CN110901889B - Variant aircraft - Google Patents
Variant aircraft Download PDFInfo
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- CN110901889B CN110901889B CN201911228905.3A CN201911228905A CN110901889B CN 110901889 B CN110901889 B CN 110901889B CN 201911228905 A CN201911228905 A CN 201911228905A CN 110901889 B CN110901889 B CN 110901889B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/06—Fins
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/06—Adjustable control surfaces or members, e.g. rudders with two or more independent movements
Abstract
The invention belongs to the technical field of aircraft design, and particularly relates to a morphing aircraft. The morphing aircraft comprises a fuselage, an inner morphing wing section, an outer morphing wing section, a high-speed wing section and a morphing mechanism; wherein, the inner variable wing section is rotationally connected with the fuselage; the wing sections are connected in a rotating way; the inner variable wing panel and the outer variable wing panel form a variable wing panel, and the variant operation is realized through a variant mechanism; control surfaces are arranged on the inner variable wing panel, the outer variable wing panel and the high-speed wing panel; the morphing aircraft provided by the invention uses a large aspect ratio at a low speed, realizes high-efficiency flight and shortens the running distance; the high-speed high-maneuverability aircraft has the advantages that the high-speed high-maneuverability aircraft is changed at high speed, so that the resistance is reduced, the maneuverability is improved, and the high-speed high-maneuverability target is comprehensively realized; the design configuration provided by the invention greatly improves the flight speed and maneuverability of the aircraft.
Description
Technical Field
The invention belongs to the technical field of aircraft design, and particularly relates to a morphing aircraft.
Background
The ratio of span to mean chord length, called the aspect ratio, can also be expressed as the ratio of the square of the span to the area of the wing. The aircraft with a large aspect ratio has a larger lift coefficient, so that the proportion of induced resistance to resistance can be reduced, the wing efficiency is improved, and the voyage is increased; the small aspect ratio aircraft has small lift coefficient and small resistance, which shows that the flight speed is fast, the maneuverability is flexible, and when the aspect ratio is increased, the induced resistance of the wing can be reduced, thereby improving the maneuverability of the aircraft and increasing the subsonic range, but the wave resistance can be increased to influence the flight supersonic flight performance.
The wing areas are the same, and under the same condition, the wing lift force with large aspect ratio is large, so that the takeoff and landing distances of the airplane can be reduced. According to the flight characteristics of different aspect ratios, the subsonic aircraft generally adopts wings with a large aspect ratio, mainly large-range and low-maneuverability aircraft, for example, the aspect ratio of a B-52 bomber is 6.5, the aspect ratio of a U-2 scout is 10.6, and the aspect ratio of a global eagle unmanned aerial vehicle is 25; the supersonic fighter has a small aspect ratio, can fly at high speed and complete high-maneuverability tactical actions, and is generally 2.0-4.0.
The aircrafts with fixed aspect ratios are generally used for fixing, only one aspect of low-speed high-efficiency or high-speed high-maneuverability can be realized, and the advantages of low-speed high-efficiency and high-speed high-maneuverability cannot be integrated. Therefore, in order to meet the requirements of different flight states, the technology of the morphing wing is developed. However, in the existing morphing wing technologies, such as a telescopic morphing wing in CN201711299673.1 and a folding wing in CN201711299674.6, both adopt flexible skins, the number of pivots is large, the span change is small, the requirements of low speed and large span cannot be met, and when the load is large, the flexible skin shape becomes large, the stable aerodynamic shape cannot be ensured, and the overall flight performance is affected.
In addition, the folding adopted by a certain existing variable-span aircraft is that the center of gravity is arranged below the wing by vertically folding the inner wing upwards and folding the outer wing to the horizontal direction, so that the center of gravity generates a reverse restoring moment relative to the rotation center during rolling flight, and the adjusting force delta L of the gravity G of the aircraft relative to a control surface is large, so that the influence on the rolling attitude adjusting effect is large
Disclosure of Invention
The purpose of the invention is as follows: because the aircrafts with fixed aspect ratios are generally used for fixation, only one aspect of low-speed high efficiency or high-speed high maneuverability can be realized, and the advantages of the two aspects of low-speed high efficiency and high maneuverability cannot be integrated, the variant aircrafts are provided, and use the large aspect ratio at low speed, realize high-efficiency flight and shorten the running distance; the high-speed high-maneuverability aircraft has the advantages that the high-speed high-maneuverability aircraft is changed into the low-aspect-ratio aircraft, the resistance is reduced, the maneuverability is improved, and the high-speed high-maneuverability target is comprehensively realized.
The technical scheme of the invention is as follows: a morphing aircraft comprises a fuselage, an inner morphing wing section, an outer morphing wing section, a high-speed wing section and a morphing mechanism; the inner variable wing section, the outer variable wing section and the high-speed wing section are symmetrically arranged on two sides of the middle part of the airplane body after being sequentially and rotatably connected; the inner variable wing panel and the outer variable wing panel form a variable wing panel, and the variant operation is realized through a variant mechanism; control surfaces are arranged on the inner variable wing panel, the outer variable wing panel and the high-speed wing panel.
The invention provides a variant aircraft, which comprises the following specific variant operations: at low speed, the variant mechanism extends, the inner variant wing section, the outer variant wing section and the high-speed wing section jointly form a wing with a large aspect ratio, the operation of the aircraft is the same as that of a flying wing aircraft, and the control surface is used for adjusting the pitching attitude and the rolling attitude of the aircraft; the control surfaces on the two sides are adjusted in the same direction, namely the pitching attitude of the aircraft can be adjusted by deflecting upwards or downwards at the same time; the control surfaces on the two sides are reversely adjusted, namely, the control surfaces deflect upwards and downwards at the same time to adjust the rolling attitude of the aircraft; the yaw attitude of the aircraft can be adjusted by deflecting the control surface on the same side up and down in the opposite direction.
In the transition from low speed to high speed, the variant mechanism gradually shrinks to draw the lower surfaces of the inner variant wing section and the outer variant wing section, in the drawing process, the inner variant wing section and the outer variant wing section are both changed into half wing sections, wherein the lower surfaces are upwards recycled to be changed into planes, after the lower surfaces are completely drawn and attached, a complete symmetrical wing section is formed, at the moment, the inner variant wing section and the outer variant wing section are upwards erected to be changed into vertical tails, and the control surfaces on the vertical tails are used for adjusting and controlling the course attitude of the aircraft.
At high speed, the aircraft variant is a flying wing aircraft with vertical tails, the adjustment of the yaw attitude is changed, and the control surfaces on the same side of the high-speed wing section deflect in the up-and-down direction; meanwhile, a control surface on a vertical tail formed by the inner/outer variable wing sections deflects left and right to cooperate with the yaw attitude control.
The invention has the beneficial technical effects that: according to the morphing aircraft, the variable wing with the long span of the expander is adopted during low-speed flight, the aerodynamic force is small during low-speed flight, the aerodynamic force borne by the variable wing is small at the moment, the flight efficiency can be improved, and the take-off and landing sliding distance can be shortened; at high speed, the wing body is in a high-speed configuration, the inner side wings are folded and spliced to form vertical tails, the flying speed and the maneuverability can be improved according to the aspect ratio, meanwhile, the vertical tails are added relative to the flying wing aircraft, and the maneuverability in a high-speed state is further improved. In addition, the variant mechanism is arranged on the wing beam, aerodynamic force of the wing can be borne, the force transmission structure is more reliable and efficient compared with a plurality of sections of folding rods, the force transmission effect of the wing can be effectively guaranteed, the wing is flat and straight as a whole, the bending moment applied to the locking mechanism is small, the strength requirement on the locking mechanism can be reduced, and the weight of the airplane body can be reduced.
Drawings
FIG. 1 is an axial view of a variation of the aircraft of the present invention at low speed;
FIG. 2 is a top view of a variation of the aircraft of the present invention at low speed;
FIG. 3 is a front view of a variation of the aircraft of the present invention at low speed;
FIG. 4 is a side view of a variation of the aircraft of the present invention at low speed;
FIG. 5 is a schematic view of the construction of the variable wing section of the present invention;
FIG. 6 is an axial view of the invention in a variation;
FIG. 7 is a schematic view of the present invention in a variation retracting the variable rib;
FIG. 8 is a schematic illustration of the present invention in a variant drawing two variable wing sections together;
fig. 9-12 are axial, top, front and side views, respectively, of the present invention at high speeds.
Description of numbering: 1-fuselage, 2-inner variable wing section, 3-outer variable wing section, 4-high speed wing section, 6-variant mechanism, 7-first control surface, 8-vertical tail control surface, 21-rigid upper wing surface, 22-flexible lower wing surface, 23-fixed wing rib, 24-variable wing rib, 25-control surface control mechanism, 27-second control surface and 37 third control surface.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without making any creative effort based on the embodiments in the present invention, belong to the protection scope of the present invention.
Referring to the accompanying drawings 1-12, a specific configuration of a morphing aircraft is shown in fig. 1, and the aircraft comprises a fuselage 1, and an inner morphing wing section 2, an outer morphing wing section 3 and a high-speed wing section 4 which are symmetrically arranged on two sides of the fuselage, wherein the inner morphing wing section 2 and the outer morphing wing section 3 realize morphing control through a morphing mechanism 6; wherein, the inner variable wing section 2 is rotationally connected with the fuselage 1; the wing sections are connected in a rotating way; the inner variable wing panel 2 and the outer variable wing panel 3 form a variable wing panel, and the variant operation is realized through a variant mechanism 6; the high-speed wing panel 4 is provided with a first control surface 7 which is a horizontal tail control surface, and the inner variable wing panel 2 and the outer variable wing panel 3 are respectively provided with a second control surface 27 and a third control surface 37.
The inner variable wing section 2 comprises a rigid upper wing surface 21, a flexible lower wing surface 22, a fixed wing rib 23, a variable wing rib 24, a control surface steering mechanism 25 and a second control surface 27. Wherein the rigid upper wing surface 21 is arranged above the fixed wing rib 23, the flexible lower wing surface 22 is arranged below the variable wing rib 24, the variant mechanism is arranged below the front end of the variable wing rib 24, and the control surface operating mechanism 25 and the second control surface 27 are arranged at the rear end of the inner variant wing section 2.
In addition, the inner variable wing section 2 is hinged with one side of the fuselage.
The structure of the outer variable wing section 3 is similar, one side of the outer variable wing section is hinged with the inner variable wing end, the outer variable wing section can extend and be parallel or folded and involuted under the extension and contraction of the variable mechanism, and the other side of the outer variable wing section is hinged with the high-speed wing section 4 so as to be convenient for folding, extending and deforming.
The variant mechanism is a telescopic rod body, one end of which passes through the mounting groove of the variable wing rib 24 below the inner variant wing section 2 and is connected with the fuselage. The other end of the variable wing rib is positioned below the external variable wing section 3, is fixedly connected with the high-speed wing section 4, is used as a high-speed wing end wing beam bearing and force transmission mechanism, can bear the aerodynamic force of the wing, can effectively ensure the force transmission effect of the wing, is flat and straight with the whole wing, effectively ensures the high-speed flight performance, has small bending moment applied to the locking mechanism, can reduce the strength requirement on the locking mechanism, and reduces the weight of the aircraft body. Meanwhile, a certain gap is formed between the variable mechanism and the hinged parts of the inner and outer variable wing sections, so that interference is avoided. The variable mechanism is a multi-section telescopic rod body, and the length of the variable mechanism is controlled by a control system in the machine body through an internal circuit.
In the flying process of the aircraft, in a low-speed state, the flying posture is as shown in fig. 1-4, at this time, the morphing mechanism 6 extends, the inner variant wing section 2, the outer variant wing section 3 and the high-speed wing section 4 are arranged straightly to form a wing with a large aspect ratio, and the morphing mechanism 6 is in an extending state and is positioned below the flexible lower wing surfaces of the inner variant wing section 2 and the outer variant wing section 3. The aircraft manipulation at the moment is the same as that of a flying wing aircraft, and is performed through a first control surface 7 arranged on an inner variable wing section 2, an outer variable wing section 3 and a high-speed wing section 4, wherein the control surfaces on two sides are adjusted in the same direction, namely the pitch attitude of the aircraft can be adjusted by deflecting upwards or downwards at the same time; the control surfaces on the two sides are reversely adjusted, namely, the control surfaces deflect upwards and downwards at the same time to adjust the rolling attitude of the aircraft; the yaw attitude of the aircraft can be adjusted by deflecting the control surface on the same side up and down in the opposite direction.
The transition of the aircraft from low speed to high speed, the flight attitude is as shown in fig. 6 and 8, at this time, the variant mechanism 6 gradually contracts to draw the lower surfaces of the inner variant wing section 2 and the outer variant wing section 3, in the drawing process, the inner variant wing section 2 and the outer variant wing section 3 are both changed into half wing shapes, the flexible lower wing surfaces of the inner variant wing section and the outer variant wing section are upwards recovered and folded, and after the complete drawing and attaching, a complete symmetrical wing shape is formed. At this moment, the variable wing section becomes the vertical fin for this vertical fin and wing are on same wing spar, therefore structural strength is high, and course balance, stability and maneuverability are good, and this vertical fin is the rectangle, and its area is 30% -70% of wing area, and this big vertical fin can promote this unmanned aerial vehicle high-speed flying's stability and maneuverability by a wide margin. The control surface on the variable wing section is used for course attitude adjustment and control of the aircraft, and the problem of large turning radius of the flying wing layout aircraft can be effectively solved. Meanwhile, the flexible lower wing surface is contained in the inner variable wing section 2 and the outer variable wing section 3, so that deformation and damage caused by high load during high-speed movement can be effectively avoided.
During the drawing process, the variable wing rib 24 is made of memory metal and can be controlled to retract into the projection plane of the fixed wing rib 23 through a material memory deformation or control mechanism, and meanwhile, the flexible lower wing surface 22 also follows the lower surface of the fixed wing rib 23, and the lower surface of the wing profile becomes a plane; the variant mechanism 6 contracts to draw the lower surfaces of the inner variant wing section 2 and the outer variant wing section 3, so that the lower surfaces of the inner variant wing section 2 and the outer variant wing section 3 are attached together, the variant wing section becomes a vertical tail, and at the moment, the second control surface 27 of the inner variant wing section 2 and the third control surface 37 of the outer variant wing section 3 are combined into a vertical tail control surface 8 for improving the course attitude adjustment effect of the aircraft, and meanwhile, the flexible lower wing surface between the inner variant wing section 2 and the outer variant wing section 3 can be effectively protected, and the damage caused by overlarge load during high-speed flight is avoided. Compared with the original flying wing configuration, the speed of course attitude adjustment is higher, the wings only have the high-speed wing sections 4 on the outer sides, the high-speed configuration aircraft is changed, the wings and the vertical tails have small aspect ratio, high-speed and high maneuverability can be realized, the flying wings at low speed have more vertical tails, and the maneuverability at high speed is further improved.
At high speed, the flight attitude is as shown in fig. 9-12, at this time, the variant mechanism is safely contracted, the variable wing sections on both sides of the fuselage are pulled into a complete symmetrical wing profile, at this time, the aircraft variant is a flying wing aircraft with vertical tails, the adjustment of the yaw attitude is changed, and the control surfaces on the same side of the high-speed wing sections reversely deflect up and down; meanwhile, a control surface on a vertical tail formed by the inner/outer variable wing sections deflects left and right to cooperate to realize yaw attitude control. Under the high-speed state, the yaw adjustment of the vertical tail control surface is added on the basis of the original pure up-down reverse adjustment of the control surface of the wing on one side in the course adjustment, the yaw adjustment moment is increased, the agility of the course attitude adjustment can be improved, and the condition that the yaw attitude adjustment of the flying wing layout aircraft is slow is obviously improved.
When the variant aircraft is actually designed, the rotary connection between the variable wing section and the aircraft body, and the rotary connection between the inner variable wing section 2, the outer variable wing section 3 and the high-speed wing section 4 can adopt a hinged connection mode, and specifically can be hinged through hinges or other modes.
The foregoing is merely a detailed description of the embodiments of the present invention, and some of the conventional techniques are not detailed. The scope of the present invention is not limited thereto, and any changes or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (8)
1. A morphing aircraft, characterized by: the variable wing aircraft comprises an aircraft body, an inner variable wing section, an outer variable wing section, a high-speed wing section and a variable mechanism; the inner variable wing section comprises a rigid upper wing surface, a flexible lower wing surface, a fixed wing rib, a variable wing rib, a control surface control mechanism and a control surface, wherein the rigid upper wing surface is arranged above the fixed wing rib, the flexible lower wing surface is arranged below the variable wing rib, the variant mechanism is arranged below the front end of the variable wing rib, and the control surface control mechanism and the control surface are positioned at the rear end of the inner variable wing section; the variable wing structure comprises a fuselage, an inner variable wing section, an outer variable wing section and a high-speed wing section, wherein the fuselage, the inner variable wing section, the outer variable wing section and the high-speed wing section are sequentially connected and arranged, the inner variable wing section and the outer variable wing section form a variable wing section, the variable wing section is stretched and retracted by a variable mechanism arranged below the variable wing section to realize variable operation, and after the inner variable wing section and the outer variable wing section are folded, the variable wing section and the outer variable wing section are symmetrically and vertically arranged on two sides of the fuselage and are used as vertical tails for adjusting the flight course;
when the aircraft is at high speed, the variant mechanism is completely contracted, the variable wing sections on the two sides of the fuselage are pulled into a complete symmetrical wing profile, at the moment, the aircraft variant is a flying wing aircraft with vertical tails, the adjustment of the yaw attitude is changed, and the control surfaces on the same side of the high-speed wing sections reversely deflect up and down; meanwhile, a control surface on a vertical tail formed by the inner/outer variable wing sections deflects left and right to cooperate with the yaw attitude control.
2. The morphing aircraft of claim 1, wherein: the variant mechanism and the control surface control mechanism are connected with and controlled by an airborne servo control system arranged in the machine body.
3. The morphing aircraft of claim 1, wherein: the variable rib is made of a memory alloy.
4. The morphing aircraft of claim 1, wherein: the inner variable wing section is hinged with the airplane body, the inner variable wing section is hinged with the outer variable wing section, and the outer variable wing section is hinged with the high-speed wing section.
5. The morphing aircraft of claim 4, wherein: and control surfaces are arranged on the inner variable wing panel, the outer variable wing panel and the high-speed wing panel.
6. The morphing aircraft of claim 1, wherein: the method for adjusting the pitching attitude and the rolling attitude of the aircraft comprises the following steps: the control surfaces on the two sides of the aircraft body are adjusted in the same direction, namely the pitching attitude of the aircraft can be adjusted by deflecting upwards or downwards at the same time; the control surfaces on the two sides are reversely adjusted, namely, the control surfaces deflect upwards and downwards at the same time to adjust the rolling attitude of the aircraft; the yaw attitude of the aircraft can be adjusted by deflecting the control surface on the same side up and down in the opposite direction.
7. The morphing aircraft of claim 6, wherein: when the aircraft flies at low speed, the variant operation method comprises the following steps: the variant mechanism extends, the inner variant wing section, the outer variant wing section and the high-speed wing section jointly form a wing with a large aspect ratio, and the operation of the aircraft is the same as that of an all-wing aircraft.
8. The morphing aircraft of claim 7, wherein: when the aircraft transits from low speed to high speed, the variant operation method comprises the following steps: the deformation mechanism gradually shrinks to draw the lower surfaces of the inner variable wing section and the outer variable wing section, the inner variable wing section and the outer variable wing section are changed into half wing sections in the drawing process, the lower surfaces are upwards recycled to be changed into planes, and after the lower surfaces are completely drawn and attached, a complete symmetrical wing section is gradually formed; the inner variable wing section and the outer variable wing section are erected upwards to be changed into vertical tails, and control surfaces on the vertical tails are used for course attitude adjustment and control of the aircraft.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911228905.3A CN110901889B (en) | 2019-12-04 | 2019-12-04 | Variant aircraft |
| PCT/CN2020/000188 WO2021109312A1 (en) | 2019-12-04 | 2020-08-24 | Morphing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911228905.3A CN110901889B (en) | 2019-12-04 | 2019-12-04 | Variant aircraft |
Publications (2)
| Publication Number | Publication Date |
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| CN110901889A CN110901889A (en) | 2020-03-24 |
| CN110901889B true CN110901889B (en) | 2023-04-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201911228905.3A Active CN110901889B (en) | 2019-12-04 | 2019-12-04 | Variant aircraft |
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| Country | Link |
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| CN (1) | CN110901889B (en) |
| WO (1) | WO2021109312A1 (en) |
Families Citing this family (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110901889B (en) * | 2019-12-04 | 2023-04-11 | 中国直升机设计研究所 | Variant aircraft |
| CN111746783B (en) * | 2020-07-01 | 2022-07-01 | 西湖大学 | A flank structure and navigation ware for navigation ware |
| CN112173065A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Be applied to wing of wing aircraft that verts |
| CN112722237B (en) * | 2021-02-20 | 2023-08-25 | 江西经济管理干部学院 | Aviation aircraft wing tip winglet |
| CN112977879A (en) * | 2021-04-01 | 2021-06-18 | 中国航天空气动力技术研究院 | Aeroelastic test platform |
| US20220332406A1 (en) * | 2021-04-15 | 2022-10-20 | Northeastern University | Variable Morphing Wing Using Surface Actuated Origami Folds |
| CN113291457B (en) * | 2021-05-19 | 2023-09-05 | 中航西安飞机工业集团股份有限公司 | Aircraft nose fairing structure and aircraft attitude control method |
| CN114590395A (en) * | 2022-03-11 | 2022-06-07 | 中国人民解放军军事科学院国防科技创新研究院 | Flexible telescopic extension mechanism of folding wing |
| CN114889804B (en) * | 2022-04-19 | 2023-03-24 | 清华大学 | Variant flying-wing aircraft |
| CN115009507A (en) * | 2022-04-19 | 2022-09-06 | 清华大学 | Multi-connecting-rod type single-wing double-wing variant aircraft |
| CN116101475B (en) * | 2022-09-07 | 2023-08-25 | 清华大学 | Wide-speed-domain variant double-wing structure and wide-speed-domain aircraft |
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| GB0002992D0 (en) * | 2000-02-10 | 2000-03-29 | Zee Franklin | Remote control vehicle |
| CN201604793U (en) * | 2009-11-17 | 2010-10-13 | 西安飞亚航空科技有限责任公司 | Lifting area-variable fixed wing unmanned aerocraft |
| US8844879B2 (en) * | 2011-12-12 | 2014-09-30 | The Boeing Company | Wing variable camber trailing edge tip |
| CN103129735B (en) * | 2013-03-08 | 2015-09-16 | 北京航空航天大学 | Three sections of twofold wings |
| CN104843186B (en) * | 2015-05-14 | 2017-03-01 | 许允夫 | A kind of drive mechanism of the wing of flapping-wing aircraft |
| CN206273678U (en) * | 2016-10-31 | 2017-06-23 | 南昌航空大学 | The unmanned plane that a kind of variable empennage is controlled with folded wing |
| CN108502183A (en) * | 2017-02-25 | 2018-09-07 | 原熙 | Folding wings helicopter |
| CN107054645B (en) * | 2017-04-01 | 2019-04-09 | 西安交通大学 | A kind of assistant deforms bionical unmanned vehicle and deformation control method |
| CN109592004A (en) * | 2017-09-30 | 2019-04-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of wing motion aerofoil |
| CN109250105A (en) * | 2018-09-25 | 2019-01-22 | 成都飞机工业（集团）有限责任公司 | A kind of variable configuration supersonic speed flying wing layout plane and its flying method |
| CN109703741B (en) * | 2019-01-28 | 2020-10-20 | 中国人民解放军国防科技大学 | Folding morphing wing and aircraft based on Sarrus structure drive |
| CN110901889B (en) * | 2019-12-04 | 2023-04-11 | 中国直升机设计研究所 | Variant aircraft |
-
2019
- 2019-12-04 CN CN201911228905.3A patent/CN110901889B/en active Active
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2020
- 2020-08-24 WO PCT/CN2020/000188 patent/WO2021109312A1/en active Application Filing
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| Publication number | Publication date |
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| CN110901889A (en) | 2020-03-24 |
| WO2021109312A1 (en) | 2021-06-10 |
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