CN109808871A - A kind of all-wing aircraft combination rudder face with high maneuvering characteristics - Google Patents
A kind of all-wing aircraft combination rudder face with high maneuvering characteristics Download PDFInfo
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- CN109808871A CN109808871A CN201811394796.8A CN201811394796A CN109808871A CN 109808871 A CN109808871 A CN 109808871A CN 201811394796 A CN201811394796 A CN 201811394796A CN 109808871 A CN109808871 A CN 109808871A
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Abstract
This application discloses a kind of, and the all-wing aircraft with high maneuvering characteristics combines rudder face, including fuselage, the fuselage includes head, wing and tail, the wing is two, and it is symmetricly set on the two sides of fuselage, the two sides of the head are provided with strake wing, the strake wing passes through shaft and the dynamic connection of head axis, the upper end of the wing is provided with droope snoot, side is provided with rudder face, lower end is provided with elevon, the droope snoot, rudder face and elevon pass through shaft and the dynamic connection of wing axis, jet vane is provided on the tail, the jet vane passes through shaft and the dynamic connection of tail axis.By the control combination of reasonable Arrangement rudder face and rudder face, requirement of the high maneuvering flight of all-wing aircraft to pitching moment and the conventional needs for equalling low-resistance when flying are taken into account, is easily achieved high maneuvering flight in engineering.
Description
Technical field
The application belongs to field of flight vehicle design, and in particular to a kind of all-wing aircraft combination rudder face with high maneuvering characteristics.
Background technique
All-wing aircraft is mainly characterized by no empennage, and main wing constitutes entire body (wingflying aircraft) plus fuselage, in the world the~
What airplane used is exactly this form.The U.S. and Germany almost start simultaneously at research wingflying aircraft, and Germany researches and develops and produces suddenly
Pause H0229 (World War II of testing machine production phase terminates).
Patent No. CN201520968560.6, applying date 2015-11-30 disclose a kind of four axis all-wing aircraft of combined type
Aircraft, it is characterised in that: including newel fuselage, two wings of left and right settings are symmetrically arranged on the newel fuselage,
All-wing aircraft assembly I is equipped at the rib of described two wings, the all-wing aircraft assembly I is mounted on wing by wing mount brackets；Institute
Former and later two vertical fins being additionally provided on newel fuselage with wing vertical setting are stated, are equipped on the vertical fin by support rod winged
Wing assembly II, the center of the all-wing aircraft assembly II to newel fuselage is away from the center with all-wing aircraft assembly I to newel fuselage away from phase
Together, and all-wing aircraft assembly II and all-wing aircraft assembly I are in same level.
Above-mentioned patent passes through the structure changes offline mode that mixes with all-wing aircraft of four axis, and it is big to compensate for four-axle aircraft power consumption,
The low disadvantage of flying speed realizes VTOL and turns flat winged.But Flying-wing's aircraft does not have empennage, controls the rudder of pitching
The face arm of force is short, and rudder effectiveness is low, and when carrying out high maneuvering flight, the rudder face for controlling pitching, which is difficult to effectively to provide enough torque, to exist
Change of flight device posture in short time, or even will cause the lift that excessive negative lift offsets full machine, therefore Flying-wing flies
Device is difficult to realize high maneuvering flight.
Summary of the invention
To solve the above-mentioned problems, the application provides a kind of all-wing aircraft combination rudder face with high maneuvering characteristics, by each
The collaboration of rudder face provides the pitching moment and lift-rising that can quickly change posture for Flying-wing's aircraft.
The application is achieved through the following technical solutions.
A kind of all-wing aircraft combination rudder face with high maneuvering characteristics, including fuselage, it is characterised in that: the fuselage includes machine
Head, wing and tail, the wing is two, and is symmetricly set on the two sides of fuselage, and the two sides of the head are provided with edge strip
The wing, the strake wing are provided with droope snoot by shaft and the dynamic connection of head axis, the upper end of the wing, and side is provided with rudder
Face, lower end are provided with elevon, and the droope snoot, rudder face and elevon are described by shaft and the dynamic connection of wing axis
Jet vane is provided on tail, the jet vane passes through shaft and the dynamic connection of tail axis.
The strake wing, droope snoot, elevon and jet vane along body upper rotation angle be a, a be 15~
20 °, the rudder face is fixed with standard of fuselage level.
