CN204709801U - Adjustable wing aeromodelling aerocraft - Google Patents
Adjustable wing aeromodelling aerocraft Download PDFInfo
- Publication number
- CN204709801U CN204709801U CN201520372199.0U CN201520372199U CN204709801U CN 204709801 U CN204709801 U CN 204709801U CN 201520372199 U CN201520372199 U CN 201520372199U CN 204709801 U CN204709801 U CN 204709801U
- Authority
- CN
- China
- Prior art keywords
- wing
- dihedral
- angle
- actuation unit
- servo
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Landscapes
- Toys (AREA)
Abstract
A kind of adjustable wing aeromodelling aerocraft, this aircraft comprises wing and plunders angle actuation unit, wing dihedral actuation unit and wing position actuation unit; The beneficial effects of the utility model: the change of being plunderred angle, dihedral and position by wing, can promote the flying quality of aeromodelling aerocraft.1, wing is plunderred angle actuation unit and can be changed the leading edge of a wing lift of aircraft in low speed and flight course, optimizes with this resistance, lift etc. that aircraft is subject to.2, wing dihedral actuation unit can improve the lateral stability of aircraft in any flight course.3, wing position actuation unit can balance wing and plunders angle and change the gravity center shift problem brought, and makes the flight course of aircraft more stable, is beneficial to manipulation.A kind of adjustable wing aeromodelling aerocraft can be formed, to a certain extent for China's adjustable wing aircraft research is offered help by this integrated control system.
Description
Technical field
The utility model belongs to vehicle technology field, particularly relates to a kind of adjustable wing aeromodelling aerocraft.
Background technology
As the aircraft that a wing parameter is significantly adjustable, there is no similar type both at home and abroad at present and emerge.At present, " changing wing parameter " on ordinary meaning is only limitted to variable swept back wing or variable camber, and is subject to the impact of computer and fly-by-wire, and the type be born at present all retires from active service.The aircraft of a few money typical wing changeable parameters and project: the F-14 " male cat " as the U.S. fights: the first practical " swing-wing " fighter plane of this Ji Shi USN, the air defense and the bank base that are mainly used in fleet are supported; The tornado jet fighters in Europe." blast " fighter plane is two-seater two swing-wing fighter planes that Britain, Germany and Italy develop jointly; meter Ge-23 fighter plane of the former Soviet Union is a kind of swing-wing single seat single-shot supersonic fighterplane of antagonism u.s.a. military affairs power development in the cold war later stage.As the main force of air force of former Soviet Union air defense type, have stronger to-ground attack capability concurrently simultaneously.Its swing-wing technology improves takeoff and landing performance and increases voyage simultaneously, reduces supersonic drag.
When taking off, speed air flow is low, needs to adopt larger wing area to impel aircraft to take off fast; Then do not need so large lift when aircraft is put down and flown, at this moment need reduce engine wing area, reduce resistance and make aircraft reach flying speed as early as possible.Meanwhile, when flight reaches high speed, flight attitude is comparatively large by pneumatic impact, easily sideslip phenomenon occurs, and so the change of aircraft wing dihedral is just very important.
Summary of the invention
The purpose of this utility model is to overcome above-mentioned deficiency, provides a kind of adjustable wing aeromodelling aerocraft.
The technical solution of the utility model is such: this aircraft comprises wing and plunders angle actuation unit, wing dihedral actuation unit and wing position actuation unit;
Wing plunders that angle actuation unit comprises wing mount plate, plunders angle Servo-controller, plunders angle toothed disc, wing bearing rod and wing, wing mount plate is arranged on one end of wing, wing is arranged wing bearing rod, plunder angle toothed disc to be fixedly connected with wing bearing rod, plunder on the Servo-controller of angle with to plunder angle toothed disc external.
Wing dihedral actuation unit comprises chute, bent axle, dihedral toothed disc, dihedral Servo-controller and bearing; Dihedral toothed disc to be fixed on bearing and to be connected with bent axle, and chute is laterally arranged on the end of wing mount plate, and is connected with bent axle and forms sliding pair, and dihedral Servo-controller is arranged on bearing, dihedral Servo-controller and dihedral toothed disc external.
Wing position actuation unit comprises wing box girder, synchrome conveying belt, gear train, position servo steering wheel and wing box frame; Gear train and position servo steering wheel are arranged on wing box frame, and gear and the gear train of position servo steering wheel are external, and synchrome conveying belt connects gear train and bearing, and girder and synchrome conveying belt are fixed on bearing.
Described plunder gear on the Servo-controller of angle and to plunder angle toothed disc external.
Gear on described dihedral Servo-controller and dihedral toothed disc external.
The beneficial effects of the utility model:
Plunderred the change of angle, dihedral and position by wing, the flying quality of aeromodelling aerocraft can be promoted.
1, wing is plunderred angle actuation unit and can be changed the leading edge of a wing lift of aircraft in low speed and flight course, optimizes with this resistance, lift etc. that aircraft is subject to.
2, wing dihedral actuation unit can improve the lateral stability of aircraft in any flight course.
3, wing position actuation unit can balance wing and plunders angle and change the gravity center shift problem brought, and makes the flight course of aircraft more stable, is beneficial to manipulation.
A kind of adjustable wing aeromodelling aerocraft can be formed, to a certain extent for China's adjustable wing aircraft research is offered help by this integrated control system.
Accompanying drawing illustrates:
Fig. 1 is the utility model structural representation;
Fig. 2 is the top view of Fig. 1;
Fig. 3 is the right view of Fig. 1;
Fig. 4 is that wing plunders angle actuation unit structure chart;
Fig. 5 is the top view of Fig. 4;
Fig. 6 is the right view of Fig. 4;
Fig. 7 is wing dihedral actuation unit structure chart;
Fig. 8 is the top view of Fig. 7;
Fig. 9 is the right view of Fig. 7;
Figure 10 is wing position actuation unit structure chart;
Figure 11 is the top view of Figure 10;
Figure 12 is the right view of Figure 10;
In figure: 1, wing mount plate; 2, angle Servo-controller is plunderred; 3, angle toothed disc is plunderred; 4, wing bearing rod; 5, wing; 6, chute; 7, bent axle; 8, dihedral toothed disc; 9, dihedral Servo-controller; 10, bearing; 11, wing box girder; 12, synchrome conveying belt; 13, gear train; 14, position servo steering wheel; 15, wing box frame.
Detailed description of the invention
Below in conjunction with accompanying drawing and enforcement, the utility model is further described.
As shown in Figure 1,2 and 3, this aircraft comprises wing and plunders angle actuation unit, wing dihedral actuation unit and wing position actuation unit;
As shown in Fig. 4,5 and 6, wing plunders that angle actuation unit comprises wing mount plate 1, plunders angle Servo-controller 2, plunders angle toothed disc 3, wing bearing rod 4 and wing 5, wing mount plate 1 is arranged on one end of wing 5, wing 5 is arranged wing bearing rod 4, plunder angle toothed disc 3 to be fixedly connected with wing bearing rod 4, so that wing can only can rotate in the horizontal direction.Plunder gear on angle Servo-controller 2 and to plunder angle toothed disc 3 external, form the first gear unit, utilize the rotation driven gear of steering wheel to rotate and reach the variation effect that aircraft plunders angle.
When need to change wing plunder angle time, plunder angle Servo-controller 2 and receive the signal that remote controller sends and produce power, drive driving gear in the first gear unit to rotate, drive driven gear to turn an angle by the first gear unit link.Plunderring when angle toothed disc 3 rotates drives wing bearing rod 4 to rotate, and directly drive aircraft wing horizontal direction to rotate, namely wing plunders the change at angle.
