CN207374652U - Unmanned plane - Google Patents
Unmanned plane Download PDFInfo
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- CN207374652U CN207374652U CN201721451704.6U CN201721451704U CN207374652U CN 207374652 U CN207374652 U CN 207374652U CN 201721451704 U CN201721451704 U CN 201721451704U CN 207374652 U CN207374652 U CN 207374652U
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- 238000000429 assembly Methods 0.000 claims abstract description 35
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- 238000006243 chemical reaction Methods 0.000 abstract description 5
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 description 5
- 238000010586 diagram Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 238000004064 recycling Methods 0.000 description 2
- 238000005096 rolling process Methods 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 1
- 229910018095 Ni-MH Inorganic materials 0.000 description 1
- 229910018477 Ni—MH Inorganic materials 0.000 description 1
- 241000276425 Xiphophorus maculatus Species 0.000 description 1
- 239000002253 acid Substances 0.000 description 1
- 239000000654 additive Substances 0.000 description 1
- OJIJEKBXJYRIBZ-UHFFFAOYSA-N cadmium nickel Chemical compound [Ni].[Cd] OJIJEKBXJYRIBZ-UHFFFAOYSA-N 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 229910052744 lithium Inorganic materials 0.000 description 1
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- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 201000009482 yaws Diseases 0.000 description 1
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Abstract
The utility model is related to a kind of unmanned planes.Above-mentioned unmanned plane includes fuselage body, photovoltaic module, power supply module, the wing components of plate and the multiple rotor assemblies that can be rotatably mounted on fuselage body, multiple rotor assemblies are electrically connected with power supply module, each rotor assemblies include vert bar and rotor, the bar that verts can be rotationally connected with fuselage body, rotor is fixedly connected with the bar that verts, so that rotor can be with the bar rotation that inclines.When taking off, rotor is capable of providing upward lift, and unmanned plane is made to go up to the air vertically；During cruise, the bar that verts, which verts, makes rotor assemblies provide the power to advance；During landing, the bar that verts, which verts, drives rotor to return to position when taking off, and realizes vertical drop.By above-mentioned conversion, unmanned plane is made both to have possessed fixed-wing unmanned plane during flying distance, the advantages such as flying speed is fast；The advantage of landing vertically can be capable of with rotor wing unmanned aerial vehicle when taking off and landing again.
Description
Technical field
The utility model is related to a kind of unmanned planes.
Background technology
Existing fixed-wing unmanned plane during flying speed is fast, and flying distance is remote, but the landing requirement height that takes off is, it is necessary to have specific
Place, and voyage is limited.
Utility model content
Based on this, it is necessary to which provide a kind of without particular requirement and can have longer cruising time to landing place of taking off
Unmanned plane.
A kind of unmanned plane, including：
Fuselage body；
Photovoltaic module is fixed on the fuselage body；
Power supply module is arranged in the fuselage body, and is electrically connected with the photovoltaic module；
The wing components of plate are fixedly connected with the fuselage body；And
The multiple rotor assemblies that can be rotatably mounted on the fuselage body, multiple rotor assemblies with it is described
Power supply module is electrically connected, and each rotor assemblies include vert bar and rotor, it is described vert bar can rotationally with the machine
Body body connects, and the rotor is fixedly connected with the bar that verts, so that the rotor can be with the bar rotation that inclines.
Due to being equipped with photovoltaic module on the fuselage body of above-mentioned unmanned plane, photovoltaic module can be in the worked of unmanned plane
It converts solar energy into electrical energy in journey, is charged with pair power supply module being electrically connected with photovoltaic module, there is unmanned plane longer
Cruising time；Wing components are fixedly connected with fuselage body, and unmanned plane is made to have under cruise mode, and flying distance is long, flight is fast
Degree is fast, flying height is high, course line can be set to fly automatically, the area that cruises is big and it is excellent that recycling point coordinates can be set to land automatically
Point；Rotor assemblies are fixedly connected with fuselage body, and rotor assemblies include verting bar and rotor, vert bar can rotationally with fuselage
Body connects, and rotor is fixedly connected with the bar that verts, the bar rotation so that rotor can incline at any time；When unmanned plane takes off, rotor
Upward lift for unmanned plane can be provided, unmanned plane is made to take off in the case where runway is not required；When being increased to desired height
When, the bar that verts verts the power that rotor assemblies is made to provide advance for unmanned plane；When unmanned plane lands, the bar that verts verts and makes
Rotor returns to position when taking off, and when so that the unmanned plane is landed, runway is not required directly to land.By above-mentioned conversion, make unmanned plane
Possesses fixed-wing unmanned plane during flying distance during operation in the air, the advantages such as flying speed is fast；There is rotation when taking off and landing
Wing unmanned plane is capable of the advantage of flexible landing.
