CN115196009A - Vertical take-off and landing aircraft - Google Patents
Vertical take-off and landing aircraft Download PDFInfo
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- CN115196009A CN115196009A CN202211067460.7A CN202211067460A CN115196009A CN 115196009 A CN115196009 A CN 115196009A CN 202211067460 A CN202211067460 A CN 202211067460A CN 115196009 A CN115196009 A CN 115196009A
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/064—Stringers; Longerons
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
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Abstract
The invention discloses a vertical take-off and landing aircraft, which adopts the technical scheme that the vertical take-off and landing aircraft comprises an aircraft body, a tail pushing system and a lift force system; the lift system comprises a lift truss girder, a structure truss girder and a rotor wing structure, wherein the lift truss girder is symmetrically arranged along the wingspan direction of a wing, the structure truss girder is connected with the wing and is arranged between the lift truss girder and a machine body, the structure truss girder is further connected with an empennage structure, the structure truss girder and the lift truss girder are both connected with a plurality of rotor wing structures, the rotor wing structure is arranged on the upper portion of the machine body, the tail pushing system is obliquely arranged on the rotor wing structure and comprises a tail pushing propeller, and the tail pushing propeller is arranged on the machine body and is arranged at the tail of the machine body and between the machine body and the empennage structure. The vertical take-off and landing aircraft has the effects of providing convenient flight control, improving the stability of attitude control and improving the safety.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a vertical take-off and landing aircraft.
Background
With the continuous development of aviation technology, different types of manned aircrafts are also proposed to relieve the traffic pressure of ground traveling in order to reduce the traveling pressure of ground traffic to a certain extent, but many existing aircrafts need to take off by running assistance, so that the aircrafts are inconvenient to apply in cities, and the vertical takeoff and landing type aircrafts are particularly important and become the most main propulsion content of the aircrafts at present.
A traditional chinese patent publication No. CN111731475A discloses a vertical take-off and landing tilting composite wing aircraft, which includes a fuselage, wings and a tail wing, wherein the middle part of the fuselage is provided with a battery cabin, the middle rear part is provided with a flight control cabin, the rear part is provided with a propulsion engine cabin, and the bottom of the fuselage is provided with a load cabin and a aerial survey camera lens; the battery cabin is internally provided with power battery components in an opposite insertion way, the flight control cabin is internally provided with a flight control module and an integrated control circuit board, the propulsion engine cabin is internally provided with a propulsion motor and a propulsion control electric controller, and the load cabin is internally provided with a replaceable load cabin module; the front and back sides of the wings are provided with a plurality of rotor struts, the upper parts of the wing struts are provided with wing folding mechanisms, the bottoms of the wing struts are provided with flaperon steering engines, the outer ends of the wing struts extend backwards to be provided with flaperon mixed control surfaces, and the outer ends of the two sides of the wing struts are provided with wingtip winglets.
Although this kind of aircraft can carry out VTOL, during the yaw control under many rotor modes, because the rotor is in the lower part, the moment of standing of easily appearing deflecting is not enough when controlling deflecting, need consume more electric energy to because the rotor is in the lower part, lead to penetrating into the risk of cockpit when the rotor breaks, still can have the risk of penetrating into other power pack, make the circumstances of inconvenient and the security is low on holistic flight control, need to solve to this kind of safe and convenient VTOL aircraft of operation.
Disclosure of Invention
In view of the defects in the prior art, the invention aims to provide a vertical take-off and landing aircraft which has the effects of providing convenient flight control, improving the stability of attitude control and improving the safety.
