CN203666966U - Canard wing configuration aircraft provided with movable strakes - Google Patents
Canard wing configuration aircraft provided with movable strakes Download PDFInfo
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- CN203666966U CN203666966U CN201320212543.0U CN201320212543U CN203666966U CN 203666966 U CN203666966 U CN 203666966U CN 201320212543 U CN201320212543 U CN 201320212543U CN 203666966 U CN203666966 U CN 203666966U
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Abstract
The utility model belongs to the technical field of an aerodynamics configuration design of an aircraft, and particularly relates to a canard wing configuration aircraft provided with movable strakes. Aiming at the features of high lift-drag ratio of wing configuration, low trim lift coefficient, poor maneuverability and the like, the canard wing configuration aircraft provided with the movable strakes is subjected to aircraft body shape correction on the basis of the wing configuration, distance control canards are additionally mounted at the front ends of the aircraft body, and a larger trim lift coefficient and good maneuverability are obtained with tiny lift-drag ratio loss; and the integrated movable strakes are mounted on the inner sides of leading edges of wings, vortex lift force under different flying attitudes can be obtained by adjusting anhedral angles of the strakes, and lift and lift-drag characteristics are further improved; and the aircraft adopts a stealth design principle simultaneously and is suitable for a high-altitude and long-endurance aircraft and an unmanned combat air vehicle, the cruise altitude of the aircraft can be increased remarkably, the cruise time of the aircraft can be prolonged remarkably, and the take-off and landing performance and maneuverability of the aircraft can be improved remarkably.
Description
Technical field
This patent belongs to aircraft aerodynamic arrangement design field, particularly relates to a kind of canard Flying-wing aircraft with movable edge strip.
Background technology
The conventional layout of aircraft mainly contains normal arrangement, canard configuration, Flying-wing etc.
Normal arrangement comprises wing, horizontal tail, vertical fin etc., wing is front, empennage is rear, such aircraft technology maturation, application at most, but shortcoming while being trim horizontal tail produce negative lift, increased trim resistance and aircraft weight, more aerofoil has also reduced 1ift-drag ratio and Stealth Fighter, and the Typical Representative of such layout has F-15, Su-27 and Boeing series, AirBus series airline carriers of passengers, " global hawk " Altitude Long Endurance Unmanned Air Vehicle etc.
Canard configuration cancels horizontal tail, adopt preposition canard, in the time of trim, canard can produce positive lift force, improve takeoff and landing performance and the handling of aircraft, canard is divided into again long distance control canard and close coupled canard, long distance control canard does not produce vortex lift, but make full use of the long characteristic of the arm of force and carry out trim and manipulation, Typical Representative is as Europe " typhoon " fighter plane, close coupled canard can produce vortex lift, improve airplane ascensional force characteristic and At High Angle of Attack maneuvering performance, Typical Representative has the J-10 fighter plane of French Rafale combat aircraft and China etc.
Flying-wing has cancelled horizontal tail and vertical fin, can effectively reduce by zero resistance of aircraft, improve the 1ift-drag ratio of aircraft, but Flying-wing is owing to lacking trim aerofoil, for improving trim performance, generally adopt the recurvation aerofoil profile of little lift coefficient, the lift coefficient of such aerofoil profile only has 0.2-0.4 left and right, be difficult to reach the flying height as " global hawk ", picture only has 11000m with the ceiling altitude of Lockheed Corp.'s " faint star " all-wing aircraft unmanned plane of " global hawk " competition, equally, famous Nuo Siluopu. the B-2 of Grumman Co., Ltd stealth bomber operating altitude only has 9000-12000m, greatly differ from each other with the 18000-20000m in high-altitude.In addition, trim configuration also can reduce 3-5 1ift-drag ratio than clean configuration, causes landing apart from strengthening, handling the problems such as difficulty, can only adopt advanced complicated control system to handle control.But the Stealth of Flying-wing is better, can improve battlefield survival, therefore generally for up-to-date Unmanned combat aircraft, as the X-45 of the U.S., X-47, " neuron ", " Thunder God " of Britain etc. of France.
How, in ensureing the high lift-drag ratio of all-wing aircraft, good Stealth Fighter, improve lift coefficient, improve handling, be applied to HAE class aircraft or high motor-driven Unmanned combat aircraft, have important engineering using value.
Summary of the invention
The object of the invention is:
This patent has proposed a kind of canard Flying-wing aircraft with movable edge strip, can effectively improve lift coefficient and the handling of Flying-wing, make the lift coefficient of conventional all-wing aircraft bring up to 0.80～1.20 by original 0.20-0.40, trim 1ift-drag ratio improves 1～3, use height to bring up to 18000-20000m from 9000-11000m, takeoff and landing performance and maneuvering performance effectively improve, and the weight increasing is less, are applicable to HAE class aircraft and high motor-driven stealthy Unmanned combat aircraft.
Technical scheme of the present invention is:
See accompanying drawing 1, with the canard Flying-wing aircraft of movable edge strip, this aircraft comprises all-wing aircraft fuselage, long distance control canard, wing, integrated movable edge strip, wing flap in before wing, outer wing flap before wing, flaperon in after wing, external resistance yaw rudder after wing, winglet, body pitching control surface, nozzle, admission port, air inlet/engine cabin, noselanding gear well, main landing gear compartment, built-in load cabin, wherein, long distance control canard is arranged on the front end of all-wing aircraft fuselage, wing is arranged on the rear end of all-wing aircraft fuselage, integrated movable edge strip is positioned at the position that leading edge merges mutually inside all-wing aircraft fuselage and wing, be connected with all-wing aircraft fuselage by rotating shaft, and utilize the actuator of installing with all-wing aircraft fuselage side edge part position to drive, the luff cloth of left/right wing be equipped with before wing in after wing flap and wing in two control surface of wing flap, trailing edge be furnished with after wing in two control surface of external resistance yaw rudder after flaperon and wing, wing wing tip is provided with winglet, the rear portion of fuselage is furnished with two nozzles arranged side by side, and nozzle both sides are furnished with body pitching control surface, and the belly of fuselage is furnished with the air inlet/engine cabin of bilateral type, aircraft adopts tricycle landing gear, and noselanding gear well is arranged in the front end of belly center line, and left and right main landing gear compartment is arranged in the outside in air inlet/engine cabin, aircraft adopts built-in load cabin, is arranged in belly center line.
Advantage of the present invention is:
(1) adopt long distance control canard to improve trim and maneuvering characteristics
Conventional Flying-wing exists and handles difficulty, and the shortcoming that trim resistance is large adopts high lift aerofoil profile can produce again larger nose-down pitching moment, and the loss of trim 1ift-drag ratio is larger.This patent has adopted long distance control canard design, at all-wing aircraft body front end, longitudinal control canard is installed, and has formed a kind of canard Flying-wing, can significantly improve trim 1ift-drag ratio, improves landing and the maneuvering performance of aircraft.
(2) adopt the design of high lift laminar flow wing to improve lift coefficient
The body of this patent is the all-wing aircraft fuselage of correction of the flank shape, itself has lift efficiency and interference drag is very little; Owing to can utilizing long distance control canard to carry out trim, without as all-wing aircraft for ensureing that trim adopts the recurvation aerofoil profile of low lift-to-drag ratios, and can adopt the laminar flow wing of high coefficient of lift combined, therefore can obtain higher lift coefficient and effectively reduce friction drag; At wing tip, winglet is installed, can reduces induced drag, obtain higher 1ift-drag ratio simultaneously.
(3) adopt integrated movable edge strip to increase vortex lift
This patent is at leading edge of a wing root, arrange a pair of integrated movable edge strip, edge strip can induce a series of edge strip whirlpool by adjusting dihedral angle degree under different state of flights, produce additional vortex lift, and control the burbling on main wing, reduce load and the area of wing, alleviate the structural weight of aircraft.
(4) adopt distributed multi-control to obtain good controller characteristic curve
This patent has been arranged a series of control surface at front and rear edge, the After-Body of main wing, match with the long distance control canard of aircraft, integrated movable edge strip, jointly can make aircraft under various flying conditions, all have best trim lifting resistance characteristic for the flight control of aircraft, and can realize excellent trim response with less trim moment and trim drift angle.
By the method for this patent, can obtain the aircraft aerodynamic arrangement with high lift, high lift-drag ratio and good operation performance.