In one of the embodiments, multiple rotor assemblies are separately positioned on the both sides of the fuselage body, and phase
The fuselage body is symmetrical arranged two-by-two.
In one of the embodiments, the bar that verts can drive the rotor rotational to the Plane of rotation of the rotor
It is vertical with vertical direction, and the bar that verts can also drive the rotor rotational to the rotor Plane of rotation with it is vertical
Direction is parallel.
In one of the embodiments, the rotor assemblies further include motor and governor, the motor and the rotor
Electrical connection, so that the motor can drive the rotor wing rotation, the governor and the motor, the power supply module are electric
Connection.
In one of the embodiments, the wing components include empennage, and the empennage includes vertical tail, described vertical
Empennage is fixedly connected with the fuselage body, and the vertical tail includes the vertically stable wing and rudder, the vertically stable wing
It is fixedly connected with the fuselage body, the rudder can be rotatably mounted on the vertically stable wing.
In one of the embodiments, the empennage further includes two tailplanes, and two tailplanes are with respect to institute
It states vertical tail to be symmetrical arranged, each tailplane includes the horizontal stable wing and elevator, the horizontal stable wing and institute
It states the vertically stable wing to be fixedly connected, the elevator can be rotatably mounted on the horizontal stable wing.
In one of the embodiments, the power supply module includes accumulator and controller, the controller and the storage
Battery is electrically connected, and the controller is electrically connected with the photovoltaic module.
In one of the embodiments, the power supply module further includes electric power source distribution device, and the rotor assemblies pass through described
Electric power source distribution device is electrically connected with the controller.
In one of the embodiments, the unmanned plane further includes undercarriage, and the undercarriage is fixed on the fuselage sheet
On body.
In one of the embodiments, the wing components can rotate, and the unmanned plane, which further includes, flies control component, described
Fly control component to be contained in inside the fuselage body, the winged control component and the bar that verts, the wing components are to be electrically connected
It connects, the winged control component can control the bar rotation that inclines, and the winged control component can also control the wing components to live
It is dynamic.
Description of the drawings
Fig. 1 is the unmanned plane structure diagram of an embodiment；
Fig. 2 is the circuit connection diagram of unmanned plane shown in FIG. 1；
Fig. 3 is the structure diagram of another state of unmanned plane shown in FIG. 1.
Specific embodiment
For the ease of understanding the utility model, the utility model is more fully retouched below with reference to relevant drawings
It states.The preferred embodiment of the utility model is given in attached drawing.But the utility model can come in many different forms
It realizes, however it is not limited to embodiment described herein.On the contrary, the purpose for providing these embodiments makes to the utility model
The understanding of disclosure more thorough and comprehensive.
It should be noted that when element is referred to as " being fixed on " another element, it can be directly on another element
Or it also can have element placed in the middle.When an element is considered as " connection " another element, it can be directly connected to
To another element or it may be simultaneously present centering elements.Term as used herein " vertical ", " horizontal ", " left side ",
" right side " and similar statement are for illustrative purposes only.
Unless otherwise defined, all of technologies and scientific terms used here by the article is led with belonging to the technology of the utility model
The normally understood meaning of technical staff in domain is identical.The term used herein in the book disclosed in the specification of the utility model
It is intended merely to the purpose of description specific embodiment, it is not intended that limitation the utility model.
As shown in Figures 1 and 2, the unmanned plane 10 of an embodiment includes fuselage body 100, undercarriage 200, power supply module
300th, photovoltaic module 400, wing components 500 and rotor assemblies 600.
100 generally cylindrical body of fuselage body.Fuselage body 100 is photovoltaic module 400, power supply module 300, wing components
500 and the fixed support structure of rotor assemblies 600.Fuselage body 100 includes cylindrical body 110 and is formed at cylindrical body 110
One end head 120.Further, head 120 is generally conical, and stub end and the cylindrical body 110 on head 120 are fixed
Connection.
Undercarriage 200 is arranged on the bottom of fuselage body 100, and is fixedly connected with fuselage body 100.Undercarriage 200 is used
Positive seat in the plane is kept when unmanned plane 10 is aided in take off or landing.
Power supply module 300 is arranged on fuselage body 100, and power supply module 300 is each electrical equipment in unmanned plane 10
Power supply.Power supply module 300 includes accumulator 320, controller 330 and electric power source distribution device 340.
Again chemical energy when external electric energy can be saved as chemical energy, it is necessary to discharge by accumulator 320 when charging
Electric energy output is converted to, electric power is provided for each electrical equipment.Specifically, accumulator 320 can be lead-acid battery, can also be
Ni-MH battery, nickel-cadmium cell or lithium battery.
Controller 330 is electrically connected with accumulator 320.Controller 330 can to the charging and discharging state of accumulator 320 into
Row control.Meanwhile controller 330 can carry out additives for overcharge protection and over to accumulator 320, can extend accumulator
320 service life.Controller 330 can control the circuit working state of 10 whole system of unmanned plane.
Electric power source distribution device 340 can convert the output voltage of accumulator 320, be divided by electric power source distribution device 340
The different utilization voltage demand of each electrical equipment can be met after processing.Wherein, electric power source distribution device 340 and 330 electricity of controller
Connection.
Photovoltaic module 400 is fixed on the outer surface of fuselage body 100, and in photovoltaic module 400 and power supply module 300
Controller 330 be electrically connected, photovoltaic module 400 can convert solar energy into electrical energy, can be under the control of controller 330
The obtainable electric energy of 400 conversion solar of photovoltaic module is stored in accumulator 320 in case use, and has unmanned plane 10
Longer cruising time.
Wing components 500 are platy structure, and wing components 500 are fixedly connected with fuselage body 100, wing components 500
It is electrically connected with power supply module 300.Wing components 500 can be movable, before can controlling unmanned plane 10 so as to wing components 500
Into direction.Wing components 500 include wing 520 and empennage 540.
Wing 520 is mounted on fuselage body 100, the aerofoil of wing 520 can activity to change the flight of unmanned plane 10
Posture, and wing 520 is electrically connected with electric power source distribution device 340.Wing 520 includes wing body 522 and aileron 524.
Wing body 522 forms the main body frame of wing 520, and external applied load is transmitted to fuselage body 100.
Aileron 524 is electrically connected with electric power source distribution device 340, and aileron 524 can be rotatably mounted on wing body 522, aileron
524 deflections, which can generate rolling moment, makes unmanned plane 10 that rolling occur.
Specifically in the illustrated embodiment, wing 520 is two, and two wings 520 are symmetrically disposed in fuselage body 100
Both sides, two wings 520 are trapezoidal harden structure, and the long base of trapezoidal plate is fixedly connected with fuselage body 100.
Empennage 540 is mounted on the one end of cylindrical body 110 away from head 120, and empennage 540 can control the inclined of unmanned plane 10
Turn, and ensure 10 smooth flight of unmanned plane, and empennage 540 is electrically connected with electric power source distribution device 340, empennage 540 and fuselage body 100
It is fixedly connected.Empennage 540 includes vertical tail 542 and tailplane 544.
Vertical tail 542 can be movable and carries out yaw steering to unmanned plane 10, while it is laterally quiet to have unmanned plane 10
Stability.Vertical tail 542 is arranged on the one end of cylindrical body 110 away from head 120.Vertical tail 542 and fuselage body 100
It is fixedly connected.Vertical tail 542 includes the vertically stable wing 5422 and rudder 5424.
Vertically the stable wing 5422 is fixedly connected with fuselage body 100.Specifically, the wing 5422 and cylindrical body are vertically stabilized
110 one end away from head 120 are fixedly connected.Vertically the stable wing 5422 makees approximate linear uniform motion in unmanned plane 10 along straight line
During flight, vertically the stable wing 5422 will not generate unmanned plane 10 additional torque.But when unmanned plane 10 is disturbed be subject to air-flow,
When head 120 deflects, the aerodynamic force that acts at this time on the vertical stable wing 5422 will generate one it is opposite with deflecting direction
Torque makes unmanned plane 10 be restored to original flight attitude.And unmanned plane 10 yaws more severe, vertically stabilizes 5422 institute of the wing
The righting moment of generation is bigger.
Rudder 5424 is electrically connected with electric power source distribution device 340, and rudder 5424 is rotatably mounted at the vertically stable wing 5424
On.Rudder 5424 can carry out yaw adjustment to unmanned plane 10.
