CN207450215U - A kind of change sweepforward twin-fuselage configuration aircraft - Google Patents
A kind of change sweepforward twin-fuselage configuration aircraft Download PDFInfo
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- CN207450215U CN207450215U CN201721208797.XU CN201721208797U CN207450215U CN 207450215 U CN207450215 U CN 207450215U CN 201721208797 U CN201721208797 U CN 201721208797U CN 207450215 U CN207450215 U CN 207450215U
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Abstract
The utility model provides a kind of change sweepforward twin-fuselage configuration aircraft, is related to a kind of multipurpose air fighting platform layout scheme.The utility model becomes sweepforward twin-fuselage configuration aircraft, it can be achieved that subsonic flight state is to the conversion of supersonic flight state, and becoming sweepforward twin-fuselage configuration aircraft includes：Anterior centrosome (1), two variable sweepback front wings (2), two fuselages (4), variable buzzard-type wing (6) and undercarriage.Becoming sweepforward twin-fuselage configuration aircraft can realize subsonic speed state to the mode conversion of supersonic speed state by becoming body mechanism, become sweepforward, the design of boxlike wing layout takes into account Asia/supersonic speed lift resistance ratio, and it can realize retrofocus amount more smaller than conventional airplane, supersonic speed state both sides fuselage is combined into one, increase slenderness ratio, longitudinal cross-section area distribution is gentle, twin fuselage and anterior centrosome fuselage arrangement, add the delivered payload capability of body, compatible kinetic energy and directional energy antipersonnel weapon.
Description
Technical field
The utility model is related to multipurpose air fighting platform layout scheme, more particularly to a kind of change sweepforward twin-fuselage configuration
Aircraft.
Background technology
Following air mission proposes multiple requesting to aircraft flight performance：Very-long-range long-range raid is cruised for a long time
Combat duty requirement aircraft meets the requirement of big voyage, long endurance, and aircraft should have higher subsonic speed lift resistance ratio；It intercepts and fights
Mission requirements aircraft meets the requirement of high-speed flight, and aircraft should have relatively low supersonic speed resistance；Normal arrangement stealthing design is
It can not ensure that aircraft has high viability in high threat environment, aircraft should design to meet self-defence with good fuselage volume
Weapon loads.
The design requirement of Asia/supersonic speed high lift-drag ratio is taken into account on a kind of placement scheme, while there is enough machines
Body volume, possible solution at present including：Become sweepback aircraft, such as B-1B aircrafts, by change the angle of sweep of wing come
Subsonic speed and supersonic speed lifting resistance characteristic requirement are taken into account, problem is that aircraft retrofocus amount will compared to immutable wing configurations aircraft
Greatly, it is affected to aircraft control and stability；Subsonic speed anury Flying-wing aircraft, such as B-2, X-47B, are set using blended wing-body
Meter has excellent subsonic speed lift resistance ratio and good fuselage loading features, but can not realize supersonic flight, can not meet and cut
Hit operational need；Hypersonic Aircraft, such as SR-71 realize that halting is fought and high viability, still using flying speed advantage
It can not carry out long-time subsonic speed cruise.
Utility model content
The utility model provides a kind of change sweepforward twin-fuselage configuration aircraft, and Asia/supersonic speed cannot be taken into account to solve aircraft
The problem of Flight Design requirement and no good fuselage loading features.
In order to achieve the above object, the embodiment of the utility model adopts the following technical scheme that：
It is a kind of to become sweepforward twin-fuselage configuration aircraft, it can be achieved that the mode of subsonic flight state to supersonic flight state turns
It changes, which is characterized in that the change sweepforward twin-fuselage configuration aircraft includes：
Anterior centrosome, in spheroid shape, the anterior centrosome is disposed longitudinally on body front end；
Two variable sweepback front wings are connected to the left and right sides of the anterior centrosome lower part, institute by becoming body mechanism
The trailing edge for stating variable sweepback front wing is disposed with preceding lifting wing flap, and the variable sweepback front wing is before the conduct of subsonic flight state
The wing, in supersonic flight state as body edge strip；
Two fuselages, described two fuselages are connected to the variable sweepback front wing of the left and right sides by becoming body mechanism respectively
End, zigzag lip air intake duct, the outside of described two afterbodies are respectively arranged at the back of described two fuselages
Dynamic flare vertical fin entirely is set respectively, and engine tail nozzle is set in the tail end of two fuselages, it is described in subsonic flight state
Two fuselages extend to separate, in supersonic flight state, described two fuselages extend to move toward one another realize fitting；
Variable buzzard-type wing, including left wing and right flank, the left wing is connected with right flank by becoming body mechanism, the left wing and
Right flank is connected respectively with the lower part of described two fuselages by becoming body mechanism, and the trailing edge ecto-entad of the left wing and right flank is successively
Be provided with aileron, flaperon and after lift wing flap；
Undercarriage, the undercarriage are distributed in first three point type, are separately positioned on the anterior centrosome and two fuselage lower ends.
Optionally, the change sweepforward twin-fuselage configuration aircraft realizes subsonic flight state to supersonic speed by becoming body mechanism
The mode conversion of state of flight, the change body mechanism include：
Driving mechanism, including four, described two fuselages of the left and right sides are connected respectively by two driving mechanisms
To the variable sweepback front wing of respective side and variable buzzard-type wing；
Follower, including precursor follower and rear body follower, the precursor follower is connected described in two
Variable sweepback front wing and the anterior centrosome, the rear body follower connect left wing and the right flank of the variable buzzard-type wing.
Optionally, the driving mechanism includes：
Fixed rotating shaft connects described two fuselage outer side longerons and the variable sweepback front wing back rest and difference respectively
Connect described two fuselage outer side longerons and the variable buzzard-type wing front-axle beam；
Arc gear wheel guide rail is arranged in corresponding fuselage between jack stringer；
Drive gear is arranged on the variable sweepback front wing front-axle beam and the variable buzzard-type wing back rest, by motor
The drive gear is driven to be moved on the arc gear wheel guide rail, drive the variable sweepback front wing and variable buzzard-type wing around
The fixed rotating shaft rotation.
Optionally, the precursor follower includes：
Two precursor fixed rotating shafts connect two variable sweepback front wing back rest and anterior centrosome described in respective side respectively
Longeron, during the variant of body, the variable sweepback front wing back rest is rotated around the precursor fixed rotating shaft；
Two front wing sliding fulcrums are respectively fixedly disposed on two variable sweepback front wings；
Two driven slides of precursor are separately positioned on two variable sweepback front wing front-axle beams and preceding center described in respective side
Body longeron junction, during the variant of body, two front wing sliding fulcrums of the variable sweepback front wing are described two
It is moved on the driven slide of precursor.
Optionally, the rear body follower includes：
Body fixed rotating shaft afterwards is arranged on the front-axle beam of the variable buzzard-type wing left wing and right flank junction, in body
During variant, the front-axle beam of the variable buzzard-type wing left wing and right flank is rotating around the rear body fixed rotating shaft rotation.
Optionally, the anterior centrosome is internally provided with loading space.
Optionally, the aspect ratio variable range of the variable sweepback front wing be 1-3,25 ° of leading edge sweep excursion-
70°；The aspect ratio variable range 1.7-9 of the variable buzzard-type wing, 25 ° -70 ° of leading edge sweepforward angle excursion.
Optionally, the preceding lifting wing flap and rear lifting wing flap are configured to only be operated under subsonic flight state.
Optionally, the entirely dynamic flare vertical fin cuts sharp layout using double sweepback.
The beneficial effects of the utility model：
The change sweepforward twin-fuselage configuration aircraft of the utility model, can by become body mechanism realize subsonic flight state to surpass
The mode conversion of velocity of sound state of flight improves aircraft Asia/supersonic speed lift resistance ratio using change sweepforward, boxlike wing layout designs, can
Realize retrofocus amount more smaller than conventional airplane, supersonic flight state both sides fuselage is combined into one, and increases slenderness ratio, longitudinal direction
Area of section distribution is gentle, effectively reduces supersonic speed zero and hinders coefficient, twin fuselage design the delivered payload capability for enhancing body.
