CN208931639U - A kind of novel culvert type vertical take-off and landing drone - Google Patents
A kind of novel culvert type vertical take-off and landing drone Download PDFInfo
- Publication number
- CN208931639U CN208931639U CN201821385234.2U CN201821385234U CN208931639U CN 208931639 U CN208931639 U CN 208931639U CN 201821385234 U CN201821385234 U CN 201821385234U CN 208931639 U CN208931639 U CN 208931639U
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- China
- Prior art keywords
- wing
- fuselage
- steering engine
- vertical take
- landing drone
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Abstract
The utility model discloses a kind of novel culvert type vertical take-off and landing drone, including fuselage, the two sides of the fuselage are symmetrically arranged with a pair of of wing, the fuselage and wing are blended wing-body structure, the edge of the wing is equipped with reclinate bending section, steering engine is installed, the transmission shaft of the steering engine is connected with ducted fan on the bending section；The program drives ducted fan to turn to control posture, improves the mobility of vertical take-off and landing drone, eliminate exposed lift engine, reduce windage, improve lifting capacity and cruising ability relatively by the way that steering engine is arranged in the two sides of wing by steering engine；In addition fuselage and wing use blended wing-body structure to improve pneumatic efficiency using flying wing type aerodynamic arrangement；Using ducted fan, efficiency of energy utilization is high, highly-safe.
Description
Technical field
The utility model relates to air vehicle technique field, in particular to it is a kind of can VTOL culvert type unmanned plane.
Background technique
In recent years, unmanned plane is more and more extensive since its distinct technical characterstic all obtains in military and civilian field
Using and rapid development, especially agricultural plant protection, military surveillance, environmental abnormality detection, disaster relief and rescue, electric inspection process, mapping and
The fields such as modeling, take photo by plane, entertaining has extensive demand, it represents an important development direction of the following aircraft.
Existing vertical take-off and landing drone provides vertical direction using the propeller that additional brushless motor drives mostly
Power not only influences pneumatic efficiency in this way, but also will increase unnecessary weight bearing.
Utility model content
For solve existing VTOL formula unmanned plane useful load small, the low problem of cruising ability, the utility model
There is provided that a kind of payload is larger, the higher culvert type vertical take-off and landing drone of cruising ability.
To achieve the goals above, technical solution provided by the utility model is: a kind of novel culvert type VTOL without
Man-machine, including fuselage, the two sides of the fuselage are symmetrically arranged with a pair of of wing, and the fuselage and wing are blended wing-body structure, institute
The edge for stating wing is equipped with reclinate bending section, is equipped with steering engine, the transmission axis connection of the steering engine on the bending section
There is ducted fan.
In the above-mentioned technical solutions, further, the tail portion of the fuselage is equipped with undercarriage.
Based on the above technical solution, it is preferred that the undercarriage includes first support, second support and third
Bracket, wherein the angle between first support and second support is 135 °, and the angle between first support and third bracket is
135°。
In the above-mentioned technical solutions, further, the rotation direction of the steering engine is vertical with plane where the wing.
Further, the ducted fan can be rotated along the rotation direction of the steering engine, and rotational angle is 0 ° to 90 °.
The beneficial effect of the utility model compared with the existing technology is: the program by the two sides of wing be arranged steering engine,
It drives ducted fan to turn to control posture by steering engine, improves the mobility of vertical take-off and landing drone；It eliminates exposed
Lift engine, rudder, elevator, wing flap and aileron, reduce windage and body weight, the opposite lifting capacity that improves
And cruising ability；In addition fuselage and wing use blended wing-body structure, improve pneumatic efficiency；Use ducted fan, energy benefit
It is highly-safe with high-efficient.
Detailed description of the invention
Fig. 1 is the utility model state of flight structure chart；
Fig. 2 is the structure graph that rises and falls of the utility model.
Specific embodiment
Specific embodiment of the present utility model is described further with reference to the accompanying drawing.It should be noted that
The explanation of these embodiments is used to help to understand the utility model, but does not constitute the restriction to the utility model.This
Outside, technical characteristic involved in the various embodiments of the present invention described below is as long as they do not conflict with each other
It can be combined with each other.
As shown in Figure 1, a kind of novel culvert type vertical take-off and landing drone, including fuselage 1, the two sides of fuselage 1 are symmetrically arranged with
A pair of of wing 21 and 22, fuselage 1 and wing 21 and 22 are blended wing-body structure, the available better aeroperformance of aircraft.
The advantages of blended wing-body is that resistance is small, improves pneumatic efficiency, increases the ultimate run of unmanned plane.
In addition, the edge of wing 21 and 22 is respectively equipped with reclinate bending section 210 and 220, bending section can
The further pneumatic efficiency for improving aircraft.Edge on bending section 210 and 220 is separately installed with steering engine 31 and 32, rudder
Machine is a kind of driver of position (angle) servo, the control system that needs angle constantly to change suitable for those and can keep
System, the output shaft of steering engine 31 are connected with ducted fan 41, and the transmission shaft of steering engine 32 is connected with ducted fan 42, ducted fan due to
It is limited at blade tip by duct, impact noise reduces, and induced drag is reduced, and efficiency is higher.Under Same Efficieney consumption, duct wind
The isolated propeller for fanning more same diameter, can generate bigger thrust, simultaneously because the ring of duct includes effect, compact-sized,
Aerodynamic noise is low, safety in utilization is good.
The rotation direction of steering engine 31 and 32 is vertical with plane where wing, and rotational angle is 0 ° -90 °, due to steering engine
Transmission shaft is connect with ducted fan, so being able to drive the rotation of ducted fan 41 and 42, this makes it possible to by changing thrust
Advance, retrogressing and the steering of hovering mode and pitching, the rolling of flat winged mode are realized, in addition, providing by ducted fan in direction
The distance between the position of thrust and the center of gravity of airplane form the arm of force, so as to control the posture of aircraft；Pass through two culverts of control
The differential of road fan 41 and 42 realizes yaw, steering when side when hovering mode flies peaceful winged mode, is pushed away by controlling it
Lifting when acceleration, deceleration and hovering mode when the synchronous plus-minus of power realizes flat winged mode.
As shown in Fig. 2, the tail portion of fuselage 1 be equipped with undercarriage 5, undercarriage 5 include three brackets be respectively 51,52 and
53, wherein the angle between bracket 52 and bracket 51 is 135 °, and the angle between bracket 52 and bracket 53 is also 135 °, is set in this way
It sets the effect that can not only play undercarriage and the effect of empennage can be played during flight.
By by undercarriage setting in tail portion, it is not only compact-sized, when taking off perhaps landing without packing up or putting down
Undercarriage, and when taking off, the head of unmanned plane upward, due to the head of unmanned plane be it is streamlined, so entire unmanned plane
Air drag when taking off can greatly reduce, and reduce energy consumption.
In addition, the unmanned plane is powered using lithium polymer battery, it is remotely controlled by 2.4G radio, winged control can be carried,
Development space is big.
The embodiments of the present invention is explained in detail in conjunction with attached drawing above, but the utility model is not limited to be retouched
The embodiment stated.For a person skilled in the art, right in the case where not departing from the utility model principle and spirit
These embodiments carry out a variety of change, modification, replacement and modification, still fall in the protection scope of the utility model.
Claims (5)
1. a kind of novel culvert type vertical take-off and landing drone, including fuselage, it is characterised in that: the two sides of the fuselage are symmetrically arranged with
A pair of of wing, the fuselage and wing are blended wing-body structure, and the edge of the wing is equipped with reclinate bending section, described
Steering engine is installed, the transmission shaft of the steering engine is connected with ducted fan on bending section.
2. novel culvert type vertical take-off and landing drone according to claim 1, it is characterised in that: the tail portion of the fuselage is set
There is undercarriage.
3. novel culvert type vertical take-off and landing drone according to claim 2, it is characterised in that: the undercarriage includes the
One bracket, second support and third bracket, wherein the angle between first support and second support is 135 °, first support with
Angle between third bracket is 135 °.
4. novel culvert type vertical take-off and landing drone according to claim 1, it is characterised in that: the rotation side of the steering engine
To vertical with plane where the wing.
5. novel culvert type vertical take-off and landing drone according to claim 4, it is characterised in that: the ducted fan can
Rotation direction along the steering engine rotates, and rotational angle is 0 ° to 90 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821385234.2U CN208931639U (en) | 2018-08-27 | 2018-08-27 | A kind of novel culvert type vertical take-off and landing drone |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821385234.2U CN208931639U (en) | 2018-08-27 | 2018-08-27 | A kind of novel culvert type vertical take-off and landing drone |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208931639U true CN208931639U (en) | 2019-06-04 |
Family
ID=66718922
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821385234.2U Expired - Fee Related CN208931639U (en) | 2018-08-27 | 2018-08-27 | A kind of novel culvert type vertical take-off and landing drone |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208931639U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111661344A (en) * | 2020-07-13 | 2020-09-15 | 中国航空发动机研究院 | Wing-body integrated aircraft propulsion system |
-
2018
- 2018-08-27 CN CN201821385234.2U patent/CN208931639U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111661344A (en) * | 2020-07-13 | 2020-09-15 | 中国航空发动机研究院 | Wing-body integrated aircraft propulsion system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190604 Termination date: 20210827 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |