structure diagram of another angle of the present invention.
Fig. 3 is the overall assembling dimensional structure diagram of another angle of the present invention.
Drawing reference numeral:1- fuselages;2- flanks;3- tails;4- heads;5- front-wheels;The 6- sidespin wings;7- sides rotor motor;8- Trailing wheel;Rotor motor after 9-;Rotor in 10-;11- control systems;12- cameras;13- installs case lid;Rotor before 14-;15- pacifies Vanning electric pushrod;Rotor after 16-;17- front-wheels rise and fall electric pushrod;18- front-wheel mounting brackets;Rotor motor in 19-;After 20- Take turns the electric pushrod that rises and falls;21- batteries;Rotor motor before 22-;23- trailing wheel mounting brackets.
Embodiment
With reference to specific embodiment, the invention will be further described, the illustrative examples and explanation invented herein For explaining the present invention, but it is not as a limitation of the invention.
As shown in Figure 1, Figure 2, Figure 3 shows, a kind of unmanned plane, including 3, two head 4, fuselage 1, tail flanks 2, head 4 are solid Dingan County is mounted in the end of fuselage 1, and described tail 3 is fixedly mounted on the afterbody of fuselage 1, head 4, fuselage 1, the length direction of tail 3 It is located on the same line.Two flanks 2 are respectively and fixedly installed to the both sides of fuselage 1.The front and rear of fuselage 1 be respectively arranged with The orthogonal mounting hole of the length direction of fuselage 1, preceding rotor 14 are arranged in the anterior mounting hole of fuselage 1, the axle of preceding rotor 14 Line and mounting hole centerline collineation, the preceding main shaft of rotor 14 are fixedly and coaxially connected with preceding rotor motor 22.Middle rotor 10 is arranged on machine In the mounting hole at the rear portion of body 1, the axis of middle rotor 10 and mounting hole centerline collineation, the middle main shaft of rotor 10 and middle rotor motor 19 It is fixedly and coaxially connected.The middle part of fuselage 1 is provided with installs case, and control system 11 is provided with inside installs case, is set at the top of installs case There are installation case lid 13, the downside of installation case lid 13 and the be hinged installation in top of installs case electric pushrod 15, installs case electric pushrod 15 Bottom be hingedly mounted on installs case bottom.It is respectively arranged with two flanks 2 and the orthogonal installation of the length direction of flank 2 Hole, the sidespin wing 6, axis and the mounting hole centerline collineation of the sidespin wing 6, side are separately installed with the mounting hole on two flanks 2 The main shaft of rotor 6 is fixedly and coaxially connected with side rotor motor 7.Two flanks 2 have been respectively arranged below two front-wheel mounting brackets 18, preceding It is hinged on wheel mounting bracket 18 and front wheel carrier is installed, front-wheel 5 is rotatably installed on front wheel carrier, and front-wheel rises and falls the bottom of electric pushrod 17 It is hingedly mounted on front-wheel mounting bracket 18, the rise and fall top of electric pushrod 17 of front-wheel is hingedly mounted on front wheel carrier.The bottom of fuselage 1 Trailing wheel mounting bracket 23 is provided with, is hinged on trailing wheel mounting bracket 23 and rear wheel frame is installed, trailing wheel 8 is rotatably installed on rear wheel frame, after The rise and fall bottom of electric pushrod 20 of wheel is hingedly mounted on trailing wheel mounting bracket 23, and trailing wheel rises and falls the be hinged peace in top of electric pushrod 20 On rear wheel frame.Tail 3 is cyclic structure, rotor 16 after being symmetrically arranged with two in tail 3, the axis and machine of rear rotor 16 The length direction of body 1 is parallel to each other, and the rear main shaft of rotor 16 is fixedly and coaxially connected with rear rotor motor 9.
Battery 21 is installed, installs case electric pushrod 15, front-wheel rise and fall electric pushrod 17, trailing wheel inside the installs case of fuselage 1 Electric pushrod 20, preceding rotor motor 22, middle rotor motor 19, rear rotor motor 9, the side rotor motor 7 of rising and falling pass through circuit respectively It is connected with the control system 11 inside the installs case of fuselage 1 and battery 21.
The bottom of head 4 is provided with camera 12.Folder between the length direction of two flanks 2 and the length direction of fuselage 1 Angle is 60 degree ~ 80 degree.Rise and fall electric pushrod 17, trailing wheel of front-wheel rises and falls and is provided with pressure sensor, Ke Yishi on electric pushrod 20 When monitor contact between front-wheel 5 and trailing wheel 8 and ground.
The present invention operation principle be:Controlled in the use of the present invention, being sent first by remote control to control system 11 Signal, then by controlling, two front-wheels rise and fall electric pushrod 17 and the trailing wheel electric pushrod 20 that rises and falls falls front-wheel 5 and trailing wheel 8 Under, unmanned plane is taken action on different ground, and rotor motor 22, middle rotor motor 19, side rotor motor 7 before unlatching, before making 10, two rotor 14, middle rotor flanks 2 move, and form four rotors so that the present invention is raised to certain altitude, can now pass through Control system 11 to two front-wheels rises and falls electric pushrod 17 and trailing wheel rises and falls, and electric pushrod 20 sends signal by front-wheel 5 and trailing wheel 8 Withdraw, and simultaneously close off preceding rotor motor 22, middle rotor motor 19, side rotor motor 7, rotor motor 9, makes the present invention after unlatching Flown as Fixed Wing AirVehicle.During unmanned plane during flying, control system 11 can be entered by camera 12 at any time Row captured in real-time, and send information to control centre.