As shown in Fig. 7,8 and 9, wing dihedral actuation unit comprises chute 6, bent axle 7, dihedral toothed disc 8, dihedral Servo-controller 9 and bearing 10; Dihedral toothed disc 8 to be fixed on bearing 10 and to be connected with bent axle 7.Chute 6 is laterally arranged on the end of wing mount plate 1, and is connected with bent axle 7 and forms sliding pair, and dihedral Servo-controller 9 is arranged on bearing 10, the gear on dihedral Servo-controller 9 and dihedral toothed disc 8 external, form the second gear unit.
When dihedral Servo-controller 9 receives the signal of the dihedral change that remote controller sends, the motor driving gear in dihedral Servo-controller 9 rotates, and by transmission system, dihedral toothed disc 8 is rotated, and is with dynamic crankshaft 7 to move in a circle.When bent axle 7 moves, make wing mount plate 1 with chute 6 for initial point does fan shape moving by sliding pair.Such as: when dihedral toothed disc 8 turns clockwise, band dynamic crankshaft 7 does clockwise movement, and chute 6 is moved downward, then wing 5 does counter-movement.
As shown in Figure 10,11 and 12, wing position actuation unit comprises wing box girder 11, synchrome conveying belt 12, gear train 13, position servo steering wheel 14 and wing box frame 15; Gear train 13 and position servo steering wheel 14 are arranged on wing box frame 15, and gear and the gear train 13 of position servo steering wheel 14 are external, and synchrome conveying belt 12 connects gear train and bearing.Girder 11 and synchrome conveying belt 12 are fixed on bearing 10.
When position servo steering wheel 14 receives wing evolution signal, drive position servo steering wheel 14 pinion rotation, slowed down by gear train 13, drive synchrome conveying belt 12 to run, synchrome conveying belt 12 pulls bearing 10 level run on wing box girder 11.
Operation principle of the present utility model: the flat wing of plunderring can be adopted when taking off to increase the lift that takes off, when enter flat fly state time, increasing wing setting by plunderring angular transformation unit, reducing resistance; When aircraft carry out front and back plunder time, in order to make the center of gravity of complete machine remain unchanged, the phenomenon that the position adopting wing position actuation unit to move aircraft is moved after the center of gravity balancing sweepback and bring; In order to unstable flight situations such as balance airplane sideslips, the upper and lower dihedral of aircraft can be changed by wing dihedral actuation unit.
Wing dihedral actuation unit have employed the structural design of bent axle-chute; Driving link is tampered steering wheel, is transported on a symmetrical bent axle by big retarding than gear by moment of torsion, then drives wing dihedral actuation unit, reaches dihedral change.
Wing plunder angle actuation unit be by steering wheel connect potentiometer and and gear, gearing makes wing can realize plunderring the change at angle in the bearing rod of wing.
Wing position actuation unit plunders angle in order to balance airplane to change displacement before and after the Center of Pressure that causes, and wing needs to be combined with to do front/rear displacement, to reach the constant object of aircraft focus; This power is provided by position servo steering wheel 14 and by gear train 13 deceleration transmission to Timing Belt, synchrome conveying belt 12 drives wing box to move forward and backward on wing box girder 11.
Claims (3)
1. an adjustable wing aeromodelling aerocraft, is characterized in that: this aircraft comprises wing and plunders angle actuation unit, wing dihedral actuation unit and wing position actuation unit;
Wing plunders that angle actuation unit comprises wing mount plate, plunders angle Servo-controller, plunders angle toothed disc, wing bearing rod and wing, wing mount plate is arranged on one end of wing, wing is arranged wing bearing rod, plunder angle toothed disc to be fixedly connected with wing bearing rod, plunder on the Servo-controller of angle with to plunder angle toothed disc external;
Wing dihedral actuation unit comprises chute, bent axle, dihedral toothed disc, dihedral Servo-controller and bearing; Dihedral toothed disc to be fixed on bearing and to be connected with bent axle, and chute is laterally arranged on the end of wing mount plate, and is connected with bent axle and forms sliding pair, and dihedral Servo-controller is arranged on bearing, dihedral Servo-controller and dihedral toothed disc external;
Wing position actuation unit comprises wing box girder, synchrome conveying belt, gear train, position servo steering wheel and wing box frame; Gear train and position servo steering wheel are arranged on wing box frame, and gear and the gear train of position servo steering wheel are external, and synchrome conveying belt connects gear train and bearing, and girder and synchrome conveying belt are fixed on bearing.
2. adopt adjustable wing aeromodelling aerocraft according to claim 1, it is characterized in that: described plunder gear on the Servo-controller of angle and to plunder angle toothed disc external.
3. adopt adjustable wing aeromodelling aerocraft according to claim 1, it is characterized in that: the gear on described dihedral Servo-controller and dihedral toothed disc external.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520372199.0U CN204709801U (en) | 2015-06-02 | 2015-06-02 | Adjustable wing aeromodelling aerocraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520372199.0U CN204709801U (en) | 2015-06-02 | 2015-06-02 | Adjustable wing aeromodelling aerocraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204709801U true CN204709801U (en) | 2015-10-21 |
Family
ID=54308834
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520372199.0U Expired - Fee Related CN204709801U (en) | 2015-06-02 | 2015-06-02 | Adjustable wing aeromodelling aerocraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204709801U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106428525A (en) * | 2016-11-11 | 2017-02-22 | 哈尔滨工业大学 | Flying robot with variable sweep angle launch tandem wings |
| CN112960143A (en) * | 2021-04-15 | 2021-06-15 | 沈阳航空航天大学 | Wing box and aircraft |
-
2015
- 2015-06-02 CN CN201520372199.0U patent/CN204709801U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106428525A (en) * | 2016-11-11 | 2017-02-22 | 哈尔滨工业大学 | Flying robot with variable sweep angle launch tandem wings |
| CN106428525B (en) * | 2016-11-11 | 2019-09-13 | 哈尔滨工业大学 | A kind of variable sweep angle ejection tandem arrangement rotor flying robot |
| CN112960143A (en) * | 2021-04-15 | 2021-06-15 | 沈阳航空航天大学 | Wing box and aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| WO2017016096A1 (en) | Novel vertical take-off and landing aircraft and control method therefor | |
| CN203681869U (en) | Power system structure suitable for vertical take-off and landing air vehicle | |
| CN105173061A (en) | Plane in supersonic speed plane layout | |
| CN202358300U (en) | Variable pitch three-axis aircraft | |
| CN103587683A (en) | Small-sized aircraft with tiltable rotor wings | |
| CN102001446B (en) | Structure of vertical take-off and landing rotor aircraft | |
| CN102514712A (en) | Vertical take-off and landing aircraft | |
| CN204916182U (en) | High -speed vertical take -off and landing aircraft | |
| CN103057702B (en) | Jet-propelled type helicopter with rotating wings | |
| CN103318410A (en) | Vertical take-off and landing micro aerial vehicle without control surface | |
| CN105015795A (en) | Airplane design method and scheme | |
| CN205239908U (en) | Fixed tilt angle rotor craft | |
| CN205396534U (en) | Rotor unmanned aerial vehicle verts | |
| CN204709801U (en) | Adjustable wing aeromodelling aerocraft | |
| CN205738073U (en) | A kind of helicopter of VTOL horizontal flight | |
| CN202923886U (en) | Plane with high safety | |
| CN105235903A (en) | Bionic swing wing aircraft | |
| CN204568062U (en) | One can be hovered flapping wing aircraft | |
| CN104670495B (en) | One can hover flapping wing aircraft and flight mode | |
| CN202481307U (en) | Four-propeller aircraft taking off and landing vertically | |
| CN109911189A (en) | A kind of horizontal double rotor unmanned plane based on 3D printing | |
| CN201520409U (en) | Backward-forward dual-rotor one-man aerobat | |
| CN107380426A (en) | A kind of compound unmanned plane of rotary shaft | |
| CN203020542U (en) | Jet-propelled rotor helicopter | |
| CN203525315U (en) | Vertical take-off and landing fixed-wing model plane toy |
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 | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20151021 Termination date: 20160602 |