The strake wing, rudder face and elevon are a along body upper rotation angle, and a is 15~20 °, before described
Edge wing flap and jet vane are fixed with standard of fuselage.
The elevon and jet vane are b along body upper rotation angle, and the b is 5~10 °, the strake wing,
Droope snoot and rudder face are fixed with standard of fuselage.
The droope snoot and rudder face are b along body upper rotation angle, and the b is 5~10 °, the strake wing, preceding
Edge wing flap and jet vane are fixed with standard of fuselage.
The strake wing, droope snoot, elevon and jet vane are c along body upper rotation angle, and the c is 2
~5 °, the rudder face is fixed with standard of fuselage.
The application bring beneficial effect has.
1, corresponding rotation is occurred relative to fuselage by strake wing, droope snoot, rudder face, elevon and jet vane,
It can be cooperateed with fuselage around the controlled deflection of shaft of fuselage and provide biggish pitching moment for all-wing aircraft, realized that the height of all-wing aircraft is motor-driven and fly
Row, under the premise of not changing Flying-wing, by the control combination of reasonable Arrangement rudder face and rudder face, it is motor-driven to take into account all-wing aircraft height
Requirement and the conventional needs for equalling low-resistance when flying to fly to pitching moment, are easily achieved high maneuvering flight in engineering.
2, the shaft by strake wing, droope snoot, elevon and jet vane around fuselage rotates 15~20 °, is flying
The wing carries out providing pitch control torque when high maneuvering flight, and all-wing aircraft is made to can be realized high motor-driven pitch attitude.
3, the shaft by a wing, rudder face and elevon around fuselage rotates 15~20 °, carries out in all-wing aircraft high motor-driven winged
The available angle-of-attack range for increasing aircraft when row makes all-wing aircraft can be realized high motor-driven roll mode.
4,5~10 ° being rotated by the shaft that elevon and jet vane surround fuselage, rudder face is arranged in wing wingtip,
It is cooperateed with when all-wing aircraft does small maneuvering flight with elevon and provides Heading control torque for all-wing aircraft, can be realized all-wing aircraft small motor-driven
Pitch attitude.
5,5~10 °, after elevon is arranged in wing are rotated along the shaft around fuselage by droope snoot and rudder face
Edge can stand alone as all-wing aircraft when all-wing aircraft does small maneuvering flight and provide rolling control moment or cooperate with rudder face 3 and provide boat for all-wing aircraft
To control moment, all-wing aircraft is made to can be realized small motor-driven roll mode.
6,2~5 ° are rotated along the shaft around fuselage by strake wing, droope snoot, elevon and jet vane, combustion
After gas rudder is arranged in nozzle, pitch control torque is provided for all-wing aircraft when all-wing aircraft carries out high maneuvering flight, keeps all-wing aircraft real
Now steady Heading control state.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the application.
Angle schematic diagram when Fig. 2 is the high motor-driven pitching of all-wing aircraft and high motor-driven rolling.
Angle schematic diagram when Fig. 3 is the small motor-driven pitching of all-wing aircraft and small motor-driven rolling.
Angle schematic diagram when Fig. 4 is all-wing aircraft Heading control.
Appended drawing reference: 1, fuselage, 2, strake wing, 3, droope snoot, 4, rudder face, 5, elevon, 6, jet vane, 7, machine
Head, 8, wing, 9, tail, 10, shaft.
Specific embodiment
Embodiment 1
As shown in Figure 1, a kind of all-wing aircraft with high maneuvering characteristics combines rudder face, including fuselage 1, the fuselage 1 include head 7,
Wing 8 and tail 9, the wing 8 is two, and is symmetricly set on the two sides of fuselage 1, and the two sides of the head 7 are provided with side
The wing 2, for the strake wing 2 by shaft 10 and the dynamic connection of 7 axis of head, the upper end of the wing 8 is provided with droope snoot 3, side
End is provided with rudder face 4, and lower end is provided with elevon 5, the droope snoot 3, rudder face 4 and elevon 5 by shaft 10 with
8 axis of wing is dynamic to be connected, and jet vane 6 is provided on the tail 9, and the jet vane 6 passes through shaft 10 and the dynamic connection of 9 axis of tail.
