CN107745810A - A kind of unmanned plane - Google Patents
A kind of unmanned plane Download PDFInfo
- Publication number
- CN107745810A CN107745810A CN201710973096.3A CN201710973096A CN107745810A CN 107745810 A CN107745810 A CN 107745810A CN 201710973096 A CN201710973096 A CN 201710973096A CN 107745810 A CN107745810 A CN 107745810A
- 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.)
- Withdrawn
Links
- 238000009434 installation Methods 0.000 claims description 10
- 125000004122 cyclic group Chemical group 0.000 claims description 3
- 230000005611 electricity Effects 0.000 claims 2
- 230000000630 rising effect Effects 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000012544 monitoring process Methods 0.000 description 1
- 239000011435 rock Substances 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
-
- 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
- B64C25/24—Operating mechanisms electric
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- 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)
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, it is provided with inside installs case inside the fuselage installs case described in control system and 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 is 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
The present invention is that the number of patent application that applicant proposed on December 23rd, 2015 is " 201510978186.2 ", title
For a kind of divisional application of the Chinese invention patent application of " unmanned plane ", entire contents are incorporated among the application.
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 (2)
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；It is described
Fuselage（1）Battery is installed inside installs case（21）, described installs case electric pushrod（15）, front-wheel rises and falls electric pushrod
（17）, trailing wheel rises and falls electric pushrod（20）, preceding rotor motor（22）, middle rotor motor（19）, rear rotor motor（9）, the sidespin wing
Motor（7）Pass through circuit and fuselage respectively（1）Control system inside installs case（11）And battery（21）It is connected；Described machine
Head（4）Bottom is provided with camera（12）；Two described flanks（2）Length direction and fuselage（1）Length direction between
Angle be 60 degree ~ 80 degree.
A kind of 2. 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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710973096.3A CN107745810A (en) | 2015-12-23 | 2015-12-23 | A kind of unmanned plane |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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 drone |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510978186.2A Division CN105501440B (en) | 2015-12-23 | 2015-12-23 | a drone |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107745810A true CN107745810A (en) | 2018-03-02 |
Family
ID=55709847
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710973096.3A Withdrawn CN107745810A (en) | 2015-12-23 | 2015-12-23 | A kind of unmanned plane |
| CN201510978186.2A Expired - Fee Related CN105501440B (en) | 2015-12-23 | 2015-12-23 | a drone |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510978186.2A Expired - Fee Related CN105501440B (en) | 2015-12-23 | 2015-12-23 | a drone |
Country Status (1)
| Country | Link |
|---|---|
| CN (2) | CN107745810A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114248912A (en) * | 2020-09-22 | 2022-03-29 | 海鹰航空通用装备有限责任公司 | Undercarriage folding and unfolding and cabin door linkage mechanism for small-sized fixed wing unmanned aerial vehicle |
Families Citing this family (8)
| 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 |
| CN106741933B (en) * | 2017-02-09 | 2023-04-18 | 金陵科技学院 | Amphibious unmanned aerial vehicle |
| 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 |
| CN111056009A (en) * | 2020-01-07 | 2020-04-24 | 北京致媒科技有限公司 | A search and rescue drone |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN101767649B (en) * | 2010-01-29 | 2012-07-18 | 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 |
| US20150274289A1 (en) * | 2014-03-31 | 2015-10-01 | The Boeing Corporation | Vertically landing aircraft |
-
2015
- 2015-12-23 CN CN201710973096.3A patent/CN107745810A/en not_active Withdrawn
- 2015-12-23 CN CN201510978186.2A patent/CN105501440B/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114248912A (en) * | 2020-09-22 | 2022-03-29 | 海鹰航空通用装备有限责任公司 | Undercarriage folding and unfolding and cabin door linkage mechanism for small-sized fixed wing unmanned aerial vehicle |
| CN114248912B (en) * | 2020-09-22 | 2024-06-11 | 海鹰航空通用装备有限责任公司 | Landing gear retracting and cabin door linkage mechanism for small fixed wing unmanned aerial vehicle |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105501440B (en) | 2018-02-06 |
| CN105501440A (en) | 2016-04-20 |
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|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20180302 |