CN109398705A - A kind of airfreighter - Google Patents
A kind of airfreighter Download PDFInfo
- Publication number
- CN109398705A CN109398705A CN201810216083.6A CN201810216083A CN109398705A CN 109398705 A CN109398705 A CN 109398705A CN 201810216083 A CN201810216083 A CN 201810216083A CN 109398705 A CN109398705 A CN 109398705A
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- Prior art keywords
- wing
- shoe
- gondola
- fuselage
- middle section
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- 238000005183 dynamical system Methods 0.000 claims abstract description 15
- 241000272517 Anseriformes Species 0.000 claims abstract description 8
- 238000013461 design Methods 0.000 claims description 13
- 230000006641 stabilisation Effects 0.000 claims description 6
- 238000011105 stabilization Methods 0.000 claims description 6
- 239000003381 stabilizer Substances 0.000 claims description 5
- 238000009434 installation Methods 0.000 abstract description 5
- 238000000034 method Methods 0.000 abstract description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 241000547651 Tricholoma album Species 0.000 description 1
- 230000004308 accommodation Effects 0.000 description 1
- 239000000969 carrier Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/12—Canard-type aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/06—Fins
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D7/00—Arrangements of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D9/00—Equipment for handling freight; Equipment for facilitating passenger embarkation or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
- B64U2101/60—UAVs specially adapted for particular uses or applications for transporting passengers; for transporting goods other than weapons
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of airfreighters, include that propulsion system and VTOL dynamical system, undercarriage form by fuselage, shoe, hanging, wing, front wing, vertical tail, gondola, dynamical system (engine)；Wing is mounted on fuselage and shoe middle section, gondola is mounted below fuselage by hanging connection, front wing is mounted on shoe front end, vertical tail is mounted on shoe rear end, propulsion system is mounted on above airfoil root, VTOL dynamical system is mounted on above shoe leading portion and back segment, and undercarriage is mounted below shoe front end and middle section.The method is mainly characterized in that: it is designed using Bi-Tail-Boom Layout, using high aspect ratio wing, resistance can be substantially reduced, gondola is mounted below fuselage by hanging, and wing middle section uses larger inverted diherdral, provides bigger gondola installation space；Using canard configuration, cancel tailplane, improve the duties maintainability of aircraft, be conducive to airplane ascensional force characteristic, reduces the risk that high altitude rocket transmitting bumps against empennage；The scheme of the invention can simultaneously serve as space flight carrier aircraft and logistics distribution unmanned plane scheme, when as space flight carrier aircraft, the gondola of hanging lower section can be replaced with rocket；When as logistics distribution unmanned plane, the motor of four driving propellers can be installed on shoe, make aircraft that there is VTOL ability.
Description
(1) technical field:
The present invention relates to a kind of airfreighters, belong to aviation aircraft design field.
(2) background technique:
With the fast development of business space flight, rocket miniaturization emits the characteristics of high frequency becomes business space flight.Using winged
Machine emits rocket transport high-altitude, can effectively reduce launch cost, become the mainstream demand in business space flight market.State
Inside and outside existing manufacturer attempts to repack space flight carrier aircraft, the transporter or passenger plane of active service into using normal arrangement transporter or airline carriers of passengers
Aerodynamic arrangement be known as Conventional pneumatic layout, be mainly characterized by high mounted wing or lower single-blade, the wing are hung or tail hangs turbofan hair
" T " shape or "T"-shaped is presented in motivation, vertical tail and tailplane mostly.Conventional pneumatic airplane repacks space flight into
Carrier aircraft can not adapt to meet the needs of business space flight there is the defects of at high cost, difficulty is big, air-launched difficulty is big is reequiped.
For business space flight, developing the unconventional dedicated carrier aircraft of layout becomes one of crucial outlet, and aerospace enterprise, various countries has also started
Carry out some trials.
Meanwhile with the development and changes in demand in logistics distribution market, using unmanned plane realize to mountainous region, plateau, island,
The dispatching of the special screnes such as remote country, which becomes, develops one of option.Traditional fixed wing aircraft and gyroplane all exists respective
Defect, it is difficult to all meet VTOL, the efficiently demands such as cruise.Using unconventional layout designs aircraft become realize logistics without
One of crucial outlet of man-machine new breakthrough.
" white knight " aircraft that Virgin Atlantic is developed is one of the successful experiment of space flight carrier aircraft, which uses double
Fuselage arrangement, but canard configuration is not used, there is significant difference with this programme.In pitch control, stability, high altitude rocket hair
It penetrates in safety, it is poorer than this programme, the innovative conflict to this programme is not constituted.
The CN202414153U patent of Tianjin Feng Zhiyi Science and Technology Ltd. equally uses Bi-Tail-Boom Layout and hybrid power
Configuration, but canard configuration is not used, and can only use as small drone, there is significant difference with this programme.In scheme
The scope of application in aircraft controllability, stability, is not so good as this programme, does not constitute the innovative conflict to this programme.
The CN201317462Y patent of Shenyang Rui Yi passenger plane Co., Ltd uses double shoes and increases aspect ratio wing design,
But its shoe form is different from this programme, and canard configuration is not used to design, also without adding setting for gondola using hanging
Meter, and can only be used as small drone, there is marked difference with this programme.In scheme use scope, the maneuverability of aircraft,
In delivered payload capability, it is not so good as this programme, does not constitute the innovative conflict to this programme.
(3) summary of the invention:
1, goal of the invention:
The purpose of the present invention is to provide a kind of airfreighters.The aircraft concept be provided simultaneously with large scale business space flight carrier aircraft and
The application potential of small-sized logistics distribution unmanned plane.
2, technical solution:
The present invention is a kind of airfreighter, it is by fuselage, hanging, shoe, gondola, wing, front wing, vertical tail, moves
Force system (engine), undercarriage composition；Fuselage is arranged in aircraft center, and wing is mounted on fuselage two sides, left shoe and right tail
Support is connect with wing, is arranged in fuselage two sides, front wing is mounted on left and right shoe front end, after vertical tail is mounted on left and right shoe
End, dynamical system (are divided into propulsion system and VTOL dynamical system), and propulsion system is mounted on airfoil root
Side, if when as small-sized logistics distribution unmanned plane, the motor of four driving propellers can be installed on left and right shoe as vertical
Straight landing dynamical system, to provide VTOL power.Undercarriage is located at left and right shoe leading portion and middle section.
The fuselage is arranged in aircraft center, is mainly used for installation and accommodates cockpit or flight control system, using traditional semihard
Shell type structure；
The left shoe and right shoe are arranged in fuselage two sides, are mainly used for installing front wing, vertical tail, connect wing middle section
With wing outer segment, operation of landing gear is accommodated；
The gondola is mounted below fuselage by hanging connection, and when the invention is as space flight carrier aircraft, gondola be can be replaced
Rocket；When the invention is as logistics distribution unmanned plane, holding freight in gondola；
The wing use 10 or more aspect ratio swept-back wing, taper ratio between 0.3-0.75, leading edge sweep 15 °-
Between 30 °, it is divided into the middle section wing and the outer segment wing, the middle section wing is between left and right shoe, and the outer segment wing is located at except left and right shoe, machine
Wing rear is disposed with wing flap, flaperon, elevon.Wing middle section inverted diherdral is between 8 ° -16 °, and the wing outer segment upper counterangle is
Between 0 ° -8 °, wing middle section use lower mimetic design, raise wing miding level height, can hide front wing generation purling and
Gondola arrangement provides bigger space, using high aspect ratio wing, can be effectively reduced resistance；
The front wing includes horizontal stabilizer and elevator, is installed on left and right shoe front end, which can be used buzzard-type wing,
Between 10 ° -20 ° the straight wing of no sweepback can also be used, between 4-10, taper ratio exists front wing aspect ratio in leading edge sweepforward angle
Between 0.4-0.7；
The vertical tail includes fixed fin, rudder, is installed on left and right shoe rear end, vertical tail at v-shaped outside
It skims, outer slash angle is between 0 ° -20 °, and aspect ratio is between 2-4, and taper ratio is between 0.3-0.75；
The dynamical system includes propulsion system and VTOL dynamical system, and propulsion system is installed on wing root
Above portion；When this programme is as small-sized logistics distribution unmanned plane, four drivings are installed above left and right shoe leading portion and rear end
The motor of propeller can enable aircraft be provided simultaneously with VTOL and high-performance cruise ability as VTOL dynamical system；
The undercarriage is divided into nose-gear and main landing gear, and nose-gear is installed on left and right shoe leading portion, main landing gear peace
Loaded on left and right shoe middle section, nose-gear and main landing gear can be taken in inside shoe.
3, advantage and effect:
The aircraft of the invention is provided simultaneously with the application scheme as large-scale space flight carrier aircraft and small-sized logistics distribution unmanned plane
Potentiality.When as space flight carrier aircraft, mimetic design under double shoe centers hanging structure and wing middle section provides great fire
Arrow installation space, fuselage rear not only improves from aircraft rear without horizontal tail design and carries out duties maintenance, and solves high altitude rocket
When transmitting, rocket is easy the problem of bumping against horizontal tail, reduces the risk of rocket launching.When as logistics distribution unmanned plane, double
The motor of four driving propellers, the ability for making aircraft have both VTOL and efficiently cruise, in double shoes are installed on shoe
Centre structure for pod provides larger accommodation space, being capable of the higher volume of cargo of modularization carrying；Using canard configuration, eliminate
Tailplane improves the duties maintainability and lift efficiency of aircraft；Using high aspect ratio wing, resistance can be effectively reduced
Power.
(4) Detailed description of the invention:
Fig. 1 logistics distribution unmanned plane axis side view of the present invention
Fig. 2 space flight carrier aircraft axonometric drawing of the present invention
Fig. 3 front view of the present invention
Fig. 4 side view of the present invention
Symbol description is as follows in figure: fuselage 1, left shoe 2, right shoe 3, wing 4, droope snoot 5, wing flap 6, flaperon 7,
Flaperon 8, front wing horizontal stabilizer 10, elevator 11, vertical tail stabilization 12, rudder 13, preceding rises and falls at elevon 9
Frame 14, main landing gear 15, propulsion system (engine) 16, VTOL dynamical system (engine) 17, hanging 18, gondola
19
(5) specific embodiment:
With reference to the accompanying drawings of the specification, further the preferred embodiment of the present invention is described in detail, description below
To be illustrative, not limitation of the present invention, any other similar situation are still fallen among protection scope of the present invention.
The present invention is a kind of double shoe airfreighters using canard configuration, it is by fuselage 1, left shoe 2, right shoe
3, wing 4, droope snoot 5, wing flap 6, flaperon 7, flaperon 8, elevon 9, front wing horizontal stabilizer 10, elevator 11,
Vertical tail stabilization 12, rudder 13, nose-gear 14, main landing gear 15, propulsion system (engine) 16, vertical
Dynamical system (engine) 17, hanging 18, the composition of gondola 19 drop；Wing 4 is installed on fuselage 1, left shoe 2,3 middle section of right shoe,
Gondola 19 is mounted on 1 lower section of fuselage by 18 connection of hanging, and front wing is mounted on left shoe 2,3 front end of right shoe, vertical tail installation
In left shoe 2,3 rear end of right shoe, propulsion system 16 is mounted on above 4 root of wing, and VTOL dynamical system 17 is pacified
Above left shoe 2,3 leading portion of right shoe and back segment, nose-gear 14 is mounted on left shoe 2,3 leading portion of right shoe, and master rises and falls
Frame 15 is mounted on left shoe 2,3 middle section of right shoe lower section.
The fuselage 1 is mainly used for installation and accommodates cockpit or flight control system, using traditional semi-monocoque structure；
The left shoe 2, right shoe 3 are arranged in 1 left and right sides of fuselage, and front wing is installed in front end, and vertical tail, tail are installed in rear end
Support middle section connection wing middle section and wing outer segment；
The wing 4 is swept-back wing, and leading edge sweep is between 15 ° -30 °, and using high aspect ratio wing, wing aspect ratio is super
Cross 10, for taper ratio between 0.3-0.75, wing middle section connects fuselage 1 and left shoe 2, right shoe 3, wing middle section using 8 °-
Inverted diherdral between 16 °, wing outer segment are mounted on left shoe 2,3 outside of right shoe, and wing outer segment uses the upper counterangle between 0 ° -8 °,
Wing middle section leading edge is disposed with droope snoot 5, and wing middle section rear is disposed with wing flap 5, and wing outer segment rear is disposed with flaperon
6, flaperon 7, elevon 8；
The front wing includes horizontal stabilizer 10, elevator 11, before front wing left and right ends are mounted on left shoe 2, right shoe 3
End, front wing use buzzard-type wing, and the straight wing of no sweepback can also be used between 10 ° -20 ° in leading edge sweepforward angle, front wing stabilization and
Elevator is used for aircraft pitch trim and manipulation, and aspect ratio is between 4-10, and taper ratio is between 0.4-0.7；
The vertical tail includes fixed fin 12, rudder 13, is mounted on left shoe 2,3 rear end of right shoe top, hangs down
Straight tail is skimmed at outside v-shaped, course trim, manipulation and stabilization of the outer slash angle between 0 ° -20 °, for aircraft；Aspect ratio is in 2-4
Between, taper ratio is between 0.3-0.75；
The undercarriage uses four-point undercarriage, including nose-gear 14, main landing gear 15, nose-gear 14 to be installed on a left side
Below shoe 2,3 front end of right shoe, main landing gear 15 is mounted on left shoe 2,3 middle section of right shoe lower section, and undercarriage can take in tail
Support is internal；
The propulsion system 16 includes two engines, is installed on above 4 root of wing, for providing the propulsion of aircraft
Power；When the program is as space flight carrier aircraft, using fanjet；When the program is as logistics distribution unmanned plane, can adopt
The motor or piston-mode motor or turbogenerator for driving propeller with two；
The VTOL dynamical system 17 includes four driving propeller motor, before being mounted on left shoe 2, right shoe 3
Above section and middle section, when the program is as logistics distribution unmanned plane, for providing VTOL power；
The gondola 19 is mounted on 1 lower section of fuselage by 18 connection of hanging, and when as space flight carrier aircraft, gondola can be replaced rocket
It is mounted on hanging lower section, when as logistics distribution unmanned plane, gondola can be used for loading cargo.
In order to realize goal of the invention, this patent uses following novel technical characteristic:
(1) using the biggish inverted diherdral design of double shoe designs and wing middle section, by mission payload (rocket or cargo hold) cloth
It is placed in hanging lower section, this design provides great load arrangement space；
(2) canard configuration is used, front wing stabilization is applicable in and elevator, elevon carries out pitching trim and pitching behaviour
It is vertical, tailplane is eliminated, duties maintainability and airplane ascensional force characteristic are conducive to, high-altitude is also solved and fires a rocket, is easy
The problem of knocking horizontal tail；Meanwhile front wing has pitch control efficiency more higher than horizontal tail before wing
(3) when being used as logistics distribution unmanned plane, increase the motor of four driving propellers on double shoes, keep aircraft same
When have the ability of VTOL and high-performance cruise.
Claims (10)
1. a kind of airfreighter, it is by fuselage, left shoe, right shoe, hanging, gondola, wing, front wing, vertical tail, rises and falls
Frame, dynamical system composition；The wing is mounted on fuselage and shoe middle section, and gondola is mounted below fuselage by hanging connection, should
Front wing is mounted on shoe front end, which is mounted on shoe rear end, which is mounted below shoe front end and middle section,
The propulsion system is mounted on above airfoil root, and VTOL dynamical system is mounted on above shoe front end and back segment.
2. aircraft according to claim 1, it is characterised in that use Bi-Tail-Boom Layout, double shoes are arranged in airframe
The left and right sides is connected by wing middle section with fuselage, installs front wing in shoe front end, vertical tail is installed in shoe rear end.
3. aircraft according to claim 1, it is characterised in that use canard configuration, front wing left and right ends are mounted on left tail
Support and right shoe front end, front wing include horizontal stabilizer and elevator, which uses buzzard-type wing, and sweepforward angle is 10 ° -20 °,
The straight wing of no sweepback can be used.
4. aircraft according to claim 1, which is characterized in that after the vertical tail is installed on left shoe and right shoe
End is skimmed at outside v-shaped, and outer slash angle is between 0 ° -20 °, and aspect ratio is between 2-4, and taper ratio is between 0.3-0.75, vertical tail
Including fixed fin and rudder.
5. aircraft according to claim 1, which is characterized in that when as space flight carrier aircraft, mentioned using two fanjets
For thrust power, when as logistics unmanned plane, can be used two driving propellers motor or piston-mode motor or
Turbogenerator provides thrust power, and engine is installed on above airfoil root.
6. aircraft according to claim 1, which is characterized in that when as logistics distribution unmanned plane, using four driving spiral shells
The motor for revolving paddle provides VTOL power, and engine is mounted on above left shoe, right shoe leading portion and back segment.
7. aircraft according to claim 1, which is characterized in that wing middle section use lower mimetic design, 8 ° of inverted diherdral -18 ° it
Between, wing outer segment uses upper mimetic design, and the upper counterangle is at 0 ° -8 °.
8. aircraft according to claim 1, which is characterized in that using center hanging design, gondola passes through hanging connection peace
It is anti-under wing middle section below fuselage, larger space is provided for gondola；When aircraft is as space flight carrier aircraft, gondola can be replaced
It is changed to rocket.
9. aircraft according to claim 1, which is characterized in that carry out pitching trim, manipulation, stabilization using front wing, cancel
Tailplane increases elevon and assists pitch control.
10. aircraft according to claim 1 rises and is characterized in that, four-point undercarriage is used, nose-gear is mounted on
Below left and right shoe front end, main landing gear is mounted below left and right shoe middle section, and undercarriage can be taken in inside shoe.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810216083.6A CN109398705A (en) | 2018-03-15 | 2018-03-15 | A kind of airfreighter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810216083.6A CN109398705A (en) | 2018-03-15 | 2018-03-15 | A kind of airfreighter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109398705A true CN109398705A (en) | 2019-03-01 |
Family
ID=65464120
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810216083.6A Pending CN109398705A (en) | 2018-03-15 | 2018-03-15 | A kind of airfreighter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109398705A (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110065637A (en) * | 2019-05-05 | 2019-07-30 | 南京智飞航空科技有限公司 | A kind of docking unmanned plane and aerial handling goods mode |
| 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 |
| CN110510116A (en) * | 2019-09-20 | 2019-11-29 | 北京大学 | Rotor and vector propulsion system combined type aircraft |
| CN111301676A (en) * | 2019-03-15 | 2020-06-19 | 上海峰飞航空科技有限公司 | VTOL aerial vehicle with ascending overlapping propellers |
| CN113232882A (en) * | 2021-05-17 | 2021-08-10 | 南京航空航天大学 | Tailstock type unmanned flight platform applicable to ballistic launching and launching method |
| CN113232854A (en) * | 2021-05-17 | 2021-08-10 | 南京航空航天大学 | Distributed unmanned aerial vehicle platform applicable to ballistic launching and launching method |
| CN113335504A (en) * | 2021-08-09 | 2021-09-03 | 中国空气动力研究与发展中心空天技术研究所 | Rotor wing fairing of composite wing aircraft |
| CN113844648A (en) * | 2021-09-21 | 2021-12-28 | 峰飞国际有限公司 | Combined type VTOL fixed wing unmanned aerial vehicle |
| CN114555467A (en) * | 2019-08-16 | 2022-05-27 | 埃姆普里萨有限公司 | Unmanned aerial vehicle with reduced acoustic signature |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111301676A (en) * | 2019-03-15 | 2020-06-19 | 上海峰飞航空科技有限公司 | VTOL aerial vehicle with ascending overlapping propellers |
| CN110065637A (en) * | 2019-05-05 | 2019-07-30 | 南京智飞航空科技有限公司 | A kind of docking unmanned plane and aerial handling goods mode |
| 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 |
| CN114555467A (en) * | 2019-08-16 | 2022-05-27 | 埃姆普里萨有限公司 | Unmanned aerial vehicle with reduced acoustic signature |
| CN114555467B (en) * | 2019-08-16 | 2024-05-03 | 埃姆普里萨有限公司 | Unmanned aerial vehicle with reduced acoustic signature |
| CN110510116A (en) * | 2019-09-20 | 2019-11-29 | 北京大学 | Rotor and vector propulsion system combined type aircraft |
| CN113232882A (en) * | 2021-05-17 | 2021-08-10 | 南京航空航天大学 | Tailstock type unmanned flight platform applicable to ballistic launching and launching method |
| CN113232854A (en) * | 2021-05-17 | 2021-08-10 | 南京航空航天大学 | Distributed unmanned aerial vehicle platform applicable to ballistic launching and launching method |
| CN113335504A (en) * | 2021-08-09 | 2021-09-03 | 中国空气动力研究与发展中心空天技术研究所 | Rotor wing fairing of composite wing aircraft |
| CN113844648A (en) * | 2021-09-21 | 2021-12-28 | 峰飞国际有限公司 | Combined type VTOL fixed wing unmanned aerial vehicle |
| EP4151540A1 (en) * | 2021-09-21 | 2023-03-22 | Shanghai Autoflight Co., Ltd. | Hybrid vtol fixed-wing aerial vehicle |
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Application publication date: 20190301 |