Fit all-wing aircraft length is 20m, is highly 3.5m, span 18m, and the wing 8 of 1 plane of symmetry of fuselage is GOE 693, machine
Thriving root, wing wingtip, winglet aerofoil profile be GOE 622, the distance of wing 8 wing root plane to the fuselage plane of symmetry is
2.5m, the distance of wing wingtip plane to the fuselage plane of symmetry are 7m, and the distance of winglet plane to the fuselage plane of symmetry is 10m,
Corresponding rotation occurs relative to fuselage by strake wing 2, droope snoot 3, rudder face 4, elevon 5 and jet vane 6, it can be around machine
The controlled deflection of shaft 10 of body 1, cooperates with fuselage 1 and provides biggish pitching moment for all-wing aircraft, realize the high maneuvering flight of all-wing aircraft,
Under the premise of not changing Flying-wing, by the control combination of reasonable Arrangement rudder face and rudder face, it is high motor-driven winged to take into account all-wing aircraft
Requirement and the conventional needs of equalling when flying low-resistance of the row to pitching moment, are easily achieved high maneuvering flight in engineering.
Embodiment 2
As shown in Figure 1, a kind of all-wing aircraft with high maneuvering characteristics combines rudder face, including fuselage 1, the fuselage 1 include head 7,
Wing 8 and tail 9, the wing 8 is two, and is symmetricly set on the two sides of fuselage 1, and the two sides of the head 7 are provided with side
The wing 2, for the strake wing 2 by shaft 10 and the dynamic connection of 7 axis of head, the upper end of the wing 8 is provided with droope snoot 3, side
End is provided with rudder face 4, and lower end is provided with elevon 5, the droope snoot 3, rudder face 4 and elevon 5 by shaft 10 with
8 axis of wing is dynamic to be connected, and jet vane 6 is provided on the tail 9, and the jet vane 6 passes through shaft 10 and the dynamic connection of 9 axis of tail.
As shown in Fig. 2, the strake wing 2, droope snoot 3, elevon 5 and jet vane 6 rotate angle above fuselage 1
It is 15~20 ° for a, a, the rudder face 4 is horizontal fixed with fuselage 1.
It is a that the strake wing 2, rudder face 4 and elevon 5 rotate angle above fuselage 1, and a is 15~20 °, institute
It is horizontal fixed with fuselage 1 to state droope snoot 3 and jet vane 6.
Fit all-wing aircraft length is 20m, is highly 3.5m, span 18m, and the wing 8 of 1 plane of symmetry of fuselage is GOE 693, machine
Thriving root, wing wingtip, winglet aerofoil profile be GOE 622, the distance of wing 8 wing root plane to the fuselage plane of symmetry is
2.5m, the distance of wing wingtip plane to the fuselage plane of symmetry are 7m, and the distance of winglet plane to the fuselage plane of symmetry is 10m,
Corresponding rotation occurs relative to fuselage by strake wing 2, droope snoot 3, rudder face 4, elevon 5 and jet vane 6, it can be around machine
The controlled deflection of shaft 10 of body 1, cooperates with fuselage 1 and provides biggish pitching moment for all-wing aircraft, realize the high maneuvering flight of all-wing aircraft,
Under the premise of not changing Flying-wing, by the control combination of reasonable Arrangement rudder face and rudder face, it is high motor-driven winged to take into account all-wing aircraft
Requirement and the conventional needs of equalling when flying low-resistance of the row to pitching moment, are easily achieved high maneuvering flight in engineering.
Shaft 10 by strake wing 1, rudder face 4 and elevon 5 around fuselage 1 rotates 15~20 °, carries out in all-wing aircraft high
The available angle-of-attack range for increasing aircraft when maneuvering flight makes all-wing aircraft can be realized high motor-driven roll mode.
5~10 ° are rotated around the shaft 10 of fuselage 1 by elevon 5 and jet vane 6, rudder face 4 is arranged in wing 8
Wingtip cooperates with elevon when all-wing aircraft does small maneuvering flight and provides Heading control torque for all-wing aircraft, can be realized all-wing aircraft
Small motor-driven pitch attitude.