Claims (4)

1. a kind of unmanned plane, including head(4), fuselage(1), tail(3), two flanks(2), it is characterised in that:Described machine Head(4)It is fixedly mounted on fuselage(1)End, described tail(3)It is fixedly mounted on fuselage(1)Afterbody, head(4), fuselage (1), tail(3)Length direction be located on the same line;Two described flanks(2)It is respectively and fixedly installed to fuselage(1) Both sides;Described fuselage(1)Front and rear is respectively arranged with and fuselage(1)The orthogonal mounting hole of length direction, preceding rotation The wing(14)Installed in fuselage(1)In anterior mounting hole, preceding rotor(14)Axis and mounting hole centerline collineation, preceding rotor (14)Main shaft and preceding rotor motor(22)It is fixedly and coaxially connected;Middle rotor(10)Installed in fuselage(1)In the mounting hole at rear portion, in Rotor(10)Axis and mounting hole centerline collineation, middle rotor(10)Main shaft and middle rotor motor(19)It is fixedly and coaxially connected; Fuselage(1)Middle part is provided with installs case, and control system is provided with inside installs case(11), installs case top is provided with installation case lid (13), described installation case lid(13)Downside and installs case electric pushrod(15)The be hinged installation in top, described installs case electricity Dynamic push rod(15)Bottom be hingedly mounted on installs case bottom;Two described flanks(2)On be respectively arranged with and flank(2)It is long Spend the orthogonal mounting hole in direction, two flanks(2)On mounting hole in be separately installed with the sidespin wing(6), the sidespin wing(6)'s Axis and mounting hole centerline collineation, the sidespin wing(6)Main shaft and side rotor motor(7)It is fixedly and coaxially connected;Two flanks(2)Under Side is respectively arranged with two front-wheel mounting brackets(18), front-wheel mounting bracket(18)Upper be hinged is provided with front wheel carrier, front-wheel(5)Rotate peace On front wheel carrier, front-wheel rises and falls electric pushrod(17)Bottom be hingedly mounted on front-wheel mounting bracket(18)On, front-wheel rises and falls electricity Dynamic push rod(17)Top be hingedly mounted on front wheel carrier;Described fuselage(1)Bottom is provided with trailing wheel mounting bracket(23), trailing wheel Mounting bracket(23)Upper be hinged is provided with rear wheel frame, trailing wheel(8)It is rotatably installed on rear wheel frame, trailing wheel rises and falls electric pushrod(20)'s Bottom is hingedly mounted on trailing wheel mounting bracket(23)On, trailing wheel rises and falls electric pushrod(20)Top be hingedly mounted on rear wheel frame; Described tail(3)For cyclic structure, tail(3)Rotor after being inside symmetrically arranged with two(16), described rear rotor(16)'s Axis and fuselage(1)Length direction is parallel to each other, rear rotor(16)Main shaft and rear rotor motor(9)It is fixedly and coaxially connected;
Described fuselage(1)Battery is installed inside installs case(21), described installs case electric pushrod(15), front-wheel rises and falls electricity Dynamic push rod(17), trailing wheel rises and falls electric pushrod(20), preceding rotor motor(22), middle rotor motor(19), rear rotor motor(9)、 Side rotor motor(7)Pass through circuit and fuselage respectively(1)Control system inside installs case(11)And battery(21)It is connected.
A kind of 2. unmanned plane as claimed in claim 1, it is characterised in that:Described head(4)Bottom is provided with camera (12).
A kind of 3. unmanned plane as claimed in claim 1, it is characterised in that:Two described flanks(2)Length direction and machine Body(1)Length direction between angle be 60 degree ~ 80 degree.
A kind of 4. unmanned plane as claimed in claim 1, it is characterised in that:Described front-wheel rises and falls electric pushrod(17), trailing wheel Rise and fall electric pushrod(20)On pressure sensor is installed, front-wheel can be monitored in real time(5)And trailing wheel(8)Contact between ground Pressure.
CN201510978186.2A 2015-12-23 2015-12-23 A kind of unmanned plane Active CN105501440B (en)