Brief description of the drawings
Accompanying drawing 1 is the canard Flying-wing schematic diagram with movable edge strip, and wherein, Fig. 1 (a) is birds-eye view, and Fig. 1 (b) is upward view;
Accompanying drawing 2 is all-wing aircraft fuselage schematic diagram, and wherein, Fig. 2 (a) is all-wing aircraft fuselage front elevation, and Fig. 2 (b) is all-wing aircraft fuselage lateral plan, and Fig. 2 (c) is all-wing aircraft fuselage birds-eye view, and Fig. 2 (d) is all-wing aircraft fuselage backplan.
Accompanying drawing 3 is the canard all-wing aircraft Altitude Long Endurance Unmanned Air Vehicle of embodiment mono-, and Fig. 3 (a) is the front elevation of embodiment mono-, and Fig. 3 (b) is the birds-eye view of embodiment mono-, and Fig. 3 (c) is the lateral plan of embodiment mono-.
Accompanying drawing 4 is the canard all-wing aircraft Unmanned combat aircraft of embodiment bis-, and Fig. 4 (a) is the front elevation of embodiment bis-, and Fig. 4 (b) is the birds-eye view of embodiment bis-, and Fig. 4 (c) is the lateral plan of embodiment bis-.
Each component names:
1-all-wing aircraft fuselage, 2-long distance control canard, 3-wing, the integrated movable edge strip of 4-, interior wing flap before 5-wing, outer wing flap before 6-wing, flaperon in after 7-wing, external resistance yaw rudder after 8-wing, 9-winglet, 10-body pitching control surface, 11-nozzle, 12-admission port, 13-air inlet/engine cabin, 14-noselanding gear well, 15-main landing gear compartment, the built-in load of 16-cabin.
Detailed description of the invention
The implementation step of this patent is as follows:
(1) all-wing aircraft body correction of the flank shape
Traditional Flying-wing is carried out to body correction of the flank shape, see accompanying drawing 2, fuselage sections extends forward, ensure that its curved surface is smooth, obtain correction of the flank shape all-wing aircraft fuselage [1], original little lift recurvation aerofoil profile (as S5010) is revised as to high lift laminar f1ow airfoil profile (as NLF1015), obtain high lift laminar flow wing [3], now favourable lift coefficient is brought up to 0.80-1.20 by original 0.20-0.40, but nose-down pitching moment increases to some extent;
(2) design and installation long distance control canard
According to nose-down pitching moment size, match suitable control canard size and installation site, obtain long distance control canard [2], its leading edge and the homonymy leading edge of a wing, trailing edge and homonymy trailing edge are all parallel to each other, axle drive shaft connects long distance control canard [2] and fuselage [1] in the horizontal, canard deflection angle-30 °～+ 30 ° (under trailing edge partially for just), utilize hydraulic pressure or the driving of electric liquid actuator;
(3) the integrated movable edge strip of design and installation
In wing [3] inner side, leading edge merges part mutually with all-wing aircraft fuselage [1], integrated movable edge strip [4] is installed, the leading edge laminating of the trailing edge of edge strip [4] and wing [3], fit and utilize rotating shaft to be connected with fuselage with all-wing aircraft fuselage [1] outer rim in the inner side of edge strip [4], actuator is arranged on the outer rim position of all-wing aircraft fuselage and can drives edge strip [4] to do counter deflexion, 0 °～+ 15 ° of deflection angles;
(4) design distributes wing body control surface
According to takeoff and landing, cruise, lift-rising, trim and manipulation request under the various flight condition such as motor-driven, design and configure the control surface of wing, external resistance yaw rudder [8] and body pitching control surface [10] after interior flaperon [7], wing after outer wing flap [6], wing before wing flap [5], wing in comprising before wing, wherein, after wing, external resistance yaw rudder is upper and lower two-piece type, serve as in the same way flaperon when deflection when upper and lower two, realize pitching or rolling control, in the time separating deflection for upper and lower two, serve as resistance rudder, realize driftage and control; Body pitching control surface [10] mainly coordinates long distance control canard [2] further to strengthen longitudinal trim ability and motor-driven control ability;
(5) carry out aircraft-Engine Matching Design and installation
Arrange driving engine in belly both sides, the correction of the flank shape optimization of selecting the driving engine of suitable types to go forward side by side to advance air flue/machinery space [13] according to the performance requriements of aircraft.
It needs to be noted, the driving engine of this patent can be arranged in back equally, adopts back-positioned type inlet channel to improve the Stealth Fighter of aircraft, or adopts single-shot to arrange, concrete mode need to be determined according to the specific requirement of aircraft.
(6) design optimization housing construction, freight space and fuel tank
On above-mentioned body profile basis, want condition for peace according to aerodynamic force calculating, test, load distribution, organism life-span etc., carry out design and the optimization of housing construction, freight space, fuel tank etc.
(7) system and load are arranged, complete full machine design and test
On the bases such as above-mentioned profile, structure, freight space, control surface layout, carry out the Design and optimization of each subsystems such as power system, fuel oil system, flight control system, electric power system, comprehensive and facility location, complete further full machine comprehensive Design and test.
Below by specific embodiment, also the present invention is described in further detail by reference to the accompanying drawings.
Embodiment mono-:
The embodiment mono-of this patent is the large-scale unmanned plane of a kind of HAE, sees accompanying drawing 3.
The step of the present embodiment is as follows:
The first step: according to operational need, determine Performance Parameters.As follows:
Capacity weight: 1800kg cruising speed: Ma0.6-0.8
Standby time: >48h standby height: 18000m-25000m
Second step: design optimization all-wing aircraft body and wing parameter.
According to weight, cruise, the requirement such as standby, the lift coefficient of determining aircraft is 0.80-1.20, the 1ift-drag ratio that cruises is 25, standby 1ift-drag ratio is 30, utilize weight computing formula further to determine take-off weight 27.5t, fuel weight 15.0t, utilizes the wing to carry computing formula and Aerodynamic Analysis and test, determines body geometric parameter: exposed wing area 62.56m
2, wing span 39.62m, body lifting surface area 157.15m
2, body length 23.50m, body height 2.62m.
The 3rd step: design optimization canard parameter.
According to landing, trim and manipulation request, determine canard span 9.00m, canard leading edge is apart from leading edge of a wing 13.10m, canard area 7.06m
2(exposed parts), deflection angle-30 °～+ 30 °.
The 4th step: design optimization edge strip parameter.
According to Aerodynamic Analysis and test, determine edge strip span 18.88m, edge strip area 7.10m
2, 0 °-12 ° of upper counter deflexion angles.
The 5th step: design optimization control surface parameter.
According to lift-rising, trim and manipulation request, determine before wing in position and the parameter of external resistance yaw rudder and body pitching control surface after interior flaperon, wing after outer wing flap, wing before wing flap, wing.
The 6th step: design optimization housing construction, freight space and fuel tank
On above-mentioned body profile basis, want condition for peace according to aerodynamic force calculating, test, load distribution, organism life-span etc., carry out design and the optimization of housing construction, freight space, fuel tank etc.
The 7th step: the each subsystem of design optimization and load are arranged, complete full machine comprehensively and test
On the bases such as above-mentioned profile, structure, freight space, control surface layout, carry out Design and optimization and the facility location of each subsystems such as power system, fuel oil system, flight control system, electric power system, complete further full machine comprehensively and test.
Embodiment bis-:
The embodiment bis-of this patent is a kind of high motor-driven Unmanned combat aircraft, sees accompanying drawing 4.
The step of the present embodiment is as follows:
The first step: according to operational need, determine Performance Parameters.As follows:
Capacity weight: 3000kg combat radius: >1000km
Cruising speed: Ma1.4-2.0 cruising altitude: 12000m-18000m
Second step: design optimization all-wing aircraft body and wing parameter.
According to weight, cruise, the requirement such as standby, the lift coefficient of determining aircraft is 0.50-0.60, the Ma0.8 1ift-drag ratio that cruises is 12, the Ma1.6 1ift-drag ratio that cruises is 9, utilize weight computing formula further to determine take-off weight 16.8t, fuel weight 6.0t, utilizes the wing to carry computing formula and Aerodynamic Analysis and test, determines body geometric parameter: exposed wing area 31.28m
2, wing span 13.50m, body lifting surface area 78.56m
2, body length 11.75m, body height 1.31m.
The 3rd step: design optimization canard parameter.
According to landing, trim and manipulation request, determine canard span 4.50m, canard leading edge is apart from leading edge of a wing 6.55m, canard area 3.53m
2(exposed parts), deflection angle-30 °～+ 30 °.
The 4th step: design optimization edge strip parameter.
According to Aerodynamic Analysis and test, determine edge strip span 9.44m, edge strip area 3.55m
2, 0 °-12 ° of upper counter deflexion angles.
The 5th step: design optimization control surface parameter.
According to lift-rising, trim and manipulation request, determine before wing in position and the parameter of external resistance yaw rudder and body pitching control surface after interior flaperon, wing after outer wing flap, wing before wing flap, wing.
The 6th step: design optimization housing construction, freight space and fuel tank
On above-mentioned body profile basis, want condition for peace according to aerodynamic force calculating, test, load distribution, organism life-span etc., carry out design and the optimization of housing construction, freight space, fuel tank etc.
The 7th step: the each subsystem of design optimization and load are arranged, complete full machine comprehensively and test
On the bases such as above-mentioned profile, structure, freight space, control surface layout, carry out Design and optimization and the facility location of each subsystems such as power system, fuel oil system, flight control system, electric power system, complete further full machine comprehensively and test.
Claims (1)
1. the canard Flying-wing aircraft with movable edge strip, it is characterized in that, this aircraft comprises all-wing aircraft fuselage, long distance control canard, wing, integrated movable edge strip, wing flap in before wing, outer wing flap before wing, flaperon in after wing, external resistance yaw rudder after wing, winglet, body pitching control surface, nozzle, admission port, air inlet/engine cabin, noselanding gear well, main landing gear compartment, built-in load cabin, wherein, long distance control canard is arranged on the front end of all-wing aircraft fuselage, wing is arranged on the rear end of all-wing aircraft fuselage, integrated movable edge strip is positioned at the position that leading edge merges mutually inside all-wing aircraft fuselage and wing, be connected with all-wing aircraft fuselage by rotating shaft, and utilize the actuator of installing with all-wing aircraft fuselage side edge part position to drive, the luff cloth of left/right wing be equipped with before wing in after wing flap and wing in two control surface of wing flap, trailing edge be furnished with after wing in two control surface of external resistance yaw rudder after flaperon and wing, wing wing tip is provided with winglet, the rear portion of fuselage is furnished with two nozzles arranged side by side, and nozzle both sides are furnished with body pitching control surface, and the belly of fuselage is furnished with the air inlet/engine cabin of bilateral type, aircraft adopts tricycle landing gear, and noselanding gear well is arranged in the front end of belly center line, and left and right main landing gear compartment is arranged in the outside in air inlet/engine cabin, aircraft adopts built-in load cabin, is arranged in belly center line.
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104494842A (en) * | 2014-11-19 | 2015-04-08 | 中国航空工业集团公司沈阳飞机设计研究所 | Rising wingtip design method |
| CN104554739A (en) * | 2014-12-16 | 2015-04-29 | 空气动力学国家重点实验室 | Air inlet lip for improving and adjusting course stability of double-engine wing-body blending tailless configuration |
| 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 |
| CN108974361A (en) * | 2017-06-01 | 2018-12-11 | 北京猎鹰无人机科技有限公司 | Canard and the hybrid layout unmanned plane of all-wing aircraft |
| CN109720535A (en) * | 2017-10-30 | 2019-05-07 | 成都飞机工业（集团）有限责任公司 | A kind of blended wing-body aircraft |
| CN109808871A (en) * | 2018-11-22 | 2019-05-28 | 成都飞机工业（集团）有限责任公司 | A kind of all-wing aircraft combination rudder face with high maneuvering characteristics |
| CN110203372A (en) * | 2019-06-28 | 2019-09-06 | 南京航空航天大学 | A kind of variant invisbile plane and its changing method and application |
| CN110316400A (en) * | 2019-07-22 | 2019-10-11 | 南京航空航天大学 | A kind of canard layout fixed-wing unmanned plane direct lift force control method |
| CN110431076A (en) * | 2017-01-19 | 2019-11-08 | 比勒陀利亚大学 | Tailless aircraft |
| 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 |
| CN111976946A (en) * | 2020-09-02 | 2020-11-24 | 南昌航空大学 | Pneumatic layout of combat bomber with segmented regula |
| CN112455699A (en) * | 2020-11-13 | 2021-03-09 | 中国航空工业集团公司沈阳飞机设计研究所 | High fusion aircraft afterbody |
| CN113562160A (en) * | 2021-08-07 | 2021-10-29 | 中国航空工业集团公司沈阳飞机设计研究所 | Front wing application method for improving pitching moment characteristic of airplane |
| CN115930694A (en) * | 2022-11-15 | 2023-04-07 | 北京宇航系统工程研究所 | Two-stage reusable carrier |
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- 2013-04-24 CN CN201320212543.0U patent/CN203666966U/en not_active Expired - Lifetime
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104494842A (en) * | 2014-11-19 | 2015-04-08 | 中国航空工业集团公司沈阳飞机设计研究所 | Rising wingtip design method |
| CN104554739A (en) * | 2014-12-16 | 2015-04-29 | 空气动力学国家重点实验室 | Air inlet lip for improving and adjusting course stability of double-engine wing-body blending tailless configuration |
| CN110431076A (en) * | 2017-01-19 | 2019-11-08 | 比勒陀利亚大学 | Tailless aircraft |
| US11554849B2 (en) | 2017-01-19 | 2023-01-17 | University Of Pretoria | Tailless aircraft |
| CN108974361A (en) * | 2017-06-01 | 2018-12-11 | 北京猎鹰无人机科技有限公司 | Canard and the hybrid layout unmanned plane of all-wing aircraft |
| CN109720535A (en) * | 2017-10-30 | 2019-05-07 | 成都飞机工业（集团）有限责任公司 | A kind of blended wing-body aircraft |
| CN108639339B (en) * | 2018-03-30 | 2023-11-14 | 彩虹无人机科技有限公司 | Pneumatic layout of unmanned aerial vehicle |
| 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 |
| CN109808871A (en) * | 2018-11-22 | 2019-05-28 | 成都飞机工业（集团）有限责任公司 | A kind of all-wing aircraft combination rudder face with high maneuvering characteristics |
| CN110203372A (en) * | 2019-06-28 | 2019-09-06 | 南京航空航天大学 | A kind of variant invisbile plane and its changing method and application |
| CN110316400A (en) * | 2019-07-22 | 2019-10-11 | 南京航空航天大学 | A kind of canard layout fixed-wing unmanned plane direct lift force control method |
| CN110316400B (en) * | 2019-07-22 | 2022-04-15 | 南京航空航天大学 | Direct lift control method for fixed-wing unmanned aerial vehicle with canard wing layout |
| 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 |
| CN111976946A (en) * | 2020-09-02 | 2020-11-24 | 南昌航空大学 | Pneumatic layout of combat bomber with segmented regula |
| CN112455699A (en) * | 2020-11-13 | 2021-03-09 | 中国航空工业集团公司沈阳飞机设计研究所 | High fusion aircraft afterbody |
| CN112455699B (en) * | 2020-11-13 | 2024-01-02 | 中国航空工业集团公司沈阳飞机设计研究所 | High-fusion aircraft rear body |
| CN113562160A (en) * | 2021-08-07 | 2021-10-29 | 中国航空工业集团公司沈阳飞机设计研究所 | Front wing application method for improving pitching moment characteristic of airplane |
| CN113562160B (en) * | 2021-08-07 | 2024-01-02 | 中国航空工业集团公司沈阳飞机设计研究所 | Front wing application method for improving pitching moment characteristics of airplane |
| CN115930694A (en) * | 2022-11-15 | 2023-04-07 | 北京宇航系统工程研究所 | Two-stage reusable carrier |
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Address after: 610091 planning and Development Department of Chengdu aircraft design and Research Institute, 1610 Riyue Avenue, Qingyang District, Chengdu City, Sichuan Province Patentee after: AVIC CHENGDU AIRCRAFT DESIGN & Research Institute Address before: 610091 planning and Development Department of Chengdu aircraft design and Research Institute, 1610 Riyue Avenue, Qingyang District, Chengdu City, Sichuan Province Patentee before: AVIC CHENGDU AIRCRAFT DESIGN & Research Institute |
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Granted publication date: 20140625 |