In order to realize the purpose, the invention provides the following technical scheme:
a vertical take-off and landing aircraft, comprising: the device comprises a machine body, a tail pushing system and a lift system;
the aircraft body is provided with wings, the lift system comprises lift trusses, structural trusses and rotor wing structures, the lift trusses are symmetrically arranged along the wingspan direction of the wings, the structural trusses are connected with the wings and are arranged between the lift trusses and the aircraft body, the structural trusses and the lift trusses are both connected with a plurality of rotor wing structures, and the rotor wing structures on the structural trusses and the lift trusses are symmetrically arranged along the width direction of the wings respectively;
the rotor wing structure is positioned at the upper part of the body and is obliquely arranged, a first rotating plane is formed on the rotor wing structure positioned on the structure truss girder, a second rotating plane is formed on the rotor wing structure positioned on the lift truss girder, the first rotating plane and the second rotating plane are arranged in a crossed manner, the first rotating plane and the second rotating plane are also obliquely arranged along the navigation direction of the body, and the oblique direction is that one side facing the tail wing structure is higher than one side facing the front end of the body;
the tail pushing system comprises a tail pushing propeller, the tail pushing propeller is arranged on the tail of the engine body and is arranged between the engine body and the tail wing structure, and the tail pushing propeller is used for providing tail pushing thrust.
As a further improvement of the invention, the distance of the rotor structure located on the structural girder and close to the tail structure to the center of mass of the body is greater than the distance of the rotor structure located on the lift girder and close to the tail structure to the center of mass of the body.
As a further improvement of the invention, the first rotating plane and the second rotating plane form the same inclined included angle with the wing.
As a further improvement of the invention, the rotor structures on the structural girders and the rotor structures on the lift girders rotate in opposite directions, the rotor structures on the same structural girders rotate in opposite directions, and the rotor structures on the same lift girders rotate in opposite directions.
As a further improvement of the invention, the structure truss is also connected with an empennage structure, the empennage structure comprises a vertical empennage and a horizontal empennage, and the horizontal empennage is connected with vertical empennages positioned at two sides of the machine body.
As a further improvement of the invention, the operation modes of the rotor structure include a rotor mode;
when the rotor structure is the rotor mode, along anticlockwise rotation the rotor structure produces first moment of torsion, follows clockwise rotation the structure rotor produces the second moment of torsion, first moment of torsion with the size of second moment of torsion equals, the total lift value size that the rotor structure produced with the gravity of organism equals.
As a further improvement of the present invention, when the yaw control is performed in the rotor mode;
if the lift force provided by the rotor wing structure generating the first torque is improved, the lift force provided by the rotor wing structure generating the second torque is reduced, the total lift force value generated by the rotor wing structure is kept equal to the gravity of the body, the first torque is larger than the second torque, and the aircraft is controlled to rotate in the counterclockwise direction generating the first torque;
if improve and produce when the lift that the rotor structure of second moment of torsion provided, then reduce and produce the lift that the rotor structure of first moment of torsion provided, the total lift value size that the rotor structure produced keeps and the gravity of organism equals, the second moment of torsion is greater than first moment of torsion, control the aircraft is rotatory along the clockwise direction that produces the second moment of torsion.
As a further improvement of the invention, the working modes of the rotor structure further comprise a fixed wing mode;
when the rotor wing structure is switched from a rotor wing mode to a fixed wing mode, the tail thrust propeller is started and provides tail thrust, so that the wings generate lift force, the lift force generated by the rotor wing structure is reduced, when the lift force of the airframe is replaced by the wings, the rotor wing structure is closed, at the moment, the blades of the rotor wing structure are kept consistent with the navigation direction of the airframe, and the rotor wing structure generates auxiliary force for weakening resistance when the airframe navigates.
As a further improvement of the invention, the rotor structure on the lift spar also serves to provide a righting force when the body is subjected to a crosswind in the direction of the wing.
As a further improvement of the invention, the bottom of the machine body is also provided with a front three-point type undercarriage.
The invention has the beneficial effects that: through the rotor structure of symmetry setting on structure longeron and lift longeron, can provide the lift of VTOL when carrying out VTOL, the rotor structure that is located on structure longeron and the lift longeron is in the slope setting, first rotation plane and second rotation plane have been formed respectively, and set up along the slope of navigation direction and be the state of leaning forward, make and provide stable lift when control goes up and down and deflect, whole because the cross arrangement of first rotation plane and second rotation plane when controlling, realize not only can conveniently controlling the organism and carry out the change of gesture and can also keep the stability of organism, realized that convenient flight is controlled and is improved the stability that improves attitude control and the effect of security.
