CN210235305U - Flying wing type airplane with variable outer wing sweepback angle and tiltable winglet - Google Patents
Flying wing type airplane with variable outer wing sweepback angle and tiltable winglet Download PDFInfo
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- CN210235305U CN210235305U CN201920742690.6U CN201920742690U CN210235305U CN 210235305 U CN210235305 U CN 210235305U CN 201920742690 U CN201920742690 U CN 201920742690U CN 210235305 U CN210235305 U CN 210235305U
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Abstract
The utility model discloses a winged aircraft of variable wing outer wing sweepback angle and tilting winglet, winged aircraft have interior wing leading edge, outer wing leading edge, winglet, outer wing trailing edge, interior wing trailing edge, lift aileron, and the outer wing sets up the both sides at the inner wing, and the winglet sets up the wing tip at the outer wing, and the outer wing all adopts flexible covering structure with the winglet, is provided with the first mechanism that actuates between outer wing and the inner wing, is provided with the second between winglet and the outer wing and actuates the mechanism. The utility model ensures that the airplane has higher lift resistance characteristic; the maximum flight speed of the flying wing type airplane can be improved, and meanwhile, the resistance of each speed stage is reduced, so that the flying wing type airplane can exert the efficiency of the flying wing type airplane on a fighter.
Description
Technical Field
The utility model belongs to the airborne vehicle field, the winged aircraft of a variable wing outer wing sweepback angle and tilting winglet of a concrete design.
Background
The swept-back wing is mainly used for modern transonic and supersonic aircrafts. The selection of the sweep angle of the outer wing of the double-sweep wing plays a crucial role in the overall performance of the airplane; the small sweep angle of the outer wing is beneficial to improving the maneuverability of the transonic aircraft, but the lift force is small during supersonic flight, so that the rapid flight cannot be realized; the large sweep angle of the outer wing is beneficial to realizing supersonic flight and completing the penetration task, but the lift force is small when taking off and landing, and short-distance sliding cannot be realized. The variable wing outer wing sweepback angle airplane has the greatest advantage that the sweepback angle can be changed, so that the performance of the airplane in high-speed and low-speed flight can be optimized. The first variable sweep wing fighter in the world was F-111, successfully developed by the U.S. general Power company in 1965, and Mige-23, which began to be in service in 1970, was one of the leading interceptor species in the 80 th century of the Soviet Union 20.
Wingtip winglets can effectively reduce the induced drag of the airplane. However, the traditional wingtip winglet can only reduce the drag in the cruising state, and has lower drag reduction efficiency in the off-design state of takeoff, climbing and the like. The wingtip winglet capable of being folded can well solve the problem, and the optimal drag reduction effect can be provided in the whole flight envelope by changing the tilting angle of the wingtip winglet in real time according to the flight state. The Morpthlet project developed by the airline company of air passengers and Bristol university adopts a servo motor as a mechanism for driving the winglet to tilt at an angle, and can improve the lift-drag ratio by 3% in the takeoff stage under the condition of keeping cruise drag reduction unchanged.
With the development of economy, the comprehensive requirements of people on flight tasks are continuously improved, and the aircraft can stably execute various tasks under different conditions and always keep good flight performance, which is a new requirement of people on the aircraft and is a great trend of the development of flying wing type aircrafts. The development of electronic technology and computer control technology, the line control stability augmentation technology and the static stability relaxation technology are gradually mature, and conditions are provided for the development of the flying wing type pneumatic layout airplane. The flying wing type airplane has no fuselage, so that the wings of the flying wing type airplane are much thicker than the conventional wings, and have no great influence on low-speed flight, but when the airplane approaches the sonic speed, the wings generate great drag effect, so that the flying wings are not suitable for high-speed flight and are more sensitive to drag than the common airplane. The flying wing has good lift-drag characteristics, and is beneficial to improving the stealth of the airplane due to no vertical fin, so that the flying wing is very suitable for being used as a fighter, but in order to ensure the good maneuverability and lift-drag characteristics of the flying wing, the flying wing mostly adopts small wing load, the flying speed is low, but if the flying speed of the flying wing is increased to be applied to the fighter, the wing load is increased essentially, so the flight wing is an inevitable contradiction in the current-stage development process of the flying wing.
SUMMERY OF THE UTILITY MODEL
In order to solve the technical problem, the utility model provides a winged aircraft of variable wing outer wing sweepback angle and tilting winglet. The invention aims to overcome the defects that the existing flying wing type airplane cannot solve the contradiction that good maneuverability and higher speed are needed when the airplane is used for battle flight and cannot keep the resistance reduction effect under all conditions.
The utility model discloses concrete scheme is as follows:
the utility model provides a variable wing outer wing sweepback angle and all right wing's all right wing tip, outer wing and winglet all adopt flexible covering structure, be provided with first mechanism of actuating between outer wing and the inner wing, first mechanism of actuating is used for driving the sweepback angle of outer wing in front and back direction, be provided with the second between winglet and the outer wing and actuate the mechanism, the second actuates the mechanism and is used for driving the winglet and upwards inclines in the vertical direction.
Further, flexible supporting rods are arranged inside the outer wing and the winglet.
Furthermore, the outer wing is provided with a point with the relative position of the inner wing unchanged, the first actuating mechanism comprises a first motor, a first rocker connected with an output shaft of the first motor and a second rocker hinged with the first rocker, and the second rocker is rotatably connected with the outer wing.
Furthermore, the second actuating mechanism comprises a second motor, a third rocker connected with an output shaft of the second motor, a first rod fixedly connected with the outer wing of the wing, and a second rod fixedly connected with the winglet, the first rod and the second rod are hinged through end parts, and one end of the third rocker can move on the second rod.
The technical solution of the utility model is as follows: the design of the variable wing outer wing sweepback angle and the tiltable small wing type flying wing aircraft structurally comprises the integral appearance of the fused wing body, a lifting aileron, a power device and a control system, and the design is mainly as follows: the wing tip winglet comprises a wing outer wing with a variable sweep angle, a tiltable wing tip winglet and an actuating mechanism connecting the wing outer wing and the tiltable wing tip winglet. The winglets are basically trapezoidal, the outer wings of the wings with variable sweepback angles are parallelogram-shaped, and the sweepback angles and the winglets inclination angles can be effectively changed by applying the flexible honeycomb skin technology to the morphing aircraft, so that the good aerodynamic layout and lift-drag characteristics of the flying wing aircraft are guaranteed. The actuating mechanism is respectively arranged between the winglet and the outer wing of the wing with the variable sweep angle and between the outer wing of the wing with the variable sweep angle and the fixed front-section wing, and plays a role in adjusting the angle.
The utility model has the advantages that: the design of the winged aircraft with the variable sweep angle of the outer wings of the wings and the tiltable winglets firstly has the good maneuverability and stealth performance of the winged aircraft and can ensure that the aircraft has higher lift resistance; and secondly, the design of the sweep angle of the outer wing of the wing with variable angles and the design of winglets are added, so that the maximum flight speed of the flying wing type airplane can be improved, and the resistance of each speed stage is reduced, so that the flying wing type airplane can exert the efficiency of the flying wing type airplane.
Drawings
FIG. 1 is a top view of a whole flying wing aircraft with variable sweep angle of outer wings and tiltable winglets;
FIG. 2 is a schematic diagram of the sweep angle of the outer wing of the airfoil varying in angle;
FIG. 3 is a schematic view of the winglet folded at different angles and in perspective;
FIG. 4 is an actuator between the outer wing and the inner wing;
FIG. 5 is an actuating mechanism between a winglet and an outer wing;
in the figure, an inner wing leading edge 1, an outer wing leading edge 2, a winglet 3, an outer wing trailing edge 4, an inner wing trailing edge 5, a lifting aileron 6, a middle position 7 of an outer wing of a wing, a maximum position 8 of forward sweep of the outer wing of the wing, a maximum position 9 of backward sweep of the outer wing of the wing, a position 10 of maximum inclined angle of the winglet, a position 11 of medium inclined angle of the winglet, a position 12 of no inclined angle of the winglet, a point 13 of constant relative position of the outer wing and the inner wing of the wing, a first rocker 14, a second rocker 15, a first rod 16, a second rod 17 and a third rocker 18.
Detailed Description
The flying wing type airplane with variable outer wing sweepback angle and tiltable winglets is to raise the lift-drag ratio and stealth performance of the airplane and to take into account the advantages of high speed and low speed aerodynamic performance on the premise of actual flight.
Combine fig. 1-5, the utility model discloses a concrete scheme does, a variable wing outer wing sweepback and the all-wing aircraft formula aircraft of tilting winglet, all-wing aircraft formula aircraft has interior wing leading edge 1, outer wing leading edge 2, winglet 3 (the wing tip winglet that can tilt over), outer wing trailing edge 4, interior wing trailing edge 5, lift aileron 6, and the outer wing sets up in the both sides of inner wing, and winglet 3 sets up the wing tip at the outer wing, the outer wing all adopts flexible skin structure with winglet 3, be provided with first actuating mechanism between outer wing and the inner wing, first actuating mechanism is used for driving the outer wing in the sweepback of front and back direction and is makeed the angle, be provided with the second between winglet and the outer wing and actuate the mechanism, the second actuates the mechanism and is used for driving the winglet and upwards rotates in the vertical direction. The inner parts of the outer wing and the winglet 3 are provided with flexible support rods (not shown in the figure). The outer wing is provided with a point 13 with a position unchanged relative to the inner wing, the first actuating mechanism comprises a first motor (not shown in the figure), a first rocker 14 connected with an output shaft of the first motor, and a second rocker 15 (a rocker driving the outer wing to rotate around the point 13) hinged with the first rocker 14, and the second rocker 15 is rotatably connected with the outer wing. The second actuating mechanism comprises a second motor (not shown in the figure), a third rocker 18 (a rocker capable of driving the winglet to rotate) connected with an output shaft of the second motor, a first rod 16 fixedly connected with the outer wing of the wing, and a second rod 17 fixedly connected with the winglet, wherein the first rod 16 is hinged with the second rod 17 through the end part, and one end of the third rocker 18 can move on the second rod 17.
