CN207346096U - Vertical take-off and landing fixed wing aircraft with rear-mounted propeller - Google Patents
Vertical take-off and landing fixed wing aircraft with rear-mounted propeller Download PDFInfo
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- CN207346096U CN207346096U CN201721256895.0U CN201721256895U CN207346096U CN 207346096 U CN207346096 U CN 207346096U CN 201721256895 U CN201721256895 U CN 201721256895U CN 207346096 U CN207346096 U CN 207346096U
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- propeller
- wing
- postposition
- fixed wing
- vtol fixed
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- 229910052799 carbon Inorganic materials 0.000 claims description 3
- 239000000835 fiber Substances 0.000 claims description 3
- 230000005484 gravity Effects 0.000 claims description 3
- 230000037237 body shape Effects 0.000 claims description 2
- 230000009471 action Effects 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000003319 supportive effect Effects 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
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Abstract
The utility model relates to a vertical take-off and landing fixed wing aircraft with rear-mounted propellers, which comprises an aircraft body, a control panel, a navigation and control system and a battery system, wherein the aircraft body comprises a left wing and a right wing, the tail parts of the left wing and the right wing are respectively provided with a propeller in an embedded manner, and a rotating shaft of the propeller is parallel to the aircraft body; at least two control panels are arranged behind the propeller and connected with the tail of the machine body, and a rotating shaft penetrates through the control panels, so that the control panels can be adjusted around the rotating shaft. The utility model is characterized in that a rear propeller is embedded at the tail part of the wing, an adjustable control panel is arranged behind the propeller, and the motor drives the rear propeller to vertically lift the aircraft under the action of the rear propeller; meanwhile, the aircraft can hover and cruise in the air by adjusting the posture of the control panel. The utility model discloses realized the complex of vertical lift, long continuation of the journey, high load function with simple structure, the security performance is high, and technical cost is low.
Description
Technical field
It the utility model is related to aircraft field, more particularly to a kind of VTOL fixed-wing flight of propeller postposition
Device.
Background technology
In unmanned plane field, multi-rotor unmanned aerial vehicle can VTOL, limited from space and place, but its cruising ability
And lifting capacity is very limited；Fixed-wing unmanned plane can realize overlength continuation of the journey and big load because of excellent wing aerodynamic efficiency
Weight, but space and place are required during landing.Therefore, have nobody of more rotors and fixed-wing combination on the market
Machine type, to being combined the advantages of the two.
The unmanned plane type for combining more rotors and fixed-wing described in the prior art, is to pass through electric rotary machine mostly
Driving, i.e. electric rotary machine first drive propeller to realize that VTOL, then integral-rotation driving unmanned plane are cruised, it is controlled
System and motor rotating mechanism are complicated, technical costs rise and security performance reduction.
Separately have, multiple fixed motors and propeller are installed on unmanned plane, at least one fixed motor driving propeller makes
Unmanned plane VTOL, at least one fixed motor driving propeller realize horizontal flight so that the unmanned plane begins in flight
There is at least one motor to be in idle idle state eventually, add unmanned plane load.
Utility model content
To solve the above problems, the utility model provides a kind of VTOL Fixed Wing AirVehicle of propeller postposition, profit
With the device of the utility model, unmanned plane can be made while VTOL is realized, there is preferable cruising ability and load
Ability；Meanwhile technical costs is reduced with simple structure, improve security performance.
Technical solution is used by the utility model solves above-mentioned technical problem：
A kind of VTOL Fixed Wing AirVehicle of propeller postposition, including：
Body, control panel, navigation and control system, battery system, the body includes port wing and starboard wing, described
The left and right inside nick of wing afterbody, each one propeller of installation by adhering, the rotation axis of the propeller are parallel with the body；
At least two pieces of control panels are located at after the propeller, and are connected with the afterbody of the body, and shaft runs through the chain of command
Plate, makes the control panel to be rotated around the shaft.
In a preferred embodiment, the body shape is full Flying-wing's shape.
In a preferred embodiment, the left and right wingtip respectively sets a wing tip stent, the wing tip stent
It is fixedly connected with the shaft both ends.
In a preferred embodiment, an empennage is further included, the empennage is fixedly connected on the body afterbody
Centre position.
In a preferred embodiment, at least two groups of the battery system, and between battery system described in every group
Operation independently of one another.
In a preferred embodiment, the navigation and control system built-in redundancy system.
In a preferred embodiment, the navigation is built in the position of centre of gravity of the body, institute with control system
Battery system is stated to be symmetrically distributed in the port wing and the starboard wing.
In a preferred embodiment, camera is further included, the camera is located at the body head.
In a preferred embodiment, the body is molded for carbon fibre integrated.
The beneficial effects of the utility model are：
The utility model is set after propeller adjustable by wing afterbody installation by adhering rear-mounted propeller
Control panel, motor driving rear-mounted propeller, make aircraft vertical lifting under the action of rear-mounted propeller；Meanwhile fly
Device realizes skyborne hovering and cruise by adjusting the posture of control panel.The utility model is realized with simple structure
Vertical lift, long continuation of the journey, compound, the security performance height of top load function, technical costs are low.
Brief description of the drawings
The utility model is described further with reference to the accompanying drawings and examples.
Fig. 1 is the composition structure diagram of the utility model one embodiment；
Fig. 2 is the composition structure diagram of Fig. 1 embodiments.
Embodiment
Carried out below with reference to the technique effect of the design of embodiment and attached drawing to the utility model, concrete structure and generation
Clear, complete description, to be completely understood by the purpose of this utility model, scheme and effect.It should be noted that do not conflicting
In the case of, the feature in embodiment and embodiment in the application can be mutually combined.
It should be noted that unless otherwise specified, when a certain feature is referred to as " fixing ", " connection " in another feature,
It can directly fix, be connected in another feature, can also indirectly fix, be connected in another feature.In addition, this
The descriptions such as the upper and lower, left and right used in utility model are only the phase relative to each part of the utility model in attached drawing
For mutual position relationship.
In addition, unless otherwise defined, the technology of all of technologies and scientific terms used here by the article and the art
The normally understood implication of personnel is identical.Term used in the description is intended merely to description specific embodiment herein, without
It is to limit the utility model.Term as used herein " and/or " include appointing for one or more relevant Listed Items
The combination of meaning.
Fig. 1, Fig. 2 are the composition structure diagrams of the utility model one embodiment, reference Fig. 1, Fig. 2, after the propeller
The VTOL Fixed Wing AirVehicle put includes：
Body 1, propeller 2, motor 3, control panel 4, wing tip stent 5, empennage 6, shaft 7, battery system 8, camera 9
And navigation and control system 10.
In the utility model, body 1 includes port wing 101, starboard wing 102, the afterbody of port wing 101 and starboard wing 102
Inside nick, each one propeller 2 of installation by adhering, the rotation axis of propeller 2 is parallel with body 1, around rotation under the driving of motor 3
Axis rotates；At least two pieces of control panels 4 are located at after propeller 2, and are connected with the afterbody of body 1, set shaft 7 through control
Panel 4 processed, makes control panel 47 can rotate around the shaft.
In this way, takeoff opportunity body 1 is disposed vertically, motor 3 drives propeller 2 to rotate, and drives Fixed Wing AirVehicle complete machine to hang down
Directly take off；During taking off vertically herein, high-speed flow has only passed through the control panel 4 of small area, the high speed that propeller 2 produces
The resistance that air-flow is subject to is small, and the payload of whole VTOL Fixed Wing AirVehicle is substantially improved.Control panel 4 and propeller
2 cooperations control effectively the flight attitude of complete machine, make unmanned plane while VTOL is realized, realize skyborne outstanding
Stop and cruise, there is preferable cruising ability and load-carrying ability；Meanwhile technical costs is reduced with simple structure, improve safety
Performance.
In the present embodiment, it is preferable that as shown in Figure 1, 2, the shape of body 1 is full Flying-wing's shape, full Flying-wing
Be conducive to be lifted the lift resistance ratio of complete machine, be that the startability of complete machine is more preferable, flight efficiency is high.
In the present embodiment, it is preferable that port wing 101 and the tip of starboard wing 102 respectively set a wing tip stent 5, wing tip branch
Frame 5 is fixedly connected with the both ends of shaft 7, plays a supportive role during aircraft vertical lifting, avoids afterbody other structures from being damaged.
In the present embodiment, an empennage 6 is set to be fixedly connected on the centre position of 1 afterbody of body, and it is vertical with body,
Play a supportive role during aircraft vertical lifting, empennage 6 is arranged on 1 afterbody of body, and aircraft is in flight course, to complete machine
Flight efficiency influences little.
In the present embodiment, it is preferable that at least two groups of battery system 8, and transported independently of one another per between Battery pack system 8
OK, the security performance of complete machine flight is lifted.
In the present embodiment, it is preferable that navigation and 10 built-in redundancy system of control system, lifted the security performance of complete machine with can
By property.
In the present embodiment, it is preferable that navigation is built in the position of centre of gravity of body 1 with control system 10, and battery system 8 is right
Title is distributed in port wing 101 with starboard wing 102, being conducive to assembled machine balance.
In the present embodiment, it is preferable that the camera 9 positioned at 1 head of body is further included, beneficial to control complete machine flight, and from
The signal-obtaining information needed that camera is passed back.
In the present embodiment, it is preferable that body 1 is carbon fibre integrated shaping, in favor of lifted the globality of complete machine with it is reliable
Property.
To sum up, the process for using of the utility model is：The axial direction of shaft 7 is Y-direction, and the rotation direction of principal axis of propeller 2 is X
Direction, is Z directions perpendicular to the direction of X/Y plane；During taking off vertically, wing tip stent 5 and empennage 6 stand on ground vertically,
Two propellers 2 rotate the thrust for providing vertical direction, meanwhile, the rotation direction of two propellers 2 is on the contrary, offset complete machine in X side
To torque.
Hovering is realized to certain altitude, herein during vertical hovering, control panel 4 is around the shaft when complete machine takes off vertically
7 rotate, and two pieces of control panels 47 rotate in same direction the rotary balance for realizing complete machine around Y-direction around the shaft, and 7 incorgruous rotations are real around the shaft
Rotary balance of the existing complete machine around X-direction；Two 2 thrust differences of propeller realize rotary balance of the complete machine around Z directions.Control panel 4
And propeller 2 rotates the control by navigation and control system 10.
For complete machine by during hovering and being transformed into level cruise, the 7 significantly rotating Vortexes around the shaft of control panel 4, realize complete machine
Significantly rotated around Y-direction, realize that complete machine is adjusted to the flight attitude of horizontal direction by vertical direction.
During cruise, control panel 4 around Y-direction the rotary balance rotate in same direction to realize complete machine around Y directions, around Y
Rotary balance of the complete machine around X-direction is realized in the incorgruous rotation in direction, is realized around Z side by the thrust difference of two propellers 2
To rotary balance and realize aerial turn.
Level cruise is transformed into vertical hovering, by control panel 4 around Y-direction opposite direction significantly in the same direction to rotation come real
Existing complete machine is significantly rotated around Y-direction arrives the conversion of vertical direction from horizontal direction to realize.
Vertical landing process, the propeller 2 driven by reducing motor 3 realize vertical drop in the thrust of vertical direction
Fall.
Above is the preferable of the utility model is implemented to be illustrated, but the invention is not limited to the reality
Example is applied, those skilled in the art can also make a variety of equivalent variations on the premise of without prejudice to the utility model spirit
Or replace, these equivalent deformations or replacement are all contained in the application claim limited range.
Claims (9)
- A kind of 1. VTOL Fixed Wing AirVehicle of propeller postposition, it is characterised in that including：Body, control panel, navigation With control system, battery system, the body includes port wing and starboard wing, and the left and right inside nick of wing afterbody is each embedding Enter formula and one propeller is installed, the rotation axis of the propeller is parallel with the body；At least two pieces of control panels are located at the spiral shell After revolving paddle, and it is connected with the afterbody of the body, shaft runs through the control panel, makes the control panel can be around described turn Axis rotates.
- 2. the VTOL Fixed Wing AirVehicle of propeller postposition according to claim 1, it is characterised in that：The body Shape is full Flying-wing's shape.
- 3. the VTOL Fixed Wing AirVehicle of propeller postposition according to claim 2, it is characterised in that：The left side, Starboard wing tip respectively sets a wing tip stent, and the wing tip stent is fixedly connected with the shaft both ends.
- 4. the VTOL Fixed Wing AirVehicle of propeller postposition according to any one of claim 1 to 3, its feature exist In：An empennage is further included, the empennage is fixedly connected on the centre position of the body afterbody.
- 5. the VTOL Fixed Wing AirVehicle of propeller postposition according to any one of claim 1 to 3, its feature exist In：At least two groups of the battery system, and run independently of one another between battery system described in every group.
- 6. the VTOL Fixed Wing AirVehicle of propeller postposition according to claim 5, it is characterised in that：The navigation With control system built-in redundancy system.
- 7. the VTOL Fixed Wing AirVehicle of propeller postposition according to claim 6, it is characterised in that：The navigation The position of centre of gravity of the body is built in control system, the battery system is symmetrically distributed in the port wing and the right machine In the wing.
- 8. according to claim 1, the VTOL Fixed Wing AirVehicle of the propeller postposition any one of 2,3,7, it is special Sign is：Camera is further included, the camera is located at the body head.
- 9. according to claim 1, the VTOL Fixed Wing AirVehicle of the propeller postposition any one of 2,3,7, it is special Sign is：The body is molded for carbon fibre integrated.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721256895.0U CN207346096U (en) | 2017-09-27 | 2017-09-27 | Vertical take-off and landing fixed wing aircraft with rear-mounted propeller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721256895.0U CN207346096U (en) | 2017-09-27 | 2017-09-27 | Vertical take-off and landing fixed wing aircraft with rear-mounted propeller |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207346096U true CN207346096U (en) | 2018-05-11 |
Family
ID=62357620
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721256895.0U Withdrawn - After Issue CN207346096U (en) | 2017-09-27 | 2017-09-27 | Vertical take-off and landing fixed wing aircraft with rear-mounted propeller |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207346096U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107618662A (en) * | 2017-09-27 | 2018-01-23 | 南方科技大学 | Vertical take-off and landing fixed wing aircraft with rear-mounted propeller |
| CN110576965A (en) * | 2019-09-23 | 2019-12-17 | 西北工业大学 | Unmanned aerial vehicle layout with least control surface configuration and control method thereof |
-
2017
- 2017-09-27 CN CN201721256895.0U patent/CN207346096U/en not_active Withdrawn - After Issue
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107618662A (en) * | 2017-09-27 | 2018-01-23 | 南方科技大学 | Vertical take-off and landing fixed wing aircraft with rear-mounted propeller |
| CN107618662B (en) * | 2017-09-27 | 2023-11-14 | 南方科技大学 | Vertical take-off and landing fixed wing aircraft with rear propeller |
| CN110576965A (en) * | 2019-09-23 | 2019-12-17 | 西北工业大学 | Unmanned aerial vehicle layout with least control surface configuration and control method thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| EE01 | Entry into force of recordation of patent licensing contract | ||
| EE01 | Entry into force of recordation of patent licensing contract |
Assignee: Shenzhen Yige Technology Co.,Ltd. Assignor: Southern University of Science and Technology Contract record no.: X2019440020025 Denomination of utility model: Vertical takeoff and landing fixed-wing aircraft with rear propellers Granted publication date: 20180511 License type: Exclusive License Record date: 20191121 |
|
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20180511 Effective date of abandoning: 20231114 |
|
| AV01 | Patent right actively abandoned |
Granted publication date: 20180511 Effective date of abandoning: 20231114 |