Drawings
FIG. 1 is a schematic view showing the structure of a machine body;
FIG. 2 is a schematic front view of the body;
FIG. 3 is a schematic top view of the housing;
FIG. 4 is a schematic view showing the structure of the air flow generated by the rotor structure during forward flight of the aircraft;
FIG. 5 is a schematic view showing a tilted arrangement of the rotor structure;
figure 6 is a schematic view showing a forward tilt arrangement of the rotor structure;
FIG. 7 is a schematic view showing the body when it is subjected to a crosswind;
fig. 8 is a schematic view showing the rotation direction of the rotor structure.
Reference numerals: 1. a body; 11. an airfoil; 12. a landing gear; 2. a lift truss; 3. a structural truss; 4. a rotor structure; 5. an empennage structure; 51. erecting a tail wing; 52. a horizontal rear wing; 53. a diversion tail angle; 6. and pushing the propeller at the tail.
Detailed Description
The present invention will be described in further detail with reference to the drawings and examples. In which like parts are designated by like reference numerals. It should be noted that the terms "front," "back," "left," "right," "upper" and "lower" used in the following description refer to directions in the drawings, and the terms "bottom" and "top," "inner" and "outer" refer to directions toward and away from, respectively, the geometric center of a particular component.
Referring to fig. 1 to 8:
the invention relates to a vertical take-off and landing aircraft, which comprises an aircraft body 1, a tail pushing system and a lift system, wherein the aircraft body 1 is provided with a wing 11, the lift system comprises a lift truss 2, a structural truss 3 and a rotor wing structure 4, the lift truss 2 is symmetrically arranged along the wingspan direction of the wing 11, the structural truss 3 is connected with the wing 11 and is arranged between the lift truss 2 and the aircraft body 1, the structural truss 3 is also connected with a tail wing structure 5, the tail wing structure 5 comprises a vertical tail wing 51 and a horizontal tail wing 52, the vertical tail wing 51 and the structural truss 3 are integrally formed, a diversion tail angle 53 is formed between the vertical tail wing 51 and the structural truss 3, the horizontal tail wing 52 is connected with the vertical tail wings 51 positioned at two sides of the machine body 1, the structural truss girder 3 and the lift truss girder 2 are both connected with a plurality of rotor wing structures 4, the rotor wing structures 4 positioned on the structural truss girder 3 and the lift truss girder 2 are respectively symmetrically arranged along the width direction of the wing 11, the lift truss girder 2 and the structural truss girder 3 can be respectively arranged into a plurality of numbers, the lift truss girder 2 and the structural truss girder 3 provided in the embodiment are respectively two, the rotor wing structures 4 arranged on the lift truss girder 2 and the structural truss girder 3 are respectively provided into two numbers in the embodiment, and the bottom of the machine body 1 is also provided with a front three-point undercarriage 12, so that the machine body 1 can be used for sliding.
The rotor wing structure 4 is arranged on the upper portion of the machine body 1 in an inclined mode, the rotor wing structure 4 is arranged on the upper portion of the machine body 1, so that the risk that fragments are injected into a cabin and other power units when the rotor wing structure 4 breaks is avoided, a first rotating plane is formed on the rotor wing structure 4 on the structure truss beam 3, a second rotating plane is formed on the rotor wing structure 4 on the lift truss beam 2, the first rotating plane and the second rotating plane are arranged in a crossed mode, the first rotating plane and the second rotating plane are arranged in an inclined mode in the sailing direction of the machine body 1, the inclined direction is one side, higher than the front end of the machine body 1, of the tail wing structure 5, the sailing direction of the machine body 1 is an X axis and a course is a positive axis, the wingspan direction of the wing 11 is a Y axis and the direction on the right side of the machine body 1 is a positive axis, the direction perpendicular to the wing 11 is a Z axis and the perpendicular upward direction is a positive axis, namely, an included angle generated between the first rotating plane and the XY plane generated by the rotor wing structure 4 on the structure truss beam 3 and the lift beam structure is arranged in the positive axis and the negative lift beam structure, and the rotor wing structure is arranged on the Z axis, and the lift beam structure is arranged in the forward tilting direction, and the lift beam structure is arranged on the Z axis and the Z axis 3.
First rotation plane and second rotation plane are the same with the slope contained angle that wing 11 formed, are located on the structure longeron 3 and be close to the rotor structure 4 of empennage structure 5 to the distance of organism 1 barycenter be greater than and be located on the lift longeron 2 and be close to the rotor structure 4 of empennage structure 5 to the distance of organism 1 barycenter, be located rotor structure 4 on the structure longeron 3 and the direction of rotation that is located rotor structure 4 on the lift longeron 2 are opposite, are located same the direction of rotation of rotor structure 4 on the structure longeron 3 is opposite, is located same the direction of rotation of rotor structure 4 on the lift longeron 2 is opposite.
The operating modes of the rotor structure 4 include a rotor mode;
when rotor structure 4 was the rotor mode, along anticlockwise rotation rotor structure 4 produced first moment of torsion, along clockwise rotation the structure rotor produces the second moment of torsion, first moment of torsion with the size of second moment of torsion equals, the total lift value size that rotor structure 4 produced with organism 1's gravity equals, when deflecting control during the rotor mode.
If the lift force provided by the rotor wing structure 4 generating the first torque is increased, the lift force provided by the rotor wing structure 4 generating the second torque is reduced, the total lift force value generated by the rotor wing structure 4 is kept equal to the gravity of the body 1, the first torque is larger than the second torque, and the aircraft is controlled to rotate in the counterclockwise direction generating the first torque.
If improve and produce when the lift that rotor structure 4 of second moment of torsion provided, then reduce and produce the lift that rotor structure 4 of first moment of torsion provided, the total lift value size that rotor structure 4 produced keeps equal with organism 1's gravity, the second moment of torsion is greater than first moment of torsion, control the aircraft is rotatory along the clockwise direction that produces the second moment of torsion.
Note that the first torque generated is Ma, the second torque generated is Mb, ma and Mb are equal when yaw control is not performed, the total lift value L generated is equal to the gravity of the body 1, when yaw control is performed, for example, counterclockwise yaw is performed, the lift value provided by the rotor structure 4 generating the first torque is increased to L1, the lift value provided by the rotor structure 4 generating the second torque is decreased to L2, the first torque is increased to Ma ', the second torque is decreased to Mb', in this case, L1-L = L-L2, the total lift value L is always equal to the gravity of the body 1, and the total torque of the body 1 rotating around the Z axis is recorded as M-in this case, M-in =4 × (Ma '-Mb'), since Ma 'is greater than Mb', the body 1 rotates entirely in the counterclockwise direction, and similarly, when the body 1 is controlled to rotate clockwise, by increasing the second torque, the first torque is reduced to control the body 1 to rotate clockwise, but the moment of inertia of the Z axis of the existing aircraft is large, so that the rotating torque is provided by the rotor alone by the counter torque, so that the acceleration of the aircraft rotating is low, and the aircraft is inconvenient to control during the deflection control, in the embodiment, the rotor structure 4 is arranged obliquely, the lift force provided by the tilted rotor structure 4 generates a horizontal component, when the inclination angle between the rotor structure 4 and the Z axis is X °, the generated horizontal component F = sinx ° L, the horizontal separation provided by the rotor structure 4 generating the first torque is F1, F1= sinx ° L1, the horizontal separation provided by the rotor structure 4 generating the second torque is F2, F2= sinx ° L2, and the flying attitude can be changed rapidly and conveniently by improving the moment of the yaw of the body 1 under the action of the horizontal component, meanwhile, the whole body of the machine body 1 can be kept stable under the action of horizontal component force.
The tail-thrust system comprises a tail-thrust propeller 6, the tail-thrust propeller 6 is arranged at the tail part of the body 1 and is arranged between the body 1 and the tail wing structure 5, the tail-thrust propeller 6 is used for providing tail-thrust, and the working mode of the rotor wing structure 4 further comprises a fixed wing mode;
when the rotor structure 4 is switched from the rotor mode to the fixed-wing mode, the tail-thrust propellers 6 are activated and provide tail thrust to cause the wings 11 to generate lift, the lift generated by the rotor structure 4 is reduced, when the lift of the body 1 is replaced by the wings 11, the rotor structure 4 is turned off, the blades of the rotor structure 4 are kept consistent with the sailing direction of the body 1, when the body 1 sails, the rotor structure 4 generates auxiliary force for weakening the resistance, the rotation speed of the rotor structure 4 is reduced while the thrust is supplied by the activation of the tail-thrust propellers 6, so that when the total lift is kept unchanged, the quick switching is performed to provide lift control when the body 1 sails by replacing the rotor structure 4 with the wings 11, thereby effectively saving electric energy and improving the overall sailing range, and when the rotor structure 4 is tilted forward, when the tilt angle is y °, when switching to the fixed-wing mode, the increased speed blades of the rotor structure 4 are consistent with the sailing direction of the fixed-wing structure 1, and during the switching, the rotor structure 4 is in a forward tilting state, so that the rotor structure 4 generates a forward horizontal component, when the flow of the rotor structure 4 generates an airflow = F2, and the auxiliary force is further reduced, thereby reducing the auxiliary force of the flight time of the flight in the flight time of the flight mode.
The rotor structure 4 on the lift truss 2 is further used for providing a aligning force when the body 1 is subjected to a crosswind along the direction of the wing 11, when the body 1 is influenced by the crosswind, the body 1 tilts, when the tilting angle is z °, the integral gravity G of the body 1 generates a component force F3 in the horizontal direction, F3= sinz °, and the direction of the component force points to the aligning direction of the body 1, the vertical component force generated by the rotor structure 4 on the lift truss 2 after tilting is F4, F4= L sin (x + z) °, F4 is smaller than L, and the rotor structure 4 on the right side can fall back to be aligned under the action of the vertical component force F4 generated by the rotor structure 4, so that the body 1 can be aligned quickly under the action of the tilted rotor structure 4 when the whole machine is subjected to the crosswind, and the condition that the body 1 is not easily overturned by the crosswind to a large extent occurs.
The working principle and the effect are as follows:
through the rotor structure 4 of symmetry setting on structure longeron 3 and lift longeron 2, can provide the lift of VTOL when carrying out VTOL, rotor structure 4 that is located on structure longeron 3 and the lift longeron 2 is in the slope setting, first rotation plane and second rotation plane have been formed respectively, and it is the state that leans forward to set up along the slope of navigation direction, make and can provide stable lift when control goes up and down and deflect, whole because the cross arrangement of first rotation plane and second rotation plane when controlling, the realization not only can conveniently control organism 1 and carry out the change of gesture and can also keep organism 1's stability, the effect of convenient flight improvement attitude control's stability and improvement security has been realized.
The above description is only a preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above embodiments, and all technical solutions belonging to the idea of the present invention belong to the protection scope of the present invention. It should be noted that modifications and embellishments within the scope of the invention may occur to those skilled in the art without departing from the principle of the invention, and are considered to be within the scope of the invention.
Claims (10)
1. A VTOL aerial vehicle, comprising: the device comprises a machine body (1), a tail pushing system and a lift force system;
the aircraft is characterized in that wings (11) are arranged on the aircraft body (1), the lift system comprises lift trusses (2), structural trusses (3) and rotor wing structures (4), the lift trusses (2) are symmetrically arranged along the wingspan direction of the wings (11), the structural trusses (3) are connected with the wings (11) and are arranged between the lift trusses (2) and the aircraft body (1), the structural trusses (3) and the lift trusses (2) are both connected with a plurality of rotor wing structures (4), and the rotor wing structures (4) on the structural trusses (3) and the lift trusses (2) are symmetrically arranged along the width direction of the wings (11);
the rotor wing structure (4) is positioned at the upper part of the machine body (1) and is obliquely arranged, a first rotating plane is formed on the rotor wing structure (4) positioned on the structure truss girder (3), a second rotating plane is formed on the rotor wing structure (4) positioned on the lift truss girder (2), the first rotating plane and the second rotating plane are arranged in a crossed manner, the first rotating plane and the second rotating plane are also obliquely arranged along the sailing direction of the machine body (1), and the oblique direction is that one side facing the empennage structure (5) is higher than one side facing the front end of the machine body (1);
the tail pushes away the system and pushes away screw (6) including the tail, the tail pushes away screw (6) and sets up in organism (1) and be the afterbody and between organism (1) and fin structure (5), the tail pushes away screw (6) and is used for providing the tail and pushes away thrust.
2. The VTOL aerial vehicle of claim 1, wherein: the distance between the rotor wing structure (4) close to the empennage structure (5) and the center of mass of the body (1) on the structure truss girder (3) is larger than the distance between the rotor wing structure (4) close to the empennage structure (5) and the center of mass of the body (1) on the lift truss girder (2).
3. The vtol aerial vehicle of claim 1, wherein: the first rotating plane and the second rotating plane form the same inclined included angle with the wing (11).
4. The VTOL aerial vehicle of claim 1, wherein: lie in rotor structure (4) on structure longeron (3) and the direction of rotation that lies in rotor structure (4) on lift longeron (2) are opposite, are located same the direction of rotation of rotor structure (4) on structure longeron (3) is opposite, is located same the direction of rotation of rotor structure (4) on lift longeron (2) is opposite.
5. The VTOL aerial vehicle of claim 1, wherein: still be connected with fin structure (5) on structure longeron (3), fin structure (5) are including standing fin (51) and horizontal fin (52), vertical fin (51) that horizontal fin (52) connection is located organism (1) both sides.
6. The VTOL aerial vehicle of claim 1, wherein: the working modes of the rotor structure (4) comprise a rotor mode;
when rotor structure (4) were the rotor mode, along anticlockwise rotation rotor structure (4) produced first moment of torsion, along clockwise rotation the structure rotor produces the second moment of torsion, first moment of torsion with the size of second moment of torsion equals, the total lift value size that rotor structure (4) produced with the gravity of organism (1) equals.
7. The VTOL aerial vehicle of claim 6, wherein: when yaw control is performed in the rotor mode;
if the lift force provided by the rotor wing structure (4) generating the first torque is increased, the lift force provided by the rotor wing structure (4) generating the second torque is reduced, the total lift force value generated by the rotor wing structure (4) is kept equal to the gravity of the body (1), the first torque is larger than the second torque, and the aircraft is controlled to rotate in the anticlockwise direction generating the first torque;
if improve and produce when rotor structure (4) of second moment of torsion provide lift, then reduce and produce the lift that rotor structure (4) of first moment of torsion provided, the total lift value size that rotor structure (4) produced keeps equal with the gravity of organism (1), the second moment of torsion is greater than first moment of torsion, control the aircraft is rotatory along the clockwise direction that produces the second moment of torsion.
8. The VTOL aerial vehicle of claim 7, wherein: the working modes of the rotor structure (4) also include a fixed wing mode;
when rotor structure (4) switches over from the rotor mode to the fixed wing mode, tail pushes away propeller (6) and starts and provide tail thrust, so that wing (11) produce the lift, reduces the lift that rotor structure (4) produced, when the lift of organism (1) is replaced by wing (11), closes rotor structure (4), and at this moment the paddle of rotor structure (4) keeps unanimous with organism (1) navigation direction, rotor structure (4) produce the auxiliary force that is used for weakening the resistance when organism (1) navigates.
9. The VTOL aerial vehicle of claim 8, wherein: the rotor structure (4) on the lift truss (2) is also used for providing a aligning force when the body (1) is subjected to a side wind along the direction of the wing (11).
10. The VTOL aerial vehicle of any one of claims 1-9, wherein: the bottom of the machine body (1) is also provided with a front three-point type undercarriage (12).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211067460.7A CN115196009A (en) | 2022-09-01 | 2022-09-01 | Vertical take-off and landing aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211067460.7A CN115196009A (en) | 2022-09-01 | 2022-09-01 | Vertical take-off and landing aircraft |
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| CN115196009A true CN115196009A (en) | 2022-10-18 |
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| CN202211067460.7A Pending CN115196009A (en) | 2022-09-01 | 2022-09-01 | Vertical take-off and landing aircraft |
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| CN114771826A (en) * | 2022-04-14 | 2022-07-22 | 成都沃飞天驭科技有限公司 | A vertical take-off and landing aircraft and a control method for a vertical take-off and landing aircraft |
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| CN218368284U (en) * | 2022-09-01 | 2023-01-24 | 零重力飞机工业(合肥)有限公司 | Vertical take-off and landing aircraft |
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