The utility model discloses the main implementation steps of winged aircraft of grazing angle and winglet of can turning over behind variable wing outer wing include:
1. and (4) a takeoff phase. By adopting a smaller wing outer wing sweepback angle 8 (the maximum position 8 of the wing outer wing sweepforward) and a winglet 12 without a tilt angle (the position of the winglet without a tilt angle), the lift force of the wing leading edge can be increased, the take-off running distance can be reduced, and the induced resistance can be reduced while no other resistance is additionally increased.
2. And a cruising stage. By adopting the middle sweep angle 7 of the outer wing of the wing (the middle position 7 of the outer wing of the wing) and the winglet 11 inclined at the middle angle (the position 11 with the middle inclination angle of the winglet), the induced resistance during subsonic cruise is effectively reduced on the premise of ensuring the lift force, so that the flying wing has longer voyage and longer endurance time.
3. And (5) a defense penetration stage. By adopting a larger wing outer wing sweepback angle 9 (the maximum position 9 of the wing outer wing sweepback) and a winglet 10 inclined at a larger angle (the position 10 of the maximum winglet inclination angle), the maneuverability and the invisibility of the flying wing can be effectively improved while the large sweepback angle and the aerodynamic shape of the flying wing structure are increased in the task completion stage, and the wing tip winglet inclined at a large angle can more effectively reduce the induced resistance in the flight at the supersonic speed stage.
4. And (5) a descending stage. The same takeoff phase.
The specific embodiment is that the variable-wing outer wing sweepback angle and the tiltable small-wing flying-wing aircraft are used, the flight speed v is 200m/s, the sweepback angle α is 30 degrees, and the winglet tilting angle β is 30 degrees, and the flying-wing aircraft can completely realize the designated task under the design condition according to the design method disclosed by the patent.
The airplane generated by the application combines the advantages of the morphing airplane and the flying wing type airplane, realizes the optimal lift force, maneuvering characteristics and drag reduction effect during high-speed and low-speed flight, and can effectively complete flight tasks, thereby improving the overall performance of the airplane.
Claims (4)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920742690.6U CN210235305U (en) | 2019-05-22 | 2019-05-22 | Flying wing type airplane with variable outer wing sweepback angle and tiltable winglet |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920742690.6U CN210235305U (en) | 2019-05-22 | 2019-05-22 | Flying wing type airplane with variable outer wing sweepback angle and tiltable winglet |
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| Publication Number | Publication Date |
|---|---|
| CN210235305U true CN210235305U (en) | 2020-04-03 |
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| CN201920742690.6U Expired - Fee Related CN210235305U (en) | 2019-05-22 | 2019-05-22 | Flying wing type airplane with variable outer wing sweepback angle and tiltable winglet |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110182353A (en) * | 2019-05-22 | 2019-08-30 | 厦门大学 | A kind of flying wing of variable geometry outboard wing sweep and tiltable winglet |
| CN111994256A (en) * | 2020-08-07 | 2020-11-27 | 山东理工大学 | Variable sweep angle and profile wing |
| CN112977818A (en) * | 2021-02-09 | 2021-06-18 | 南京航空航天大学 | Bionic winglet feather structure capable of changing flow around wing surface of leading edge of flapping wing aircraft |
| CN113044200A (en) * | 2021-04-20 | 2021-06-29 | 西北工业大学 | Novel solar unmanned aerial vehicle layout with connection wings close to space |
-
2019
- 2019-05-22 CN CN201920742690.6U patent/CN210235305U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110182353A (en) * | 2019-05-22 | 2019-08-30 | 厦门大学 | A kind of flying wing of variable geometry outboard wing sweep and tiltable winglet |
| CN111994256A (en) * | 2020-08-07 | 2020-11-27 | 山东理工大学 | Variable sweep angle and profile wing |
| CN112977818A (en) * | 2021-02-09 | 2021-06-18 | 南京航空航天大学 | Bionic winglet feather structure capable of changing flow around wing surface of leading edge of flapping wing aircraft |
| CN112977818B (en) * | 2021-02-09 | 2022-04-22 | 南京航空航天大学 | A bionic winglet structure that can change the flow around the leading edge of a flapping aircraft |
| CN113044200A (en) * | 2021-04-20 | 2021-06-29 | 西北工业大学 | Novel solar unmanned aerial vehicle layout with connection wings close to space |
| CN113044200B (en) * | 2021-04-20 | 2023-10-27 | 西北工业大学 | Solar unmanned aerial vehicle layout in adjacent space of connecting wing |
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Granted publication date: 20200403 Termination date: 20210522 |