Description of the drawings
Attached drawing herein is merged in specification and forms the part of this specification, shows and meets the utility model
Embodiment, and for explaining the principle of the utility model together with specification.
Fig. 1 is that the utility model becomes sweepforward twin-fuselage configuration aircraft subsonic speed state top view；
Fig. 2 is that the utility model becomes sweepforward twin-fuselage configuration aircraft subsonic speed state front view；
Fig. 3 is that the utility model becomes sweepforward twin-fuselage configuration aircraft subsonic speed side view of the state；
Fig. 4 is that the utility model becomes the isometric figure of sweepforward twin-fuselage configuration aircraft subsonic speed state；
Fig. 5 is that the utility model becomes sweepforward twin-fuselage configuration aircraft supersonic speed state top view；
Fig. 6 is that the utility model becomes sweepforward twin-fuselage configuration aircraft supersonic speed side view of the state；
Fig. 7 is that the utility model becomes the isometric figure of sweepforward twin-fuselage configuration aircraft supersonic speed state；
Fig. 8 is that the utility model becomes the sweepforward twin-fuselage configuration aircraft change main layout drawing of body mechanism；
Fig. 9 is that the utility model becomes sweepforward twin-fuselage configuration aircraft variant structural scheme of mechanism；
Figure 10 is that the utility model becomes sweepforward twin-fuselage configuration aircraft variant process schematic.
Wherein, 1- anterior centrosomes, 2- variable sweepback front wings lift wing flap, 4- fuselages, 5- zigzag lip air inlets before 3-
Road, the variable buzzard-type wings of 6-, 7- ailerons, 8- flaperons, 9- move flare vertical fin entirely, 10- engine tail nozzles, and the flap is lifted after 11-
The wing, 12- driving mechanisms, 13- precursor followers, body follower after 14-, 121- fixed rotating shafts, 122- arc gear wheel guide rails,
123- drive gears, 131- precursor fixed rotating shafts, the driven slide of 132- precursors, body fixed rotating shaft after 141-.
Specific embodiment
Here exemplary embodiment will be illustrated in detail, example is illustrated in the accompanying drawings.Following description is related to
During attached drawing, unless otherwise indicated, the same numbers in different attached drawings represent the same or similar element.
As shown in Figures 1 to 10, the utility model becomes sweepforward twin-fuselage configuration aircraft, it can be achieved that subsonic flight state arrives
The mode conversion of supersonic flight state, becoming sweepforward twin-fuselage configuration aircraft includes：Anterior centrosome 1, variable sweepback front wing 2, two
A fuselage 4, variable buzzard-type wing 6 and undercarriage.
Specifically, anterior centrosome 1 is in spheroid shape, is disposed longitudinally on body front end.In the present embodiment, preferably in anterior centrosome
1 inside sets loading space, becomes the loading space of body mechanism, airborne defensive weapon etc., anterior centrosome as nose-gear, front wing
1 can organically blend in supersonic flight state with twin fuselage, form succinct high speed placement.
Two variable sweepback front wings 2 are connected with the left and right sides of 1 lower part of anterior centrosome by precursor follower 13 respectively,
Lifting wing flap 3 before the trailing edge of variable sweepback front wing 2 is disposed with, wherein, preceding lifting wing flap 3 only makes in subsonic flight state
With；Variable sweepback front wing 2 is in subsonic flight state as front wing, and variant is afterwards in supersonic flight state as body side
Item.In the present embodiment, the aspect ratio of variable sweepback front wing 2 can in sweepforward twin-fuselage configuration flight status transfer process is become
Change scope is 1-3,25 ° -70 ° of leading edge sweep excursion.