Embodiment 3
As shown in Figure 1, a kind of all-wing aircraft with high maneuvering characteristics combines rudder face, including fuselage 1, the fuselage 1 include head 7,
Wing 8 and tail 9, the wing 8 is two, and is symmetricly set on the two sides of fuselage 1, and the two sides of the head 7 are provided with side
The wing 2, for the strake wing 2 by shaft 10 and the dynamic connection of 7 axis of head, the upper end of the wing 8 is provided with droope snoot 3, side
End is provided with rudder face 4, and lower end is provided with elevon 5, the droope snoot 3, rudder face 4 and elevon 5 by shaft 10 with
8 axis of wing is dynamic to be connected, and jet vane 6 is provided on the tail 9, and the jet vane 6 passes through shaft 10 and the dynamic connection of 9 axis of tail.
As shown in Fig. 2, the strake wing 2, droope snoot 3, elevon 5 and jet vane 6 rotate angle above fuselage 1
It is 15~20 ° for a, a, the rudder face 4 is horizontal fixed with fuselage 1.
It is a that the strake wing 2, rudder face 4 and elevon 5 rotate angle above fuselage 1, and a is 15~20 °, institute
It is horizontal fixed with fuselage 1 to state droope snoot 3 and jet vane 6.
As shown in figure 3, the elevon 5 and jet vane 6 rotated above fuselage 1 angle be b, the b be 5~
10 °, the strake wing 2, droope snoot 3 and rudder face 4 are horizontal fixed with fuselage 1.
It is b that the droope snoot 3 and rudder face 4 rotate angle above fuselage 1, and the b is 5~10 °, the strake wing
2, droope snoot 3 and jet vane 6 are horizontal fixed with fuselage 1.
As shown in figure 4, the strake wing 2, droope snoot 3, elevon 5 and jet vane 6 rotation angle above fuselage 1
Degree is c, and the c is 2~5 °, and the rudder face 4 is horizontal fixed with fuselage 1.
Fit all-wing aircraft length is 20m, is highly 3.5m, span 18m, and the wing 8 of 1 plane of symmetry of fuselage is GOE 693, machine
Thriving root, wing wingtip, winglet aerofoil profile be GOE 622, the distance of wing 8 wing root plane to the fuselage plane of symmetry is
2.5m, the distance of wing wingtip plane to the fuselage plane of symmetry are 7m, and the distance of winglet plane to the fuselage plane of symmetry is 10m,
Corresponding rotation occurs relative to fuselage by strake wing 2, droope snoot 3, rudder face 4, elevon 5 and jet vane 6, it can be around machine
The controlled deflection of shaft 10 of body 1, cooperates with fuselage 1 and provides biggish pitching moment for all-wing aircraft, realize the high maneuvering flight of all-wing aircraft,
Under the premise of not changing Flying-wing, by the control combination of reasonable Arrangement rudder face and rudder face, it is high motor-driven winged to take into account all-wing aircraft
Requirement and the conventional needs of equalling when flying low-resistance of the row to pitching moment, are easily achieved high maneuvering flight in engineering.
Shaft by strake wing 1, rudder face 4 and elevon 5 around fuselage 1 revolves 10 turns 15~20 °, carries out in all-wing aircraft high
The available angle-of-attack range for increasing aircraft when maneuvering flight makes all-wing aircraft can be realized high motor-driven roll mode.
5~10 ° are rotated around the shaft 10 of fuselage 1 by elevon 5 and jet vane 6, rudder face 4 is arranged in wing 8
Wingtip cooperates with elevon when all-wing aircraft does small maneuvering flight and provides Heading control torque for all-wing aircraft, can be realized all-wing aircraft
Small motor-driven pitch attitude.
5~10 ° are rotated by the shaft 10 that elevon and jet vane surround fuselage, rudder face is arranged in wing wingtip,
It is cooperateed with when all-wing aircraft does small maneuvering flight with elevon and provides Heading control torque for all-wing aircraft, can be realized all-wing aircraft small motor-driven
Pitch attitude.
5~10 ° are rotated along the shaft 10 around fuselage 1 by droope snoot 3 and rudder face 4, elevon 5 is arranged in machine
Wing rear, all-wing aircraft can be stood alone as when all-wing aircraft does small maneuvering flight provides rolling control moment or cooperate with rudder face 3 and mention for all-wing aircraft
For Heading control torque, all-wing aircraft is made to can be realized small motor-driven roll mode.
By strake wing 2, droope snoot 3, elevon 5 and jet vane 6 along the rotation of shaft 10 2 around fuselage 7~
5 °, after jet vane is arranged in nozzle, pitch control torque is provided for all-wing aircraft when all-wing aircraft carries out high maneuvering flight, enables all-wing aircraft
Enough realize steady Heading control state.