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CN201710973096.3A CN107745810A (en) 2015-12-23 2015-12-23 A kind of unmanned plane
CN201510978186.2A CN105501440B (en) 2015-12-23 2015-12-23 A kind of unmanned plane

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CN105501440B true CN105501440B (en) 2018-02-06

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Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105905294B (en) * 2016-04-25 2018-05-01 北京中科遥数信息技术有限公司 VTOL fixed-wing unmanned plane
CN105711831B (en) * 2016-04-25 2018-03-06 长江大学 The fixed-wing unmanned plane of VTOL
CN107972861B (en) * 2017-11-22 2020-06-16 安徽天鹰兄弟无人机科技创新有限公司 Unmanned aerial vehicle
CN108263594B (en) * 2018-01-31 2019-05-10 曹蔚萌 A kind of bladeless fan power vertical take-off and landing drone
CN109292080A (en) * 2018-11-06 2019-02-01 深圳市富裕泰贸易有限公司 A kind of unmanned plane with foldable undercarriage
CN109292079A (en) * 2018-11-06 2019-02-01 深圳市富裕泰贸易有限公司 A kind of unmanned plane

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CN101767649A (en) * 2010-01-29 2010-07-07 中国航天空气动力技术研究院 Unmanned plane undercarriage control system
CN103832585A (en) * 2012-11-22 2014-06-04 上海市浦东新区知识产权保护协会 Cruise aircraft

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US20030062443A1 (en) * 2001-10-02 2003-04-03 Joseph Wagner VTOL personal aircraft
EP1831073A2 (en) * 2004-12-22 2007-09-12 Aurora Flight Sciences Corporation System and method for utilizing stored electrical energy for vtol aircraft thrust enhancement and attitude control
US20150274289A1 (en) * 2014-03-31 2015-10-01 The Boeing Corporation Vertically landing aircraft

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Publication number Priority date Publication date Assignee Title
CN101767649A (en) * 2010-01-29 2010-07-07 中国航天空气动力技术研究院 Unmanned plane undercarriage control system
CN103832585A (en) * 2012-11-22 2014-06-04 上海市浦东新区知识产权保护协会 Cruise aircraft

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CN105501440A (en) 2016-04-20

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Inventor after: Ning Zhenlei

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