CN109080824A - A kind of Fixed Wing AirVehicle with tilted propeller - Google Patents
A kind of Fixed Wing AirVehicle with tilted propeller Download PDFInfo
- Publication number
- CN109080824A CN109080824A CN201810974885.3A CN201810974885A CN109080824A CN 109080824 A CN109080824 A CN 109080824A CN 201810974885 A CN201810974885 A CN 201810974885A CN 109080824 A CN109080824 A CN 109080824A
- Authority
- CN
- China
- Prior art keywords
- fixed wing
- propeller
- shaft
- steering engine
- fuselage
- 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.)
- Pending
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
-
- 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
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
- B64C29/0033—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being tiltable relative to the fuselage
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/13—Propulsion using external fans or propellers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
Abstract
The present invention provides a kind of Fixed Wing AirVehicles with tilted propeller, including fuselage, steering engine, propeller and fixed wing；The fuselage is symmetrically arranged fixed wing centered on central axes, and propeller is respectively set in the fixed wing end pin, the steering engine that setting control propeller verts in the fuselage；Parallel perforative tiliting axis is set in fixed wing, and the tiliting axis end protruded into fixed wing is connected by steering engine wheel disc with steering engine；The tiliting axis end for stretching out fixed wing is connected with tilter, is rotatablely connected shaft on the tilter, and the shaft free end above tilter is connected with propeller, and setting drives the brake component of propeller rotation in shaft.A kind of Fixed Wing AirVehicle with tilted propeller of the present invention, can VTOL and level run speed it is fast, high reliablity.
Description
Technical field
The invention belongs to unmanned plane fields, more particularly, to a kind of Fixed Wing AirVehicle with tilted propeller.
Background technique
Aircraft is by mankind's manufacture, can fly away from ground, in the instrument flying object of space flight.Model plane and small-sized in recent years
The fast development of aircraft brings convenience for activities such as aerial survey, scoutings in small size air.
Small aircraft is divided into Fixed Wing AirVehicle and rotor craft, the advantage of Fixed Wing AirVehicle be loading capacity it is big,
Horizontal flight speed is fast, voyage is remote and high reliablity, but needs landing runway, cannot complete VTOL movement；And rotor
Although aircraft horizontal direction speed does not have, Fixed Wing AirVehicle is fast, it is irrealizable excellent with Fixed Wing AirVehicle
Gesture can be realized VTOL, and advantage is to adapt to the landform of various complexity, can accomplish quick landing, hovering.
Therefore, designing a aircraft for having both both Fixed Wing AirVehicle and rotor craft advantage has important meaning
Justice.
Summary of the invention
In view of this, the present invention is directed to propose a kind of Fixed Wing AirVehicle with tilted propeller, can VTOL and
Energy level run speed is fast, high reliablity.
In order to achieve the above objectives, the technical scheme of the present invention is realized as follows:
A kind of Fixed Wing AirVehicle with tilted propeller, including fuselage, steering engine, propeller and fixed wing；
The fuselage is symmetrically arranged fixed wing centered on central axes, and spiral shell is respectively set in the fixed wing end pin
Paddle is revolved, the steering engine that setting control propeller verts in the fuselage；
Parallel perforative tiliting axis is set in fixed wing, protrudes into the tiliting axis end in fixed wing and passes through steering engine wheel
Disk is connected with steering engine；The tiliting axis end for stretching out fixed wing is connected with tilter, and shaft, position are rotatablely connected on the tilter
Shaft free end above tilter is connected with propeller, and setting drives the brake component of propeller rotation in shaft.
Further, the tilter includes the upper beam and lower beam of setting side by side up and down, in upper beam and lower beam
Two sides are vertically arranged support plate respectively, and the shaft is rotatablely connected by bearing and upper beam.
Further, the brake component includes motor, and the motor is set to below lower beam, and the output shaft of motor protrudes into down
Above crossbeam, output shaft outer wall is nested with decelerating through motor tooth, shaft reducing gear is nested on shaft outer wall, and decelerating through motor tooth subtracts with shaft
Fast tooth engagement.
Further, be respectively set in two support plates fixing set, the tiliting axis be through at fixing set in, tiliting axis and
Fix set is radially correspondingly arranged clamping hole, fixes bolt and is bolted in clamping hole.
Further, aileron is set far from head side on the fixed wing.
Further, fixed wing girder is respectively set in the two sides up and down of tiliting axis, two fixed wing girder ends are logical
It crosses and snaps connection.
Further, fixed wing reinforced shaft is respectively set at left and right sides of tiliting axis.
Further, the steering engine is fixed in steering engine mounting base, and it is solid that the steering engine mounting base passes through fixed wing attachment base
It is scheduled on fuselage mounting plate, the connecting plate perpendicular with it is set on fixed wing attachment base, is distinguished on the connecting plate
Wing reinforced shaft connecting hole and wing girder connecting hole are set.
Further, the empennage is set as twin vertical fin structure, including lateral empennage and is set to hanging down for lateral empennage both ends
Elevator is arranged in the end of straight tail, the transverse direction empennage, and rudder is respectively set in the end of the vertical tail.
Further, the fuselage includes stringer and bulkhead, and the stringer and bulkhead grafting support, the fuselage surface are overcoating
Mask.
Compared with the existing technology, a kind of Fixed Wing AirVehicle with tilted propeller of the present invention has following excellent
Gesture:
Fuselage and fixed wing are the structure of Fixed Wing AirVehicle, have the advantage of Fixed Wing AirVehicle, and voyage is remote, horizontal
Flying speed is fast；And propeller is set in the fixation wing end pin of Fixed Wing AirVehicle, realize VTOL, the energy of vertical flight
Power enables its aircraft to have both the advantage of the two simultaneously；
Steering engine and tiliting axis are respectively arranged in fuselage and fixed wing, and space utilization rate is high, ingenious in design；
By fuselage be central axes centered on be symmetrically arranged fixed wing, propeller is respectively set in fixed wing end pin,
Two groups are symmetrical arranged, the yawed flight of aircraft may be implemented.
Detailed description of the invention
The attached drawing for constituting a part of the invention is used to provide further understanding of the present invention, schematic reality of the invention
It applies example and its explanation is used to explain the present invention, do not constitute improper limitations of the present invention.In the accompanying drawings:
Fig. 1 is a kind of Fixed Wing AirVehicle broken isometric schematic diagram with tilted propeller described in the embodiment of the present invention；
Fig. 2 is a kind of Fixed Wing AirVehicle section schematic top plan view of energy VTOL described in the embodiment of the present invention；
Fig. 3 is part A enlarged diagram in Fig. 2；
Fig. 4 is tilter schematic diagram described in the embodiment of the present invention.
Description of symbols:
1- steering engine；11- steering engine wheel disc；12- steering engine mounting base；13- axle sleeve；2- tiliting axis；3- tilter；31- upper beam；
32- lower beam；33- support plate；41- motor；42- shaft；43- decelerating through motor tooth；44- shaft reducing gear；45- fixes set；46-
Fix bolt；47- propeller；5- fuselage；51- fixes wing attachment base；52- connecting plate；53- wing reinforced shaft connecting hole；54-
Wing girder connecting hole；55- stringer；56- bulkhead；6- fixes wing；61- aileron；62- fixes wing reinforced shaft；63- fixes machine
Wing girder；64- buckle；7- transverse direction empennage；8- vertical tail；9- elevator；10- rudder.
Specific embodiment
It should be noted that in the absence of conflict, the feature in embodiment and embodiment in the present invention can phase
Mutually combination.
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", "upper", "lower",
The orientation or positional relationship of the instructions such as "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is
It is based on the orientation or positional relationship shown in the drawings, is merely for convenience of description of the present invention and simplification of the description, rather than instruction or dark
Show that signified device or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as pair
System of the present invention.In addition, term " first ", " second " etc. are used for description purposes only, it is not understood to indicate or imply relatively heavy
The property wanted or the quantity for implicitly indicating indicated technical characteristic.The feature for defining " first ", " second " etc. as a result, can be bright
Show or implicitly include one or more of the features.In the description of the present invention, unless otherwise indicated, " multiple " contain
Justice is two or more.
In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or be integrally connected；It can
To be mechanical connection, it is also possible to be electrically connected；It can be directly connected, can also can be indirectly connected through an intermediary
Connection inside two elements.For the ordinary skill in the art, above-mentioned term can be understood by concrete condition
Concrete meaning in the present invention.
The present invention will be described in detail below with reference to the accompanying drawings and embodiments.
Picture 1-4, a kind of Fixed Wing AirVehicle with tilted propeller, including fuselage 5, steering engine 1, propeller 47 and fixation
Wing 6；
The fuselage 5 is symmetrically arranged fixed wing 6 centered on central axes, and fixed 6 end pin of wing is set respectively
Propeller 47 is set, the steering engine 1 that setting control propeller 47 verts in the fuselage 5；
Parallel perforative tiliting axis 2 is set in fixed wing 6, and 2 end of tiliting axis protruded into fixed wing 6 passes through rudder
Wheel disk 11 is connected with steering engine 1；2 end of tiliting axis for stretching out fixed wing 6 is connected with tilter 3, rotates on the tilter 3
Shaft 42 is connected, 42 free end of shaft above tilter 3 is connected with propeller 47, and setting drives propeller in shaft 42
The brake component of 47 rotations.
Fuselage 5 and fixed wing 6 are the structure of Fixed Wing AirVehicle, the advantage with Fixed Wing AirVehicle, and voyage is remote, water
Flat flying speed is fast；And propeller 47 is set in 6 end pin of fixation wing of Fixed Wing AirVehicle, and realize VTOL, it is vertical to fly
Capable ability enables its aircraft to have both the advantage of the two simultaneously；
Steering engine 1 and tiliting axis 2 are respectively arranged in fuselage 5 and fixed wing 6, and space utilization rate is high, ingenious in design；
By fuselage 5 be central axes centered on be symmetrically arranged fixed wing 6, spiral is respectively set in fixed 6 end pin of wing
Paddle 47 is symmetrical arranged two groups, the yawed flight of aircraft may be implemented.
The tilter 3 includes the upper beam 31 and lower beam 32 of setting side by side up and down, in upper beam 31 and lower beam 32
Two sides be vertically arranged support plate 33 respectively, the shaft 42 is rotatablely connected by bearing and upper beam 31.
The upper beam 31 and lower beam 32 of tilter 3 including setting side by side up and down, the two of upper beam 31 and lower beam 32
Support plate 33 is respectively set in side, such to design the weight that can reduce whole tilter 3, mitigates the load-bearing of whole aircraft.
Also, lightening hole is also set up on upper beam 31, to mitigate the weight of tilter 3, to mitigate whole aircraft
Load-bearing.
The brake component includes motor 41, and the motor 41 is set to 32 lower section of lower beam, and the output shaft of motor 41 protrudes into
32 top of lower beam, output shaft outer wall are nested with decelerating through motor tooth 43, are nested with shaft reducing gear 44, decelerating through motor on 42 outer wall of shaft
Tooth 43 is engaged with shaft reducing gear 44.
Brake component includes motor 41, and motor 41 is engaged with decelerating through motor tooth 43 by shaft reducing gear 44 to control to spiral shell
The power output effect of paddle 47 is revolved, the tooth pitch ratio that wherein shaft reducing gear 44 is engaged with decelerating through motor tooth 43 is 4:1, plays speed
Spend the effect adjusted.
Fixing set 45 is respectively set in two support plates 33, the tiliting axis 2 is through in fixing set 45, tiliting axis 2
Clamping hole is radially correspondingly arranged with fix set 45, is fixed bolt 46 and is bolted in clamping hole.
Setting fixing set 45 in support plate 33, fixing set 45 and tiliting axis 2 are radially correspondingly arranged clamping hole, fix spiral shell
Rotation is bolted in clamping hole, and such design realizes that tiliting axis 2 and tilter 3 are detachably connected, and is not only fixed and is stablized, but also dismantles
Convenient, design is reasonable.
Aileron 61 is set far from head side on the fixed wing 6；The setting of aileron 61 can be in aircraft flight mistake
The rolling of aircraft is controlled in journey.
Fixed wing girder 63 is respectively set in the two sides up and down of tiliting axis 2, two 63 ends of fixed wing girder pass through
64 connection of buckle.
The fixed fixed wing 6 of 63 pairs of wing girder plays the fixed effect of support, and fixed 63 end of wing girder passes through card
64 connection of button prevents the fixed deformation of wing 6 from fixed wing girder 63 being caused to be absolved, guarantees the stability of fixed wing 6.
Fixed wing reinforced shaft 62 is respectively set in the left and right sides of tiliting axis 2.
As the ancillary equipment of fixed wing reinforced shaft 62, play the role of reinforcing support to fixed wing 6, with fixed machine
Wing girder 63 combines, dual fixed reinforcement, sturdy construction.
The steering engine 1 is fixed in steering engine mounting base 12, and it is solid that the steering engine mounting base 12 passes through fixed wing attachment base 51
It is scheduled on fuselage mounting plate, the connecting plate 52 perpendicular with it, the connecting plate 52 is set on the fixed wing attachment base 51
On wing reinforced shaft connecting hole 53 and wing girder connecting hole 54 is respectively set.
The fuselage 5 includes stringer 55 and bulkhead 56, and the stringer 55 and 56 grafting of bulkhead support, 5 surface of fuselage
Overcoating mask.
Bulkhead 56 use linden laminate, stringer 55 use carbon fiber pipe, bulkhead 56 be 5 frame of fuselage, 55 grafting of stringer every
Frame 56 runs through entire fuselage 5, increases by 5 intensity of fuselage.Mask uses Ba Ersha cork wood.The quality of materials that overall structure uses is light,
High reliablity, manufacturing cost is low, and processing technology is simple.
Wherein the blade of propeller 47 uses big 2170 model of boundary.
The course of work: steering engine 1 carries out angular adjustment to tilter 3 by tiliting axis 2, to realize the control to propeller 47
System.When aircraft vertical landing, the drive of propeller 47 is moved upwardly or downwardly；When aircraft tilts flight upward or downward
When, verted to propeller 47 certain angle using steering engine 1, while realizing aircraft vertical upward or downward, have forward or
Pulling force backward；When vehicle yaw, two symmetrically arranged tiliting axis 2 drive respectively 47 1, propeller to it is previous to
After yaw can be realized；When two tiliting axis 2 turn forward simultaneously to be turn 90 degrees, at this moment 47, propeller provide forward drawing
Power, can control the rolling of aircraft by the aileron 61 of aircraft, and the elevator 9 on empennage controls the pitching of aircraft, side
The yaw that aircraft is controlled to rudder 10, to realize that aircraft controls the flight attitude of aircraft under fixed-wing mode.
The foregoing is merely illustrative of the preferred embodiments of the present invention, be not intended to limit the invention spirit and principle it
Interior, any modification, equivalent replacement, improvement and so on should be included within the present invention encloses.
Claims (10)
1. a kind of Fixed Wing AirVehicle with tilted propeller, it is characterised in that: including fuselage (5), steering engine (1), propeller
(47) and it is fixed wing (6)；
The fuselage (5) is symmetrically arranged fixed wing (6) centered on central axes, fixed wing (6) the end pin difference
It is arranged propeller (47), the steering engine (1) that setting control propeller (47) is verted in the fuselage (5)；
Parallel perforative tiliting axis (2) is set in fixed wing (6), it is logical to protrude into tiliting axis (2) end in fixed wing (6)
Steering engine wheel disc (11) is crossed to be connected with steering engine (1)；Tiliting axis (2) end for stretching out fixed wing (6) is connected with tilter (3), institute
Rotation connection shaft (42) on tilter (3) is stated, shaft (42) free end above tilter (3) and propeller (47) phase are located at
Even, the brake component that setting drives propeller (47) to rotate in shaft (42).
2. a kind of Fixed Wing AirVehicle with tilted propeller according to claim 1, it is characterised in that: the tilter
(3) include setting side by side up and down upper beam (31) and lower beam (32), in two sides of upper beam (31) and lower beam (32) point
It is not vertically arranged support plate (33), the shaft (42) is rotatablely connected by bearing and upper beam (31).
3. a kind of Fixed Wing AirVehicle with tilted propeller according to claim 2, it is characterised in that: the brake component
Including motor (41), the motor (41) is set to below lower beam (32), and the output shaft of motor (41) protrudes into lower beam (32)
Top, output shaft outer wall are nested with decelerating through motor tooth (43), are nested with shaft reducing gear (44), decelerating through motor tooth on shaft (42) outer wall
(43) it is engaged with shaft reducing gear (44).
4. a kind of Fixed Wing AirVehicle with tilted propeller according to claim 3, it is characterised in that: supported at two
It is respectively set on plate (33) and fixes set (45), the tiliting axis (2) is through in fixing set (45), tiliting axis (2) and fixing set
(45) be radially correspondingly arranged clamping hole, fix bolt (46) and be bolted in clamping hole.
5. a kind of Fixed Wing AirVehicle with tilted propeller according to claim 1, it is characterised in that: the fixed machine
Far from head side setting aileron (61) on the wing (6).
6. a kind of Fixed Wing AirVehicle with tilted propeller according to claim 1, it is characterised in that: in tiliting axis
(2) two sides up and down are respectively set fixed wing girder (63), and two fixed wing girder (63) ends are connected by buckle (64)
It connects.
7. a kind of Fixed Wing AirVehicle with tilted propeller according to claim 6, it is characterised in that: in tiliting axis
(2) fixed wing reinforced shaft (62) is respectively set at left and right sides of.
8. a kind of Fixed Wing AirVehicle with tilted propeller according to claim 7, it is characterised in that: the steering engine
(1) it is fixed on steering engine mounting base (12), the steering engine mounting base (12) passes through fixed wing attachment base (51) and is fixed on fuselage
On mounting plate, the connecting plate (52) perpendicular with it be set, on the connecting plate (52) on fixed wing attachment base (51)
Wing reinforced shaft connecting hole (53) and wing girder connecting hole (54) is respectively set.
9. a kind of Fixed Wing AirVehicle with tilted propeller according to claim 1, it is characterised in that: the empennage is set
It is set to twin vertical fin structure, including lateral empennage (7) and is set to the vertical tail (8) at lateral empennage (7) both ends, the transverse direction tail
Elevator (9) are arranged in the end of the wing (7), and rudder (10) are respectively set in the end of the vertical tail (8).
10. a kind of Fixed Wing AirVehicle with tilted propeller according to claim 1, it is characterised in that: the fuselage
It (5) include stringer (55) and bulkhead (56), the stringer (55) and bulkhead (56) grafting support, fuselage (5) surface are overcoating
Mask.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810974885.3A CN109080824A (en) | 2018-08-24 | 2018-08-24 | A kind of Fixed Wing AirVehicle with tilted propeller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810974885.3A CN109080824A (en) | 2018-08-24 | 2018-08-24 | A kind of Fixed Wing AirVehicle with tilted propeller |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109080824A true CN109080824A (en) | 2018-12-25 |
Family
ID=64794656
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810974885.3A Pending CN109080824A (en) | 2018-08-24 | 2018-08-24 | A kind of Fixed Wing AirVehicle with tilted propeller |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109080824A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110949654A (en) * | 2019-12-25 | 2020-04-03 | 彭振根 | Aircraft |
| CN114476051A (en) * | 2021-12-29 | 2022-05-13 | 北京特种机械研究所 | Vector power rotating mechanism of aircraft |
| RU2798617C1 (en) * | 2022-12-28 | 2023-06-23 | Публичное акционерное общество "Объединенная авиастроительная корпорация" (ПАО "ОАК") | Structural-bearing system of the tail section of the aircraft |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120234968A1 (en) * | 2005-10-18 | 2012-09-20 | Smith Frick A | Aircraft with freewheeling engine |
| CN205022861U (en) * | 2015-09-06 | 2016-02-10 | 长沙鸿浪自动化科技有限公司 | VTOL fixed wing aircraft |
| CN208484828U (en) * | 2018-05-10 | 2019-02-12 | 中国民航大学 | A kind of Fixed Wing AirVehicle of energy VTOL |
-
2018
- 2018-08-24 CN CN201810974885.3A patent/CN109080824A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120234968A1 (en) * | 2005-10-18 | 2012-09-20 | Smith Frick A | Aircraft with freewheeling engine |
| CN205022861U (en) * | 2015-09-06 | 2016-02-10 | 长沙鸿浪自动化科技有限公司 | VTOL fixed wing aircraft |
| CN208484828U (en) * | 2018-05-10 | 2019-02-12 | 中国民航大学 | A kind of Fixed Wing AirVehicle of energy VTOL |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110949654A (en) * | 2019-12-25 | 2020-04-03 | 彭振根 | Aircraft |
| CN114476051A (en) * | 2021-12-29 | 2022-05-13 | 北京特种机械研究所 | Vector power rotating mechanism of aircraft |
| RU2798617C1 (en) * | 2022-12-28 | 2023-06-23 | Публичное акционерное общество "Объединенная авиастроительная корпорация" (ПАО "ОАК") | Structural-bearing system of the tail section of the aircraft |
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20181225 |
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| RJ01 | Rejection of invention patent application after publication |