Two fuselages 4 are symmetrically connected to the end of the variable sweepback front wing 2 of the left and right sides by driving mechanism 12 respectively,
Subsonic flight state, two fuselages 4 are extended to separating, and in supersonic flight state, two fuselages 4 are extended to moving toward one another
It realizes fitting, increases slenderness ratio, longitudinal cross-section area distribution is gentle, can effectively reduce supersonic speed zero and hinder coefficient；The present embodiment is excellent
Choosing is designed using symmetrical twin fuselage, can effectively disperse wing loads, it is possible to increase wing aspect ratio；Further, preferably in two machines
The back of body 4 offers the zigzag lip air intake duct 5 using BUMP formula compressing surfaces respectively, is more conducive to two fuselages as in body
The arrangement of weapon and undercarriage provides sufficient space；In addition, the outside of two 4 afterbodys of fuselage sets dynamic flare vertical fin 9 entirely respectively,
And it is equipped with engine tail nozzle 10 in the tail end of two fuselages 4；Wherein, a variety of design methods can be selected in dynamic flare vertical fin 9 entirely, this
In embodiment, dynamic flare vertical fin 9 preferably cuts sharp layout designs using double sweepback entirely, can be formed to the effective of engine tail nozzle 10
Block, at the same reduce can front and rear aerofoil flow interference to vertical fin, enhance handling.
Further, variable buzzard-type wing 6 includes left wing and right flank, and left wing is connected with right flank by rear body follower 14,
In addition left wing and right flank are connected respectively by driving mechanism 12 with the lower part of two fuselages 4, and the trailing edge of variable buzzard-type wing 6 is from outer
Aileron 7, flaperon 8 and rear lifting wing flap 11 have inwardly been sequentially arranged, wherein, the rear wing flap 11 that lifts is only in subsonic flight shape
State uses；In sweepforward twin-fuselage configuration flight status transfer process is become, the aspect ratio variable range of variable buzzard-type wing 6
1.7-9,25 ° -70 ° of leading edge sweepforward angle excursion.Become sweepforward twin-fuselage configuration aircraft in subsonic flight state have compared with
Small sweepforward angle and compared with high aspect ratio, has larger sweepforward angle and low aspect ratio in supersonic flight state.In addition, variable sweepforward
Wing 6 and variable sweepback front wing 2 form boxlike distribution form, reduce trim resistance.In the utility model, before change
Plunder, boxlike wing layout designs take into account Asia/supersonic speed lift resistance ratio, subsonic speed cruise lift resistance ratio reach 17, supersonic cruising lift resistance ratio
Reachable 6,10-11 subacoustic more than general fighter plane, supersonic 4-5；Become sweepforward, boxlike wing layout designs can be realized than normal
The smaller retrofocus amount of aircraft is advised, buzzard-type wing retrofocus amount is less than swept-back wing, the change sweepforward twin fuselage cloth of the utility model
Office's aircraft is 15% in supersonic flight state retrofocus, and in comparison, variable sweep aircraft F-111 retrofocus amounts reach
53%.
Further, undercarriage is distributed in first three point type, is separately positioned on the anterior centrosome 1 and two 4 lower ends of fuselage.
The change sweepforward twin-fuselage configuration aircraft of the utility model realizes subsonic flight state to ultrasound by becoming body mechanism
The mode conversion of fast state of flight, becoming body mechanism includes four driving mechanisms 12 and two followers.Four driving mechanisms 12
In, connect two fuselages 4 of the left and right sides and the variable sweepback front wing 2 of respective side respectively by two driving mechanisms 12, in addition
Two driving mechanisms 12 connect the variable buzzard-type wing 6 of two fuselages 4 and respective side respectively；Driving mechanism 12 includes fixed rotating shaft
121st, arc gear wheel guide rail 122 and drive gear 123；Wherein, before fixed rotating shaft 121 is separately positioned on the variable sweepback of left and right sides
Outside 6 front-axle beam of variable buzzard-type wing and two fuselages 4 of the junction and left and right sides of 2 back rest of the wing and two 4 outer side rails of fuselage
The junction of side girder；Arc gear wheel guide rail 122 is arranged in corresponding fuselage between jack stringer；Drive gear 123 is arranged on
On variable 6 back rest of buzzard-type wing of two variable 2 front-axle beams of sweepback front wing and the left and right sides, driven by motor；State of flight is converted
When, drive gear 123 is moved by the driving of motor on arc gear wheel guide rail 122, drive variable sweepback front wing 2 and it is variable before
Wing 6 is plunderred to rotate around fixed rotating shaft 121.Follower includes precursor follower 13 and rear body follower 14.Precursor is driven
Mechanism 13 connects two variable sweepback front wings 2 and anterior centrosome 1, and rear body follower 14 connects the left wing of variable buzzard-type wing 6
And right flank.Precursor follower 13 includes two precursor fixed rotating shafts, 131, two front wing sliding fulcrums and two driven cunnings of precursor
Rail 132, wherein, two precursor fixed rotating shafts 131 connect two variable 2 back rest of sweepback front wing and respective side anterior centrosome 1 respectively
Longeron；Two front wing sliding fulcrums are separately fixed on two variable sweepback front wings 2；The driven slide 132 of two precursors is set respectively
It puts in two variable 2 front-axle beams of sweepback front wing and 1 longeron junction of respective side anterior centrosome；During the variant of body, two
The back rest of variable sweepback front wing 2 is rotated rotating around two precursor fixed rotating shafts 131, and the front wing of two variable sweepback front wings 2 slides
Fulcrum moves on the driven slide 132 of precursor.Body follower 14 includes rear body fixed rotating shaft 141 afterwards, is arranged on variable sweepforward
On the front-axle beam of 6 left wing of wing and right flank junction, during the variant of body, before variable 6 left wing of buzzard-type wing and right flank
Beam is rotated rotating around rear body fixed rotating shaft 141.In the present embodiment, subsonic speed is realized by driving mechanism 12 and follower and is flown
Row state to the mode conversion of supersonic flight state, make the utility model change sweepforward twin-fuselage configuration aircraft taken into account it is sub-/
The design requirement of supersonic speed high lift-drag ratio.
The change sweepforward twin-fuselage configuration aircraft of the utility model, it can be achieved that subsonic flight state to supersonic flight state
Conversion, variant income makes subsonic speed lift resistance ratio make with improving 3-4 compared with tonnage tactical bomber when Gross Weight Takeoff is constant
War radius is improved from 3300km to 4000km, and when combat radius is constant, Gross Weight Takeoff is down to 45t from 55t, while possesses aircraft
Supersonic cruising ability；Twin fuselage and anterior centrosome fuselage arrangement, while body delivered payload capability is increased, compatible kinetic energy with
Directional energy antipersonnel weapon.In addition, the utility model can also use the design of dual radars simultaneously, cover aircraft forward detection scope
Hemisphere before entire, and conventional radar coverage is 120 °.
The above is only specific embodiment of the present utility model, but the scope of protection of the utility model is not limited to
In this, in the technical scope that any one skilled in the art discloses in the utility model, the change that can readily occur in
Change or replace, should be covered within the scope of the utility model.Therefore, the scope of protection of the utility model should be with described
Subject to scope of the claims.
Claims (9)
1. a kind of become sweepforward twin-fuselage configuration aircraft, it can be achieved that the mode of subsonic flight state to supersonic flight state turns
It changes, which is characterized in that the change sweepforward twin-fuselage configuration aircraft includes：
Anterior centrosome (1), in spheroid shape, the anterior centrosome (1) is disposed longitudinally on body front end；
Two variable sweepback front wings (2) are connected to the left and right sides of the anterior centrosome (1) lower part by becoming body mechanism,
Lifting wing flap (3) before the trailing edge of the variable sweepback front wing (2) is disposed with, the variable sweepback front wing (2) is in subsonic flight
State is as front wing, in supersonic flight state as body edge strip；
Two fuselages (4), described two fuselages (4) respectively by become body mechanism be connected to the left and right sides the variable sweepback before
The end of the wing (2) is respectively arranged with zigzag lip air intake duct (5), described two fuselages at the back of described two fuselages (4)
(4) outside of afterbody sets dynamic flare vertical fin (9) entirely respectively, and sets engine tail nozzle in the tail end of two fuselages (4)
(10), in subsonic flight state, described two fuselages (4) are extended to separating, in supersonic flight state, described two fuselages
(4) extend to move toward one another realize fitting；
Variable buzzard-type wing (6), including left wing and right flank, the left wing is connected with right flank by becoming body mechanism, the left wing and
Lower part of the right flank respectively with described two fuselages (4) is connected by becoming body mechanism, the trailing edge ecto-entad of the left wing and right flank
It is disposed with aileron (7), flaperon (8) and lifts wing flap (11) afterwards；
Undercarriage, the undercarriage are distributed in first three point type, are separately positioned under the anterior centrosome (1) and two fuselages (4)
End.
2. change sweepforward twin-fuselage configuration aircraft according to claim 1, which is characterized in that the change sweepforward twin-fuselage configuration
Aircraft realizes subsonic flight state to the mode conversion of supersonic flight state, the change body mechanism bag by becoming body mechanism
It includes：
Driving mechanism (12), including four, described two fuselages (4) of the left and right sides pass through two driving mechanisms respectively
(12) the variable sweepback front wing (2) of respective side and variable buzzard-type wing (6) are connected to；
Follower, including precursor follower (13) and rear body follower (14), precursor follower (13) connection
Two variable sweepback front wings (2) and the anterior centrosome (1), the rear body follower (14) connect the variable sweepforward
The left wing of wing (6) and right flank.
3. change sweepforward twin-fuselage configuration aircraft according to claim 2, which is characterized in that driving mechanism (12) bag
It includes：
Fixed rotating shaft (121) connects described two fuselages (4) outer side rail and variable sweepback front wing (2) back rest respectively, with
And described two fuselages (4) outer side rail and variable buzzard-type wing (6) front-axle beam are connected respectively；
Arc gear wheel guide rail (122) is arranged in corresponding fuselage between jack stringer；
Drive gear (123) is arranged on variable sweepback front wing (2) front-axle beam and the variable buzzard-type wing (6) back rest,
By motor the drive gear (123) is driven to be moved on the arc gear wheel guide rail (122), drive the variable sweepback front wing
(2) rotated with variable buzzard-type wing (6) around the fixed rotating shaft (121).
4. change sweepforward twin-fuselage configuration aircraft according to claim 2, which is characterized in that the precursor follower (13)
Including：
Two precursor fixed rotating shafts (131), connect respectively two variable sweepback front wing (2) back rest with described in respective side before in
Heart body (1) longeron, during the variant of body, variable sweepback front wing (2) back rest is rotated around the precursor fixed rotating shaft；
Two front wing sliding fulcrums are respectively fixedly disposed on two variable sweepback front wings (2)；
Two driven slides of precursor (132), before being separately positioned on described in two variable sweepback front wing (2) front-axle beams and respective side
Centerbody (1) longeron junction, during the variant of body, two front wing sliding fulcrums of the variable sweepback front wing (2)
It is moved on the driven slide of described two precursors (132).
5. change sweepforward twin-fuselage configuration aircraft according to claim 2, which is characterized in that body follower (14) after described
Including：
Body fixed rotating shaft (141) afterwards are arranged on the front-axle beam of variable buzzard-type wing (6) left wing and right flank junction, in machine
During the variant of body, the front-axle beam of variable buzzard-type wing (6) left wing and right flank is rotating around the rear body fixed rotating shaft (141)
Rotation.
6. change sweepforward twin-fuselage configuration aircraft according to claim 1, which is characterized in that the anterior centrosome (1) is internal
It is provided with loading space.
7. change sweepforward twin-fuselage configuration aircraft according to claim 1, which is characterized in that the variable sweepback front wing (2)
Aspect ratio variable range for 1-3,25 ° -70 ° of leading edge sweep excursion；The aspect ratio of the variable buzzard-type wing (6) can
Become scope 1.7-9,25 ° -70 ° of leading edge sweepforward angle excursion.
8. it is according to claim 1 change sweepforward twin-fuselage configuration aircraft, which is characterized in that it is described before lifting wing flap (3) and
Wing flap (11) is lifted afterwards to be configured to only be operated under subsonic flight state.
9. change sweepforward twin-fuselage configuration aircraft according to claim 1, which is characterized in that the entirely dynamic flare vertical fin (9)
Sharp layout is cut using double sweepback.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721208797.XU CN207450215U (en) | 2017-09-20 | 2017-09-20 | A kind of change sweepforward twin-fuselage configuration aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721208797.XU CN207450215U (en) | 2017-09-20 | 2017-09-20 | A kind of change sweepforward twin-fuselage configuration aircraft |
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|---|---|
| CN207450215U true CN207450215U (en) | 2018-06-05 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109710988A (en) * | 2018-12-04 | 2019-05-03 | 中国航空工业集团公司西安飞机设计研究所 | A kind of blended wing-body aircraft girder location determining method |
| CN110143282A (en) * | 2019-06-18 | 2019-08-20 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of aircraft using high aspect ratio twin fuselage Flying-wing |
| CN110228590A (en) * | 2019-06-30 | 2019-09-13 | 郑州航空工业管理学院 | A kind of detachable cargo hold connection wing twin fuselage logistics unmanned plane |
| CN112238941A (en) * | 2020-06-29 | 2021-01-19 | 中国南方电网有限责任公司超高压输电公司昆明局 | Unmanned aerial vehicle for accurate safe anti-misoperation convertor station inspection based on RTK positioning technology |
| CN113148141A (en) * | 2021-04-14 | 2021-07-23 | 中国空气动力研究与发展中心空天技术研究所 | Novel intelligence variant aircraft |
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2017
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109710988A (en) * | 2018-12-04 | 2019-05-03 | 中国航空工业集团公司西安飞机设计研究所 | A kind of blended wing-body aircraft girder location determining method |
| CN109710988B (en) * | 2018-12-04 | 2023-06-23 | 中国航空工业集团公司西安飞机设计研究所 | Wing body fusion body aircraft main beam position determining method |
| CN110143282A (en) * | 2019-06-18 | 2019-08-20 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of aircraft using high aspect ratio twin fuselage Flying-wing |
| CN110143282B (en) * | 2019-06-18 | 2023-07-04 | 中国空气动力研究与发展中心计算空气动力研究所 | Aircraft adopting high aspect ratio double-fuselage flying wing layout |
| CN110228590A (en) * | 2019-06-30 | 2019-09-13 | 郑州航空工业管理学院 | A kind of detachable cargo hold connection wing twin fuselage logistics unmanned plane |
| CN112238941A (en) * | 2020-06-29 | 2021-01-19 | 中国南方电网有限责任公司超高压输电公司昆明局 | Unmanned aerial vehicle for accurate safe anti-misoperation convertor station inspection based on RTK positioning technology |
| CN112238941B (en) * | 2020-06-29 | 2022-02-15 | 中国南方电网有限责任公司超高压输电公司昆明局 | Accurate safe anti-misoperation unmanned aerial vehicle for inspection of convertor station based on RTK positioning technology |
| CN113148141A (en) * | 2021-04-14 | 2021-07-23 | 中国空气动力研究与发展中心空天技术研究所 | Novel intelligence variant aircraft |
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Effective date of registration: 20201028 Address after: Building B, building 28, Jiangsu information service industry base, Guangling New Town, Yangzhou City, Jiangsu Province, 225002 Patentee after: Shenyang Aircraft Design Institute Yangzhou Collaborative Innovation Research Institute Co., Ltd Address before: Thavorn street in Huanggu District of Shenyang city of Liaoning Province, No. 40 110035 Patentee before: SHENYANG AIRCRAFT DESIGN INSTITUTE, AVIATION INDUSTRY CORPORATION OF CHINA |