CN202219839U - Omnidirectional flying wing structure of vertical lifting aircraft - Google Patents
Omnidirectional flying wing structure of vertical lifting aircraft Download PDFInfo
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- CN202219839U CN202219839U CN2011202931423U CN201120293142U CN202219839U CN 202219839 U CN202219839 U CN 202219839U CN 2011202931423 U CN2011202931423 U CN 2011202931423U CN 201120293142 U CN201120293142 U CN 201120293142U CN 202219839 U CN202219839 U CN 202219839U
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Abstract
An omnidirectional flight wing structure of a vertical lifting aircraft comprises a horizontal wing, a fuselage, a lifting power system and a control system; the lifting power system is arranged on the machine body; the horizontal wing is rotatably connected with the fuselage through a rotating mechanism; the control system comprises a wind direction/wind speed sensing device and a controller; the signal output end of the wind direction/wind speed sensing device is connected with the signal input end of the controller; the control signal output end of the controller is connected with the control signal input end of the rotating mechanism. Compared with the prior art, this novel mechanical structure makes the vertical lift aircraft under various flight condition, and usable atmosphere air flows and obtains lift from the wing of qxcomm technology flight to must reduce power consumption, increase and stay empty time, can utilize the vertical lift aircraft that has universal flight wing to carry out the short distance and roll off and land simultaneously, realize the heavy load flight. The flight mode can be smoothly changed into a conventional fixed wing flight mode, the flight mode is close to a fixed wing aircraft, and the endurance is increased.
Description
Technical field
The utility model belongs to the vehicle technology field, specifically is a kind of omnidirectional's flying machine wing structure of vertical lift aircraft.
Background technology
Vertical lift aircraft of the prior art, its lift all comes from the lift of vertical lift driving engine.Because not by means of airflow acting forces such as natural wind force, the consumption of fuel in the landing process is very big.
Summary of the invention
In order to solve the problems referred to above that exist in the prior art, the utility model proposes a kind of omnidirectional's flying machine wing structure of new vertical lift aircraft, and concrete technical scheme is following:
A kind of omnidirectional's flying machine wing structure of vertical lift aircraft comprises horizontal wings, fuselage, up-down power system and control system; Said up-down power system is located on the fuselage; Said horizontal wings and fuselage are rotationally connected through rotating mechanism;
Said control system comprises wind direction/air velocity transducer spare and controller; The signal output part of wind direction/air velocity transducer spare connects the signal input part of controller; The control signal output ends of controller connects the signal input end of rotating mechanism.
The aerofoil aligning elevation gear that comprises horizontal wings; The control signal output ends of said controller connects the signal input end of aerofoil aligning elevation gear.
Said horizontal wings is provided with spoiler.
Said spoiler comprises the wing fence that is located at the horizontal wings stage casing and/or is located at the vertical winglet at horizontal wings wingtip position.
Said horizontal wings is installed in top, below or the side of fuselage.
Said horizontal wings comprises conventional fixed wing, the umbrella wing, circle row wing, polygon wing or rotor.
The principle of the utility model be; But the omnidirectional of this vertical lift aircraft flight wing, but can be contained in the carry-on flight wing of vertical lift, and the places different with the conventional levels wing are; This wing can be done 360 degree with respect to fuselage and horizontally rotate; Under the effect of the vertical wing of orientation, horizontal wings is all the time over against windstream, and horizontal wings has the angle at the elevation angle, the elevation angle can be according to the speed automatic compensation of windstream; So no matter but the vertical lift aircraft is in high-speed flight; Low-speed operations is still in the state of flight of vertically hovering, and omnidirectional's flight wing can utilize aerial air-flow for aircraft lift to be provided, and is used for reducing consuming, increasing flight time and voyage.
Compared with prior art, but the utility model is the universal flight wing that can be used for all kinds of vertical lift aircraft such as autogyro, unmanned helicopter and many helighros.This novel mechanical structure makes the vertical lift aircraft under various state of flights; Atmospheric air capable of using flows and obtains lift from omnidirectional's flight wing; Must reduce consumption of power; Increase airborne period, can utilize vertical lift aircraft to carry out the sliding race of short range landing simultaneously, realize big load flight with universal flight wing.Can also transfer conventional fixed-wing offline mode smoothly to,, increase endurance to fly near the mode of fixed-wing aircraft.
Description of drawings
Fig. 1 is the omnidirectional's flight wing scheme drawing that is contained on four rotor crafts.
Fig. 2 is the birds-eye view of Fig. 1.
Fig. 3 is the control principle block diagram of this flying machine wing structure.
Among the figure: 1. horizontal wings, 2. fuselage, 3. screw propeller, 4. electrical motor, 5. rotating disk, 6. vertical winglet.
The specific embodiment
Below in conjunction with the accompanying drawing and the specific embodiment the utility model is further specified:
A kind of omnidirectional's flying machine wing structure of vertical lift aircraft comprises horizontal wings, fuselage, up-down power system and control system; Said up-down power system is located on the fuselage; Said horizontal wings and fuselage are rotationally connected through rotating mechanism;
Said control system comprises wind direction/air velocity transducer spare and controller; The signal output part of wind direction/air velocity transducer spare connects the signal input part of controller; The control signal output ends of controller connects the signal input end of rotating mechanism.
The aerofoil aligning elevation gear that comprises horizontal wings; The control signal output ends of said controller connects the signal input end of aerofoil aligning elevation gear.Said horizontal wings is provided with spoiler.Said spoiler is provided in a side of the vertical winglet at horizontal wings wingtip position.Said horizontal wings is installed in the top of fuselage.
In this example, the conventional fixed wing of horizontal wings; The up-down power system is the electrical motor (containing battery) that has screw propeller;
Said wind direction/air velocity transducer spare can adopt existing sensors; Controller can adopt micro controller system; Rotating mechanism is: the rotating disk that has rotary electric machine; The aerofoil aligning elevation gear is: horizontal wings and rotating disk are connected through the hinge, and pitching motor connects horizontal wings through connecting rod.
In this example, fuselage is a cross structure, is fixed with four motors and motor-driven screw propeller, is representative type four rotor craft structures.
Rotary base is fixed on fuselage, and wing is installed on the rotating disk, and fuselage rotates at any angle relatively.
Directed vertical winglet is housed on the wing, makes wing all the time over against windstream, to produce maximum lift, the heading of aircraft then is the sense of motion of fuselage.
This omnidirectional flight wing, but be to be contained in the carry-on flight wing of vertical lift, the place different with the conventional levels wing is that this wing can be done 360 degree with respect to fuselage and horizontally rotates, under the effect of attitude reference device, horizontal wings is all the time over against windstream.Horizontal wings can lock over against heading, also can become arbitrarily angled with heading after the release, all the time towards the direction of Atmospheric Flow.
Horizontal wings has the elevation angle, and the size at the elevation angle can be according to the speed adjustment of windstream.
Optional horizontal wings comprises the conventional fixed wing that can produce lift awing, the umbrella wing, the rotor of circle row or polygon wing and similar cyclogyro.
Claims (6)
1. omnidirectional's flying machine wing structure of a vertical lift aircraft is characterized in that comprising horizontal wings, fuselage, up-down power system and control system; Said up-down power system is located on the fuselage; Said horizontal wings and fuselage are rotationally connected through rotating mechanism;
Said control system comprises wind direction/air velocity transducer spare and controller; The signal output part of wind direction/air velocity transducer spare connects the signal input part of controller; The control signal output ends of controller connects the signal input end of rotating mechanism.
2. omnidirectional's flying machine wing structure of vertical lift aircraft according to claim 1 is characterized in that comprising the aerofoil aligning elevation gear of horizontal wings; The control signal output ends of said controller connects the signal input end of aerofoil aligning elevation gear.
3. omnidirectional's flying machine wing structure of vertical lift aircraft according to claim 1 is characterized in that said horizontal wings is provided with spoiler.
4. omnidirectional's flying machine wing structure of vertical lift aircraft according to claim 3 is characterized in that said spoiler comprises the wing fence that is located at the horizontal wings stage casing and/or is located at the vertical winglet at horizontal wings wingtip position.
5. omnidirectional's flying machine wing structure of vertical lift aircraft according to claim 1 is characterized in that said horizontal wings is installed in the top of fuselage, below or side.
6. omnidirectional's flying machine wing structure of vertical lift aircraft according to claim 1 is characterized in that said horizontal wings comprises conventional fixed wing, the umbrella wing, circle row wing, polygon wing or rotor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011202931423U CN202219839U (en) | 2011-08-12 | 2011-08-12 | Omnidirectional flying wing structure of vertical lifting aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011202931423U CN202219839U (en) | 2011-08-12 | 2011-08-12 | Omnidirectional flying wing structure of vertical lifting aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202219839U true CN202219839U (en) | 2012-05-16 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011202931423U Expired - Fee Related CN202219839U (en) | 2011-08-12 | 2011-08-12 | Omnidirectional flying wing structure of vertical lifting aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202219839U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106741899A (en) * | 2017-01-04 | 2017-05-31 | 上海量明科技发展有限公司 | Kite aircraft and its implementation |
| CN107176292A (en) * | 2017-06-16 | 2017-09-19 | 重庆谭工科技有限公司 | A kind of aircraft air propeller |
| CN110531739A (en) * | 2014-10-09 | 2019-12-03 | 波音公司 | Method and apparatus for operating the flight control system of aircraft |
-
2011
- 2011-08-12 CN CN2011202931423U patent/CN202219839U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110531739A (en) * | 2014-10-09 | 2019-12-03 | 波音公司 | Method and apparatus for operating the flight control system of aircraft |
| CN106741899A (en) * | 2017-01-04 | 2017-05-31 | 上海量明科技发展有限公司 | Kite aircraft and its implementation |
| CN107176292A (en) * | 2017-06-16 | 2017-09-19 | 重庆谭工科技有限公司 | A kind of aircraft air propeller |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20120516 Termination date: 20120812 |