CN205686609U - VTOL Fixed Wing AirVehicle - Google Patents
VTOL Fixed Wing AirVehicle Download PDFInfo
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- CN205686609U CN205686609U CN201620568662.3U CN201620568662U CN205686609U CN 205686609 U CN205686609 U CN 205686609U CN 201620568662 U CN201620568662 U CN 201620568662U CN 205686609 U CN205686609 U CN 205686609U
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- fixed wing
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Abstract
This utility model relates to unmanned air vehicle technique field, a kind of VTOL Fixed Wing AirVehicle is provided, basic type scheme, including body, being provided with host wing on rear side of described body, the front in the middle part of wing is provided with propeller, and rear is provided with aileron, body front is provided with canard, is respectively perpendicular and is provided with vertical fin above and below body；Extended scheme, in order to realize Redundant Control, improves flight reliability, and the vertical tail rear being positioned at described body upper is provided with vertical rudder；The end of host wing is provided with dihedral wing tip, the quantity of lower vertical fin 2.The design of this utility model basic type, utilizes two propellers and both sides aileron to provide four degree of freedom full attitude Throttle Opening Control, controls simple；Extended can realize Horizontal Take-off and Landing, and host wing is provided with dihedral wing tip and stereoscopic vision avoidance sensor, it is achieved flight avoidance and vertical autonomous precisely landing；Frame for movement is relatively easy, and cost of manufacture is low.
Description
Technical field
This utility model relates to unmanned air vehicle technique field, is specifically related to a kind of VTOL fixed-wing unmanned vehicle.
Background technology
Fixed-wing unmanned plane has the advantages such as length in cruising time, cruising radius is big, flight efficiency is high.Utilize fixed-wing unmanned
Machine carries various load equipments as task platform and carries out flight operation, can be widely applied to the neck such as geographical mapping, geological prospecting
Territory.
But compared to rotary wind type unmanned plane, there is certain difficulty in the takeoff and landing of common fixed-wing unmanned plane.Just rise
For flying mode, large-scale Fixed Wing AirVehicle needs certain takeoff speed, typically utilizes the initial speed that launching cradle offer is certain
Degree, is also required to the open area of larger area during landing.Before draw the single-blade aircraft forward visual field to be obstructed, break down landing time front end
Propeller may constitute potential safety hazard；When the throwing of pusher single-blade aircraft hands or catapult-assisted take-off, the propeller of quick rotation also constitutes safety
Hidden danger.
Fixed-wing unmanned plane realizes taking off vertically and landing the most flexibly, it is possible to effectively reduce unmanned plane in landing
Time restriction to place.Application and the popularization of fixed-wing unmanned plane will be played and extremely close by the difficult problem solving fixed-wing landing limited
The impetus of key.It is true that part unmanned plane company by the way of four motor being installed on fixed-wing wing
Tentatively achieve fixed-wing to take off vertically and turn the flat function flown, but this implementation causes flight attitude unstable, causes
Flight efficiency is had a greatly reduced quality.Aircraft is in the horizontal flight stage, and four motor, all in closed mode, not only increase whole flying
The resistance of row system, also add the weight of load.
Therefore, allow Fixed Wing AirVehicle realize taking off vertically, and select runway and vertical mode to land, become needs and attack
Gram difficult point.
Summary of the invention
Solving fixed-wing unmanned plane in prior art to take off distance, the problem that landing modes is single, for all kinds of complexity
Sector application provide a kind of can VTOL also can runway landing, control accuracy high and the VTOL of plurality of devices can be carried
Fixed-wing unmanned vehicle.
This utility model realizes by the following technical solutions,
A kind of VTOL fixed-wing unmanned vehicle, basic type scheme, including body, on rear side of described body, it is provided with main frame
The wing, the front in the middle part of wing is provided with propeller, and rear is provided with aileron, and body front is provided with canard, divides above and below body
It is not vertically installed with vertical fin.
In order to realize VTOL, the vertical fin of described lower section is positioned in the middle part of body, the rear aerofoil of described vertical fin and body tail
Portion, the end of wing are generally aligned in the same plane.
In order to improve lift, described propeller and wing are close to arrange.
Extended scheme, in order to realize Redundant Control, improves flight reliability, is positioned at the vertical tail of described body upper
Rear is provided with vertical rudder.
In order to increase wing area to improve load, increase roll stability simultaneously and help to realize No Chute stall forced landing,
End at host wing is provided with dihedral wing tip.
In order to realize runway landing, the front of described body is provided with undercarriage, and the structure of vertical fin is for laying respectively under wing
The lower vertical fin of side, the quantity of lower vertical fin 2, the lower section of lower vertical fin is provided with pulley.
Further, the collapsible setting of front wheel carrier in described body front.
For improving the precision of flight, described canard leading edge both sides and trailing edge both sides, stereoscopic vision avoidance sensing is installed
Device, fuselage is provided with ultrasonic wave module.
Of the present utility model it is beneficial in that,
1. the design of basic type, utilizes two propellers and both sides aileron to provide four degree of freedom full attitude throttle controls
System, controls simple；The rear gas washing stream raising aileron rudder face controlled efficiency that propeller is powerful, contributes to horizontal STOL；Use
Preposition canard moves centre of lift and center of gravity to heading, increases the distance with aileron chain of command, is effectively improved gesture stability
Pitch stiffness when efficiency and horizontal flight.
The most extension type scheme can install undercarriage, it is possible to achieve Horizontal Take-off and Landing；Host wing is provided with dihedral wing tip, both
Increase wing area, to improve load, increases again roll stability and helps to realize No Chute stall forced landing；Stereoscopic vision avoidance passes
Sensor, it is achieved flight avoidance and vertical autonomous precisely landing；Frame for movement is relatively easy, and cost of manufacture is low.
Accompanying drawing explanation
Fig. 1 this utility model embodiment one perspective view；
Fig. 2 this utility model embodiment one plan structure schematic diagram；
Fig. 3 this utility model embodiment side TV structure schematic diagram；
Fig. 4 this utility model embodiment two perspective view；
Fig. 5 this utility model embodiment two backsight structural representation；
Fig. 6 this utility model embodiment two side-looking structural representation；
1. propeller in figure, 10. undercarriage, 11. pulleys, 12. times vertical fin, 2. motor, 3. steering wheel, 4. aileron, 5. vertical fins,
51. vertical rudders, 6. canard, 7. dihedral wing tip.
Detailed description of the invention
The utility model is described in further detail below in conjunction with the accompanying drawings.
Embodiment one
As it is shown in figure 1, this utility model provides a kind of VTOL Fixed Wing AirVehicle, including body, after described body
Side is provided with host wing, is positioned at the front in the middle part of wing and is provided with the propeller 1 connecting motor 2, and wing rear is provided with aileron 4, aileron 4
Connect the steering wheel 3 of internal body.Body front is provided with canard 6, is positioned at above and below body to be respectively perpendicular and is provided with vertical fin
5。
For the ease of controlling, described vertical fin 5 is positioned in the middle part of body, the rear aerofoil of described vertical fin 5 and body afterbody, wing
End is generally aligned in the same plane.
In order to improve lift, powerful rear gas washing stream is utilized to improve aileron 4 rudder face controlled efficiency, described propeller 1 and machine
The wing is close to arrange.
When the present embodiment is implemented, nose-high tail is down-set, and the rear gas washing stream utilizing propeller powerful improves aileron
Rudder face controlled efficiency, makes aircraft take off with vertical attitude.During horizontal flight, preposition canard moves in lift to heading
The heart and center of gravity, increase the distance with aileron chain of command, pitch stiffness when being effectively improved gesture stability efficiency and horizontal flight.Fall
Propeller is relied on to realize the vertical landing of fuselage vertical direction when falling.
The present embodiment provides four degree of freedom full attitude Throttle Opening Control merely with two propellers and both sides aileron；With list
Oar VTOL aircraft is different, and two propellers are contained in both sides wing nose, and the rear gas washing stream utilizing propeller powerful improves pair
Wing rudder face controlled efficiency, and improve the standard flight time airfoil lift, contribute to horizontal STOL；Use preposition canard to machine
Centre of lift and center of gravity are moved in head direction, increase the distance with aileron chain of command, are effectively improved gesture stability efficiency and level flies
Pitch stiffness during row.
Only having two propellers, when using fuel engines, frame for movement is relatively easy, and can be greatly improved voyage and load
Lotus ability.In addition, compared with single-blade fixed wing airplane, the design landing safety, manipulation practicality are good, it is to avoid draw single-blade to fly before
Machine field of front vision is obstructed, front end propeller when landing that breaks down constitutes potential safety hazard and pusher single-blade aircraft hands is thrown or launches
The problem that when taking off, the propeller of quick rotation constitutes potential safety hazard.
Embodiment two
As in figure 2 it is shown, the present embodiment is in order to improve control accuracy further, it is achieved various ways landing, with embodiment one
It is in place of comparing difference that the vertical tail rear that employed technical scheme comprise that body upper is provided with vertical rudder 51.Hydroplane 51 exists
Thering is provided during horizontal flight and point to Redundant Control, even if side propeller runs out of steam, aircraft also can be put down safely and be returned boat.