The specific embodiment of the application above described embodiment only expresses, the description thereof is more specific and detailed, but simultaneously
The limitation to the application protection scope therefore cannot be interpreted as.It should be pointed out that for those of ordinary skill in the art
For, under the premise of not departing from technical scheme design, various modifications and improvements can be made, these belong to this
The protection scope of application.
Claims (6)
1. a kind of all-wing aircraft with high maneuvering characteristics combines rudder face, including fuselage (1), it is characterised in that: the fuselage (1) includes
Head (7), wing (8) and tail (9), the wing (8) is two, and is symmetricly set on the two sides of fuselage (1), the head
(7) two sides are provided with strake wing (2), and the strake wing (2) passes through shaft (10) and the dynamic connection of head (7) axis, the wing
(8) upper end is provided with droope snoot (3), and side is provided with rudder face (4), and lower end is provided with elevon (5), the leading edge flap
The wing (3), rudder face (4) and elevon (5) are connected by the way that shaft shaft (10) and wing (8) axis are dynamic, are arranged on the tail (9)
Have jet vane (6), the jet vane (6) passes through shaft shaft (10) and the dynamic connection of tail (9) axis.
2. a kind of all-wing aircraft with high maneuvering characteristics as described in claim 1 combines rudder face, it is characterised in that: the strake wing
(2), droope snoot (3), elevon (5) and jet vane (6) the rotation angle above the fuselage (1) are a, a is 15~
20 °, the rudder face (4) and fuselage (1) are horizontal fixed.
3. a kind of all-wing aircraft with high maneuvering characteristics as described in claim 1 combines rudder face, it is characterised in that: the strake wing
(2), rudder face (4) and elevon (5) the rotation angle above fuselage (1) are a, and a is 15~20 °, the droope snoot
(3) and jet vane (6) is horizontal fixed with fuselage (1).
4. a kind of all-wing aircraft with high maneuvering characteristics as described in claim 1 combines rudder face, it is characterised in that: the lifting is secondary
The wing (5) and jet vane (6) the rotation angle above fuselage (1) are b, and the b is 5~10 °, the strake wing (2), the leading edge flap
The wing (3) and rudder face (4) are horizontal fixed with fuselage (1).
5. a kind of all-wing aircraft with high maneuvering characteristics as described in claim 1 combines rudder face, it is characterised in that: the leading edge flap
The wing (3) and rudder face (4) the rotation angle above fuselage (1) are b, and the b is 5~10 °, the strake wing (2), droope snoot
(3) and jet vane (6) is horizontal fixed with fuselage (1).
6. a kind of all-wing aircraft with high maneuvering characteristics as described in claim 1 combines rudder face, it is characterised in that: the strake wing
(2), droope snoot (3), elevon (5) and jet vane (6) the rotation angle above the fuselage (1) are c, the c is 2~
5 °, the rudder face (4) and fuselage (1) are horizontal fixed.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811394796.8A CN109808871A (en) | 2018-11-22 | 2018-11-22 | A kind of all-wing aircraft combination rudder face with high maneuvering characteristics |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811394796.8A CN109808871A (en) | 2018-11-22 | 2018-11-22 | A kind of all-wing aircraft combination rudder face with high maneuvering characteristics |
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| CN109808871A true CN109808871A (en) | 2019-05-28 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111152913A (en) * | 2020-02-28 | 2020-05-15 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Wing-body integrated airplane |
| CN112722241A (en) * | 2021-02-02 | 2021-04-30 | 中国空气动力研究与发展中心空天技术研究所 | Telescopic belly flap |
| CN115783241A (en) * | 2023-02-08 | 2023-03-14 | 中国空气动力研究与发展中心计算空气动力研究所 | Asynchronous deflection course control combined rudder control method of fusion body aircraft |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030197097A1 (en) * | 1997-08-26 | 2003-10-23 | Sean R. Wakayama | Reconfiguration control system for an aircraft wing |
| US20110095136A1 (en) * | 2009-10-27 | 2011-04-28 | Airbus Operations Gmbh | Aircraft with vertical stabilizers arranged on a central fuselage body and method, as well as control unit, for compensating a negative pitching moment |
| US20110121130A1 (en) * | 2009-11-21 | 2011-05-26 | Odle Richard C | Blended wing body cargo airplane |
| CN103010463A (en) * | 2012-12-26 | 2013-04-03 | 南京航空航天大学 | High-speed coaxial tilting double-rotor-wing flying wing machine |
| CN203666966U (en) * | 2013-04-24 | 2014-06-25 | 成都飞机设计研究所 | Canard wing configuration aircraft provided with movable strakes |
| CN103879556A (en) * | 2014-03-31 | 2014-06-25 | 冯加伟 | Wide flight envelop morphing aircraft |
| CN204399465U (en) * | 2015-01-14 | 2015-06-17 | 西北工业大学 | A kind of anury all-wing aircraft many controlsurfaces unmanned plane |
| CN205150230U (en) * | 2015-11-30 | 2016-04-13 | 保定维特瑞交通设施工程有限责任公司 | Modular four -axis all -wing aircraft aircraft |
| CN106184738A (en) * | 2016-06-17 | 2016-12-07 | 北京航空航天大学 | A kind of dismountable tailstock formula VUAV |
| US20180099735A1 (en) * | 2016-10-12 | 2018-04-12 | Airbus Operations Limited | Aircraft wing with aileron |
| CN108016617A (en) * | 2018-01-10 | 2018-05-11 | 苏州华鹏无人机科技有限公司 | A kind of stealthy unmanned plane of Flying-wing |
| CN108639339A (en) * | 2018-03-30 | 2018-10-12 | 彩虹无人机科技有限公司 | A kind of UAV aerodynamic layout |
-
2018
- 2018-11-22 CN CN201811394796.8A patent/CN109808871A/en active Pending
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030197097A1 (en) * | 1997-08-26 | 2003-10-23 | Sean R. Wakayama | Reconfiguration control system for an aircraft wing |
| US20110095136A1 (en) * | 2009-10-27 | 2011-04-28 | Airbus Operations Gmbh | Aircraft with vertical stabilizers arranged on a central fuselage body and method, as well as control unit, for compensating a negative pitching moment |
| US20110121130A1 (en) * | 2009-11-21 | 2011-05-26 | Odle Richard C | Blended wing body cargo airplane |
| CN103010463A (en) * | 2012-12-26 | 2013-04-03 | 南京航空航天大学 | High-speed coaxial tilting double-rotor-wing flying wing machine |
| CN203666966U (en) * | 2013-04-24 | 2014-06-25 | 成都飞机设计研究所 | Canard wing configuration aircraft provided with movable strakes |
| CN103879556A (en) * | 2014-03-31 | 2014-06-25 | 冯加伟 | Wide flight envelop morphing aircraft |
| CN204399465U (en) * | 2015-01-14 | 2015-06-17 | 西北工业大学 | A kind of anury all-wing aircraft many controlsurfaces unmanned plane |
| CN205150230U (en) * | 2015-11-30 | 2016-04-13 | 保定维特瑞交通设施工程有限责任公司 | Modular four -axis all -wing aircraft aircraft |
| CN106184738A (en) * | 2016-06-17 | 2016-12-07 | 北京航空航天大学 | A kind of dismountable tailstock formula VUAV |
| US20180099735A1 (en) * | 2016-10-12 | 2018-04-12 | Airbus Operations Limited | Aircraft wing with aileron |
| CN108016617A (en) * | 2018-01-10 | 2018-05-11 | 苏州华鹏无人机科技有限公司 | A kind of stealthy unmanned plane of Flying-wing |
| CN108639339A (en) * | 2018-03-30 | 2018-10-12 | 彩虹无人机科技有限公司 | A kind of UAV aerodynamic layout |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111152913A (en) * | 2020-02-28 | 2020-05-15 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Wing-body integrated airplane |
| CN112722241A (en) * | 2021-02-02 | 2021-04-30 | 中国空气动力研究与发展中心空天技术研究所 | Telescopic belly flap |
| CN112722241B (en) * | 2021-02-02 | 2024-04-12 | 中国空气动力研究与发展中心空天技术研究所 | Telescopic belly flap |
| CN115783241A (en) * | 2023-02-08 | 2023-03-14 | 中国空气动力研究与发展中心计算空气动力研究所 | Asynchronous deflection course control combined rudder control method of fusion body aircraft |
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Application publication date: 20190528 |
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