CN204895839U - Light aerocraft all -moving wing - Google Patents
Light aerocraft all -moving wing Download PDFInfo
- Publication number
- CN204895839U CN204895839U CN201520479763.9U CN201520479763U CN204895839U CN 204895839 U CN204895839 U CN 204895839U CN 201520479763 U CN201520479763 U CN 201520479763U CN 204895839 U CN204895839 U CN 204895839U
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- Prior art keywords
- wing
- aircraft
- hydraulic
- organism
- utility
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Abstract
The utility model discloses a light aerocraft all -moving wing is provided with hydraulic telescoping rod admittedly on the organism lateral wall, still set firmly the longitudinal tie pole, the wing front end is equipped with the connecting axle, and the rear end is equipped with the transverse connection pole with back beam hinge pin rigid coupling, flexible end of this hydraulic telescoping rod and wing front end connecting axle rigid coupling, the wing rear end is passed through the back beam hinge pin and is connected with the longitudinal tie pole on the organism. Hydraulic telescoping rod is by pressure boost of organism hydraulic pump and decompression. The utility model discloses a removed the aileron and the wing flap of aircraft, it is holistic upwards rotatory along wing back beam articulated joint with downwards to control the aircraft wing with the aircraft at hydraulic means of the junction of wing and fuselage installation. When controlling wing hydraulic means while upward movement, the angle of attack of aircraft wing increases, increases the lift of aircraft. When the downstream of wing hydraulic means was controlled to the aircraft, the wing angle of attack reduced, the lift divergence.
Description
Technical field
The utility model is a kind of all-moving wing that can change the wing angle of attack.This kind of wing can change the angle of attack of wing in flight course, improves the lift of aircraft or increases the resistance of aircraft.
Background technology
Traditional aircaft configuration, the wing of aircraft is fixed on the fuselage of aircraft, relative to fuselage, do not have relative motion, and wing is arranged wing flap and aileron, and being used for increases the lift of aircraft and the rolling movement of aircraft.
The roll unloads of current aircraft is realized by aileron, and the wing flap of aircraft is used for improving the lift of aircraft.But control system is complicated, and number of parts is more, fault rate is also higher.How to make the structure of aircraft more simple and practical, and reduce the fault rate of aircraft, improving its safety is also aerospace designs aspect urgent problem.
Utility model content
The utility model, for solving the problem, provides the aviette all-moving wing that a kind of structure is simple, maintainability is strong.
The technical scheme that utility model adopts is:
A kind of aviette all-moving wing, organism sidewall sets firmly and is equipped with hydraulically extensible bar, be also installed with longitudinal pipe link; Wing nose is provided with adapter shaft, and rear end is provided with the lateral connection bar affixed with back rest hinge axis; This hydraulically extensible bar telescopic end and wing nose adapter shaft affixed; Rear airfoil end is connected with the longitudinal pipe link on body by back rest hinge axis.Described hydraulically extensible bar is by the supercharging of body Hydraulic Pump and decompression.
The beneficial effect that the utility model is created is:
1, structure is simple, maintainability is strong, while not changing Aerodynamic Configuration of Aireraft, can realize the function of aileron and wing flap simultaneously, simplifies interior of aircraft structural arrangement.
2, the utility model is the aileron and the wing flap that eliminate aircraft, aircraft is installed a hydraulic efficiency gear in the junction of wing and fuselage and can control rotating along wing rear spar articulated joint up and down of aircraft wing entirety.When the wing hydraulic efficiency gear of left and right while when upward movement, the angle of attack of aircraft wing increases, and increases the lift of aircraft.When aircraft left and right wing hydraulic efficiency gear moves downward, the wing angle of attack reduces, and lift reduces.When upwards side moves downward wing side, left and right, the left and right wing angle of attack is different, and lift is different, makes aircraft rolling play the effect of aircraft aileron.
Accompanying drawing explanation
Fig. 1 is wing birds-eye view of the present utility model;
Fig. 2 is wing front elevation of the present utility model;
Schematic diagram when Fig. 3 is airfoil flight of the present utility model;
Fig. 4 is that wing of the present utility model takes off middle angle of attack enlarging state figure;
Fig. 5 be wing of the present utility model take off the middle angle of attack reduce constitution diagram.