Simultaneously in order to realize runway landing, the front of body is provided with folding undercarriage 10, vertical fin under corresponding rear
12 quantity are 2, lay respectively at the lower section of both sides wing, and the lower front portion of vertical fin is provided with pulley 11, serve as when Horizontal Take-off and Landing
Coasting mechanism, is greatly improved load-carrying ability.
Improve load and roll stability to increase wing area, help to realize No Chute stall forced landing, main frame
The end of the wing is provided with dihedral wing tip.
For realizing flight avoidance and vertical autonomous precisely landing, canard leading edge both sides and trailing edge both sides, stereopsis is installed
Feel avoidance sensor, fuselage is additionally provided with ultrasonic wave module, effectively reduces vision dead zone, expands the model of location and avoidance perception
Enclose.
When this utility model is embodied as, undercarriage and 2 groups of vertical fins at fuselage rear and pulley combination can be relied on to realize
Level runway landing, it is also possible to realize VTOL as embodiment one, and plus vertical tail chain of command, horizontal flight
Time provide point to Redundant Control, even if occurring that side adynamic situation aircraft also can be put down safely to return boat.
VTOL is relatively big by windage, can use Horizontal Take-off and Landing during strong wind weather；Due to fuel oil consumption or air-drop
The reasons such as load make a return voyage aircraft when landing may be relatively light, facilitates views with vertical landing, is substantially reduced landing difficulty.Canard leading edge
Stereoscopic vision avoidance sensor can be installed in both sides and host wing trailing edge both sides, it is achieved flight avoidance and vertical autonomous precisely fall
Fall.
Claims (8)
1. a VTOL Fixed Wing AirVehicle, including body, it is characterised in that be provided with host wing, machine on rear side of described body
Front in the middle part of the wing is provided with propeller, and rear is provided with aileron, and body front is provided with canard, is respectively perpendicular above and below body
It is provided with vertical fin.
VTOL Fixed Wing AirVehicle the most according to claim 1, it is characterised in that the vertical fin of described lower section is positioned at machine
In the middle part of body, the rear aerofoil of described vertical fin is generally aligned in the same plane with the end of body afterbody, wing.
VTOL Fixed Wing AirVehicle the most according to claim 1, it is characterised in that described propeller is close to wing
Arrange.
4. according to the VTOL Fixed Wing AirVehicle described in claim 1 or 3, it is characterised in that be positioned at above described body
Vertical tail rear be provided with vertical rudder.
VTOL Fixed Wing AirVehicle the most according to claim 4, it is characterised in that the front of described body has been provided with
Fall frame, and the structure of vertical fin is to lay respectively at the lower vertical fin below wing, the quantity of lower vertical fin 2, and the lower section of lower vertical fin is provided with cunning
Wheel.
VTOL Fixed Wing AirVehicle the most according to claim 5, it is characterised in that the front wheel carrier in described body front
Collapsible setting.
VTOL Fixed Wing AirVehicle the most according to claim 6, it is characterised in that the end of described host wing is provided with
Acclivitous dihedral wing tip.
8. according to the VTOL Fixed Wing AirVehicle described in claim 5 to 7 any claim, it is characterised in that described
Stereoscopic vision avoidance sensor is installed in canard leading edge both sides and trailing edge both sides, and fuselage is provided with ultrasonic wave module.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620568662.3U CN205686609U (en) | 2016-06-14 | 2016-06-14 | VTOL Fixed Wing AirVehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620568662.3U CN205686609U (en) | 2016-06-14 | 2016-06-14 | VTOL Fixed Wing AirVehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205686609U true CN205686609U (en) | 2016-11-16 |
Family
ID=57427202
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620568662.3U Active CN205686609U (en) | 2016-06-14 | 2016-06-14 | VTOL Fixed Wing AirVehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205686609U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105905295A (en) * | 2016-06-14 | 2016-08-31 | 临沂高新区翔鸿电子科技有限公司 | Vertical take-off and landing fixed wing aircraft |
-
2016
- 2016-06-14 CN CN201620568662.3U patent/CN205686609U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105905295A (en) * | 2016-06-14 | 2016-08-31 | 临沂高新区翔鸿电子科技有限公司 | Vertical take-off and landing fixed wing aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CB03 | Change of inventor or designer information | ||
| CB03 | Change of inventor or designer information |
Inventor after: Mao Youbin Inventor before: Wang Zhengwei |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20170816 Address after: 276000 Shandong city of Linyi province high tech Zone Technology Park B block road bimonthly Co-patentee after: Xiang hung electronic technology (Shenzhen) Co., Ltd. Patentee after: Shandong Xiang Hong Electronic Technology Co., Ltd. Address before: 276000 Shandong city of Linyi province high tech Zone Technology Park B block road bimonthly Patentee before: Shandong Xiang Hong Electronic Technology Co., Ltd. |