Tailplane 544 can be movable and changes the pitch attitude of unmanned plane 10, while makes unmanned plane 10 in pitch orientation
It is upper that there is static stability.Tailplane 544 is two, and two tailplanes 544 are installed on vertical tail 542, and two
544 Relative vertical empennage 542 of tailplane is symmetrical arranged.Each tailplane includes the horizontal stable wing 5442 and elevator
5444。
The stable wing 5442 of level is fixedly connected with the vertical stable wing 5422.The stable wing 5442 of level can have unmanned plane 10
Static stability.When 10 horizontal flight of unmanned plane, the stable wing 5442 of level will not generate unmanned plane 10 additional torque；When
When the head 120 of unmanned plane 10 is steeved straight up, the aerodynamic force acted at this time on the horizontal stable wing 5442 will generate one
It is a to make the torque of unmanned plane 10 straight down, unmanned plane 10 is made to be restored to horizontal flight posture；Similarly, if unmanned plane 10
Portion 120 bows low straight down, then the torque that the horizontal stable wing 5442 generates will make unmanned plane 10 movable straight up, until extensive
Multiple horizontal flight.
Elevator 5444 is electrically connected with electric power source distribution device 340, and elevator 5444 is rotatably mounted on the horizontal stable wing.
Elevator 5444 can carry out unmanned plane 10 adjusting of pitch attitude.
Rotor assemblies 600 are multiple, and multiple rotor assemblies 600 are rotatably mounted on fuselage body 100, and multiple rotations
Wing component 600 is electrically connected with power supply module 300.Specifically, multiple rotor assemblies 600 are separately positioned on fuselage body 100
Both sides, and opposite fuselage body 100 is symmetrical arranged two-by-two.Specifically in the illustrated embodiment, rotor assemblies 600 are four.
Wherein, each rotor assemblies 600 include vert bar 610, pedestal 620, governor 630, motor 640 and rotor
650。
Vert one end of bar 610 can be rotatably installed on fuselage body 100.Specifically, the bar 610 that verts includes installation
Drive component (not shown) inside fuselage body 100 and the bar portion with drive component drive connection (figure is not marked).It is illustrating
Embodiment in, the surface of the fuselage body 100 of the bar portion of the bar 610 that verts of four rotor assemblies 600 with being contacted is vertical,
And partner two-by-two, on the same line, two pairs of bars 610 that vert are mutual for the bar portion per a pair of corresponding two bars 610 that vert
It is arranged in parallel.
Pedestal 620 is fixedly connected with the one end of bar 610 away from fuselage body 100 of verting.Specifically, pedestal 620 is with verting
The one end of the bar portion of bar 610 away from fuselage body 100 is fixedly connected.
Governor 630 is fixedly connected with pedestal 620, and governor 630 is electrically connected with electric power source distribution device 340.Specifically, speed governing
Device 630 can be electron speed regulator.
Motor 640 is fixedly connected with pedestal 620, and motor 640 is electrically connected with electric power source distribution device 340, and motor 640 and speed governing
Device 630 is electrically connected, and governor 630 can control the rotating speed of motor 640.
Rotor 650 is fixedly connected with motor 640.Motor 640 can drive rotor 650 to rotate, so as to be carried for unmanned plane 10
For flying power.Wherein, the bar 610 that verts can drive that rotor 650 turns to the Plane of rotation of rotor 650 and vertical direction hangs down
Directly, and the Plane of rotation that bar 610 can also drive rotor 650 to turn to rotor 650 that verts is parallel with vertical direction.
It should be noted that rotor assemblies 600 are not limited to four, it can also be six, eight or more, need to only reach
It realizes 10 flexible landing of unmanned plane and the purpose of the power of advance is provided for the flight of unmanned plane 10.
Fly control component 700 to be contained in inside fuselage body 100, the flight shape of unmanned plane 10 can be controlled by flying control component 700
State.Fly control component 700 and aileron 524, rudder 5424, elevator 5444, vert bar 610 and governor 630 is to be electrically connected
It connects.
Specifically, in the case where flying the control of control component 700, aileron 524 activity and can change shape, so as to increase lift or
Change the posture of unmanned plane 10.Rudder 5424 can carry out yaw adjustment in the case where flying the control of control component 700.Elevator 5444
The conversion of mixing 10 pitch attitude of unmanned plane can be controlled in the case where flying the control of control component 700.Flying control component 700 can also control
Drive component processed drives the bar 610 that verts to rotate, and according to the needs of particular job scene, passes through the bar 610 that verts and drives 650 turns of rotor
It is dynamic, the Plane of rotation of rotor 650 and the relative angle of vertical direction is made to change.According to the needs of actual conditions, fly control group
Part 700 can control governor 630 that the running speed of motor 640 is adjusted.
The working method of above-mentioned unmanned plane 10 is as follows：
In 10 takeoff phase of unmanned plane, the Plane of rotation of the rotor 650 in rotor assemblies 600 is vertical with vertical direction,
It please refers to Fig.1.Rotor 650 can rotate in the case where flying the control of control component 700 and upward lift is provided for unmanned plane 10, make nothing
Man-machine 10 take off in the case where runway is not required.When being increased to desired height, unmanned plane 10 enters cruise mode.At this point,
In the case where flying the control of control component 700, the rotation of the rotor 650 in rotor assemblies 600 between wing 520 and empennage 540
Plane remains vertical with vertical direction, and rotor 650 is stopped.And it is set close to the head 120 of fuselage body 100
Rotor assemblies 600 in the bar 610 that verts vert and make the Plane of rotation of rotor 650 parallel with vertical direction, be unmanned plane
10 provide the power to advance, refer to Fig. 3.In 10 landing phases of unmanned plane, in the case where flying the control of control component 700, close fuselage
The bar 610 that verts in the rotor assemblies 600 that the head 120 of body 100 is set vert make rotor 650 Plane of rotation and
Vertical direction is vertical, and the rotor 650 in rotor assemblies 600 between wing 520 and empennage 540 is started to work, and passes through tune
The posture of horizontal empennage 540 and the rotating speed of motor 640 make unmanned plane be not required runway that can land.
Above-mentioned unmanned plane 10 at least has further the advantage that：
(1) due to being equipped with photovoltaic module 400 on the fuselage body 100 of above-mentioned unmanned plane 10, photovoltaic module 400 can
It is converted solar energy into electrical energy in the course of work of unmanned plane 10, with pair power supply module being electrically connected with photovoltaic module 400
300 charge, and unmanned plane 10 is made to have longer cruising time；
(2) wing components 500 are fixedly connected with fuselage body 100, make unmanned plane 10 under cruise mode have flight away from
From length, flying speed is fast, flying height is high, course line can be set to fly automatically, the area that cruises is big and can set recycling point coordinates
The advantages of automatic landing；
(3) rotor assemblies 600 are fixedly connected with fuselage body 100, and rotor assemblies 600 include vert bar 610 and rotor
650, the bar 610 that verts can be rotationally connected with fuselage body 100, and rotor 650 is fixedly connected with the bar 610 that verts, so that rotor
650 bars 610 that can vert at any time rotate；When unmanned plane 10 takes off, rotor 650 can be that unmanned plane 10 provides upward liter
Power makes unmanned plane 10 take off rapidly in the case where runway is not required；When being increased to desired height, the bar 610 that verts inclines
Turn that rotor 650 is driven to rotate, the Plane of rotation power that advance is provided for unmanned plane 10 parallel with vertical direction of rotor 650；
When unmanned plane 10 lands, the bar 610 that verts, which verts, makes the Plane of rotation of rotor 650 vertical with vertical direction, makes unmanned plane 10 not
Need runway that can land.By above-mentioned conversion, make both to have possessed during the operation in the air of unmanned plane 10 fixed-wing unmanned plane during flying away from
From length, the advantages such as flying speed is fast；There is the advantage that rotor wing unmanned aerial vehicle is capable of flexible landing again when taking off and landing.
Each technical characteristic of embodiment described above can be combined arbitrarily, to make description succinct, not to above-mentioned reality
It applies all possible combination of each technical characteristic in example to be all described, as long as however, the combination of these technical characteristics is not deposited
In contradiction, the scope that this specification is recorded all is considered to be.
Embodiment described above only expresses the several embodiments of the utility model, and description is more specific and detailed,
But therefore it can not be interpreted as the limitation to utility model patent scope.It should be pointed out that the common skill for this field
For art personnel, without departing from the concept of the premise utility, various modifications and improvements can be made, these are belonged to
The scope of protection of the utility model.Therefore, the protection domain of the utility model patent should be determined by the appended claims.
Claims (10)
1. a kind of unmanned plane, which is characterized in that including：
Fuselage body；
Photovoltaic module is fixed on the fuselage body；
Power supply module is arranged on the fuselage body, and is electrically connected with the photovoltaic module；
The wing components of plate are fixedly connected with the fuselage body；And
The multiple rotor assemblies that can be rotatably mounted on the fuselage body, multiple rotor assemblies with the power supply
Component is electrically connected, and each rotor assemblies include vert bar and rotor, it is described vert bar can rotationally with the fuselage sheet
Body connects, and the rotor is fixedly connected with the bar that verts, so that the rotor can be with the bar rotation that inclines.
2. unmanned plane according to claim 1, which is characterized in that multiple rotor assemblies are separately positioned on the fuselage
The both sides of body, and relatively described fuselage body is symmetrical arranged two-by-two.
3. unmanned plane according to claim 1, which is characterized in that the bar that verts can drive the rotor rotational to institute
It is vertical with vertical direction to state the Plane of rotation of rotor, and the bar that verts can also drive the rotor rotational to the rotor
Plane of rotation it is parallel with vertical direction.
4. unmanned plane according to claim 1, which is characterized in that the rotor assemblies further include motor and governor, institute
Motor is stated to be electrically connected with the rotor, so that the motor can drive the rotor wing rotation, the governor and the motor,
The power supply module is electrically connected.
5. unmanned plane according to claim 1, which is characterized in that the wing components include empennage, and the empennage includes
Vertical tail, the vertical tail are fixedly connected with the fuselage body, and the vertical tail includes the vertically stable wing and direction
Rudder, the vertically stable wing are fixedly connected with the fuselage body, and the rudder can be rotatably mounted at the vertical peace
Determine on the wing.
6. unmanned plane according to claim 5, which is characterized in that the empennage further includes two tailplanes, two institutes
It states the relatively described vertical tail of tailplane to be symmetrical arranged, each tailplane includes the horizontal stable wing and elevator, institute
It states the horizontal stable wing to be fixedly connected with the vertical stable wing, the elevator can be rotatably mounted at the horizontal stable wing
On.
7. unmanned plane according to claim 1, which is characterized in that the power supply module includes accumulator and controller, institute
It states controller to be electrically connected with the accumulator, the controller is electrically connected with the photovoltaic module.
8. unmanned plane according to claim 7, which is characterized in that the power supply module further includes electric power source distribution device, described
Rotor assemblies are electrically connected by the electric power source distribution device with the controller.
9. unmanned plane according to claim 1, which is characterized in that further include undercarriage, the undercarriage is fixed on described
On fuselage body.
10. unmanned plane according to claim 1, which is characterized in that the wing components can rotate, and the unmanned plane is also
Including flying control component, the winged control component is contained in inside the fuselage body, winged control component and the bar that verts, described
Wing components are electrical connection, and the winged control component can control the bar rotation that inclines, and the winged control component can also be controlled
Make the wing components activity.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721451704.6U CN207374652U (en) | 2017-11-02 | 2017-11-02 | Unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721451704.6U CN207374652U (en) | 2017-11-02 | 2017-11-02 | Unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207374652U true CN207374652U (en) | 2018-05-18 |
Family
ID=62334802
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721451704.6U Expired - Fee Related CN207374652U (en) | 2017-11-02 | 2017-11-02 | Unmanned plane |
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| Country | Link |
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| CN (1) | CN207374652U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109720553A (en) * | 2019-02-13 | 2019-05-07 | 深圳创壹通航科技有限公司 | A kind of fixed-wing unmanned plane, control method and medium with VTOL function |
| WO2020121582A1 (en) * | 2018-12-14 | 2020-06-18 | 国立研究開発法人宇宙航空研究開発機構 | Flight body |
-
2017
- 2017-11-02 CN CN201721451704.6U patent/CN207374652U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2020121582A1 (en) * | 2018-12-14 | 2020-06-18 | 国立研究開発法人宇宙航空研究開発機構 | Flight body |
| JPWO2020121582A1 (en) * | 2018-12-14 | 2021-09-27 | 国立研究開発法人宇宙航空研究開発機構 | Flying object |
| JP7181643B2 (en) | 2018-12-14 | 2022-12-01 | 国立研究開発法人宇宙航空研究開発機構 | projectile |
| US11794891B2 (en) | 2018-12-14 | 2023-10-24 | Japan Aerospace Exploration Agency | Aerial vehicle equipped with multicopter mechanism |
| CN109720553A (en) * | 2019-02-13 | 2019-05-07 | 深圳创壹通航科技有限公司 | A kind of fixed-wing unmanned plane, control method and medium with VTOL function |
| CN109720553B (en) * | 2019-02-13 | 2021-07-27 | 深圳创壹通航科技有限公司 | Fixed-wing unmanned aerial vehicle with vertical take-off and landing function, control method and medium |
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