Detailed description of the invention
Below in conjunction with Figure of description and Reference numeral, the utility model is further described.
As Figure 1-5, a kind of aviette all-moving wing, organism sidewall sets firmly and is equipped with hydraulically extensible bar 1, is also installed with longitudinal pipe link 3; Wing nose is provided with adapter shaft 2, and rear end is provided with the lateral connection bar 5 affixed with back rest hinge axis 4; This hydraulically extensible bar 1 telescopic end and wing nose adapter shaft 2 affixed; Rear airfoil end is connected with the longitudinal pipe link 3 on body by back rest hinge axis 4.
Described hydraulically extensible bar 1 is by the supercharging of body Hydraulic Pump and decompression.
Wing nose also fixes with sliding machine body and is connected.
It is identical that the wing of body both sides arranges structure.
Embodiment
When taking off in process, hydraulically extensible bar 1 extends under the effect of Hydraulic Pump, and wing rotates up around aircraft back rest hinge axis 4, and the angle of attack of aircraft wing is increased, and increases the lift of aircraft.
When in aircraft landing process, hydraulically extensible bar 1 shrinks, and wing is rotated down around aircraft back rest hinge axis 4, and the wing angle of attack of aircraft is reduced.When aircraft needs rolling, side hydraulically extensible bar 1 extends, and opposite side hydraulically extensible bar 1 shortens, and makes the lift of both sides wing different, reaches the object of aircraft rolling.
Claims (4)
1. an aviette all-moving wing, is characterized in that:
Organism sidewall sets firmly and is equipped with, be also installed with longitudinal pipe link (3);
Wing nose is provided with adapter shaft (2), and rear end is provided with the lateral connection bar (5) affixed with back rest hinge axis (4);
This hydraulically extensible bar (1) telescopic end and wing nose adapter shaft (2) affixed;
Rear airfoil end is connected with the longitudinal pipe link (3) on body by back rest hinge axis (4).
2. a kind of aviette all-moving wing according to claim 1, is characterized in that:
Described hydraulically extensible bar (1) is by the supercharging of body Hydraulic Pump and decompression.
3. a kind of aviette all-moving wing according to claim 1, is characterized in that:
Wing nose also fixes with sliding machine body and is connected.
4. a kind of aviette all-moving wing according to claim 1, is characterized in that:
It is identical that the wing of body both sides arranges structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520479763.9U CN204895839U (en) | 2015-07-06 | 2015-07-06 | Light aerocraft all -moving wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520479763.9U CN204895839U (en) | 2015-07-06 | 2015-07-06 | Light aerocraft all -moving wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204895839U true CN204895839U (en) | 2015-12-23 |
Family
ID=54918037
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520479763.9U Expired - Fee Related CN204895839U (en) | 2015-07-06 | 2015-07-06 | Light aerocraft all -moving wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204895839U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105523172A (en) * | 2016-01-11 | 2016-04-27 | 成都学尚科技有限公司 | Attack angle control system and attack angle control method |
| CN106428524A (en) * | 2016-11-25 | 2017-02-22 | 南京柯尔航空科技有限公司 | Multi-rotor wing aircraft with free wing |
-
2015
- 2015-07-06 CN CN201520479763.9U patent/CN204895839U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105523172A (en) * | 2016-01-11 | 2016-04-27 | 成都学尚科技有限公司 | Attack angle control system and attack angle control method |
| CN105523172B (en) * | 2016-01-11 | 2017-12-29 | 成都学尚科技有限公司 | Angle of attack control system and angle of attack control method |
| CN106428524A (en) * | 2016-11-25 | 2017-02-22 | 南京柯尔航空科技有限公司 | Multi-rotor wing aircraft with free wing |
| CN106428524B (en) * | 2016-11-25 | 2019-09-13 | 南京柯尔航空科技有限公司 | A kind of multi-rotor aerocraft with the free wing |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20151223 Termination date: 20160706 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |