CN112829925A - Lift device for vertical take-off and landing of aircraft, aircraft and fixed-wing aircraft - Google Patents
Lift device for vertical take-off and landing of aircraft, aircraft and fixed-wing aircraft Download PDFInfo
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- CN112829925A CN112829925A CN202110303884.8A CN202110303884A CN112829925A CN 112829925 A CN112829925 A CN 112829925A CN 202110303884 A CN202110303884 A CN 202110303884A CN 112829925 A CN112829925 A CN 112829925A
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- aircraft
- lift device
- centrifugal impeller
- transmission shaft
- lift
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/001—Shrouded propellers
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C15/00—Attitude, flight direction, or altitude control by jet reaction
- B64C15/02—Attitude, flight direction, or altitude control by jet reaction the jets being propulsion jets
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- 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
- B64C29/02—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
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- 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
- B64C29/02—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
- B64C29/04—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded characterised by jet-reaction propulsion
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/001—Flying saucers
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- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
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Abstract
The invention provides a lift device for vertical take-off and landing of an aircraft, the aircraft and a fixed-wing aircraft, comprising: a centrifugal impeller disposed above the support member; the power device is arranged below the supporting part and is connected with the centrifugal impeller through a transmission shaft, the power device drives the centrifugal impeller to rotate through the transmission shaft, a negative pressure area is formed above the supporting part, and an upward lifting force is generated on the supporting part; the guide cover is arranged on the periphery of the supporting component and is connected with the supporting component through a connecting piece; the air pushed to the periphery of the support part by the centrifugal impeller forms airflow and horizontally shoots towards the guide cover, the direction of the airflow is changed by the guide cover to enable the airflow to be jetted towards the right lower part, and upward reaction force is generated on the guide cover. The invention can make the lift force directly act on the aircraft body, the transmission shaft only drives the blades to rotate, and the weight of the aircraft body and the load is not born, thereby greatly improving the safety and the reliability of the helicopter, the rotor type unmanned aerial vehicle and the vertical take-off and landing fixed wing aircraft.
Description
Technical Field
The invention relates to the field of aircrafts and unmanned planes, in particular to a lifting device for vertically taking off and landing an aircraft, an aircraft and a fixed-wing aircraft.
Background
The helicopter is used as an aircraft capable of vertically taking off and landing, hovering and slowly flying at low altitude, has the application and importance in national defense, and plays an important role in rescue and relief work, medical rescue, public security and patrol, fire fighting and lifesaving and engineering construction. With the development of electronic technology in recent years, small-sized multi-rotor unmanned aerial vehicles using the same lift principle as traditional helicopters have been developed at a rapid pace, and have penetrated aspects of production and life from children's toys to photography and video recording, small object delivery and the like.
No matter be traditional true helicopter or small-size rotor formula unmanned aerial vehicle, its lift and the power that advances all derive from the rotor, lean on the power of engine to pass through transmission device drive screw (rotor) high-speed rotatory and produce lift, lift acts on the blade to on using the organism through the transmission shaft. Briefly, the helicopter body in flight is suspended on the rotor through the transmission shaft, which can be visually described as a "life suspension shaft", and the rotor and the transmission shaft rotate at high speed, and the rotor and the transmission shaft not only bear huge torque, but also bear the weight of the helicopter body and load, which not only increases the difficulty of manufacturing and maintenance, but also provides challenges for the safety and reliability of the helicopter, but also does not have a better design.
On the other hand, vertical take-off and landing are ideal take-off and landing modes of fixed-wing aircrafts, and through decades of research and practice, although several different lift-force types of fixed-wing aircrafts with vertical take-off and landing functions are developed in the world, the fixed-wing aircrafts and rotary-wing helicopters are combined to take off in a helicopter mode and are converted into fixed-wing aircrafts after reaching a certain height, and the conversion process has very high requirements on mechanical performance and experience of operators and accidents occur frequently.
The Chinese patent with the application number of CN201811274291.8 is found through retrieval, and discloses a vertical take-off and landing aircraft, which belongs to the technical field of aircrafts and comprises an aircraft body, wings, a reversing lift device, a vertical lift device, a steering propeller and a sled landing gear. A main controller is arranged in the machine body and is connected with the reversing lift device, the vertical lift device and the steering propeller; the wings are in a sweepback wing type; the reversing lift force device is positioned at the front end of the aircraft body, can perform multi-angle steering under the control of the main controller, provides lift force in the vertical direction or forward pulling force for the aircraft, and can change the course of the aircraft by changing the direction of the pulling force; the vertical lift device adopts a mode that a motor drives the blades to rotate to provide upward lift for the airplane, and the vertical lift device is fixed on the trailing edge of the wing through the supporting rod. The vertical lift device (4) comprises four motors with propellers, the four motors are fixed on the rear edge of the wing (2) through support rods, blades of the four motors are on the same horizontal plane, the directions of the two motors close to the wing tip part of the wing (2) are opposite, the directions of the two motors close to the fuselage (1) are opposite, and the directions of the motors on the same side of the fuselage (1) are opposite; the four motors mutually offset the torque, so that the airplane can stably vertically ascend and descend; the aircraft changes the pitching of the aircraft by controlling the motor rotating speed of the vertical lift device (4) through the main controller, when the rotating speeds of four motors of the vertical lift device (4) are increased, the lift force at the tail part of the aircraft body (1) is greater than the lift force of the wings (2), so that the aircraft nose faces downwards, when the rotating speed of the motors of the vertical lift device (4) is reduced, the lift force at the tail part of the aircraft body (1) is less than the lift force of the wings (2), and the aircraft nose faces upwards; the airplane can also control the lateral rolling of the airplane by controlling the rotating speed difference of the motors of the vertical lift devices (4) at the two sides of the airplane body (1) through the main controller; when the rotating speeds of the two motors of the vertical lift device (4) positioned on the left side of the airplane body (1) are greater than those of the two motors on the right side of the airplane body (1), the airplane rolls to the right; when the rotating speeds of the two motors of the vertical lift device (4) positioned on the left side of the airplane body (1) are lower than those of the two motors on the right side of the airplane body (1), the airplane rolls to the left. However, the vertical lift device of the above patent has the following disadvantages: the lift force device is still based on the working principle of the propeller, the lift force directly acts on the propeller blades and is transmitted to the body through the transmission shaft, and the structure and the mode of generating the lift force are similar to those of the existing rotor helicopter.
Disclosure of Invention
In view of the defects in the prior art, the invention aims to provide a lifting device for vertically taking off and landing an aircraft, the aircraft and a fixed-wing aircraft.
In a first aspect, the present invention provides a lift device for vertical take-off and landing of an aircraft, including:
a support member;
a centrifugal impeller disposed above the support member;
the power device is arranged below the supporting part, is connected with the centrifugal impeller through a transmission shaft, and drives the centrifugal impeller to rotate through the transmission shaft, so that air above the supporting part is pushed to the periphery of the supporting part by blades of the centrifugal impeller, a negative pressure area is formed above the supporting part, and upward lifting force is generated on the supporting part to form a first part of the lifting force;
the guide cover is arranged on the periphery of the supporting component, and the inner wall of the guide cover is connected with the outer wall of the supporting component through a connecting piece; the air pushed to the periphery of the support part by the centrifugal impeller forms airflow and is shot to the inner wall of the guide cover in the horizontal direction, the direction of the airflow is changed by the guide cover and is shot to the right lower side, and therefore upward reaction force is generated on the guide cover, and the second part of the lifting force is formed.
Preferably, the support member is a disc-shaped member provided with a central through hole for passing through the drive shaft, the drive shaft being rotatable about an axial direction thereof.
Preferably, the connecting piece is a bar-shaped component, the bar-shaped component is uniformly distributed on the outer wall of the disc-shaped component along the circumferential direction of the disc-shaped component, and the bar-shaped component extends outwards along the outer wall of the disc-shaped component, so that a gap is reserved between the outer wall of the disc-shaped component and the inner wall of the guide cover, a channel is provided for downward spraying of the air flow, and the air flow is sprayed downwards through the gap.
Preferably, the number of said connectors is 4.
Preferably, the guide cover is a circular truncated cone-shaped part, and an included angle between the side surface and the bottom surface of the circular truncated cone-shaped part is 45 degrees.
Preferably, a notch is arranged on the side wall of the circular truncated cone-shaped component, and the notch is a side nozzle of the air flow, so that part of the air flow is sprayed out to the side through the side nozzle;
the side nozzle is provided with a guide plate, and the guide plate can cover the whole side nozzle; the opening angle of the guide plate is controlled, so that the size and the direction of side jet flow are adjusted, the jet direction of the air flow is changed to generate torque in the direction opposite to the driving torque, and the driving torque is balanced to keep the torque balance of the whole lift device.
Preferably, the circular truncated cone-shaped component is provided with two symmetrical notches; the opening angle of the guide plate on each notch can be independently controlled.
Preferably, the guide plate is a plate-shaped member, one side of the plate-shaped member is rotatably connected with one side of the side nozzle, and the other side of the plate-shaped member is a free end and can rotate around one side of the plate-shaped member.
The invention provides a dish-shaped sightseeing aircraft in a second aspect, which comprises a lifting device for vertically taking off and landing the aircraft;
the sightseeing cabin is used for accommodating passengers and is arranged below the supporting component of the lift device;
the mechanical cabin is arranged below the sightseeing cabin and is used for installing a power device of the lift force device and storing required materials;
and the undercarriage is arranged at the bottom of the mechanical cabin.
The invention provides a fixed wing aircraft in a third aspect, which comprises a lifting device for vertically taking off and landing the aircraft; the left wing, the right wing, the left horizontal tail wing and the right horizontal tail wing of the body are all provided with the lift force device.
The working principle of the lift force device is as follows: the power device drives the centrifugal impeller to rotate through the transmission shaft, the air above the supporting part is pushed to the periphery of the supporting part by the blades of the centrifugal impeller rotating at high speed, a negative pressure area is formed above the supporting part, the air pressure below the supporting part is higher than the air pressure above the supporting part, upward lifting force is generated on the supporting part, meanwhile, the air pushed to the periphery of the supporting part by the rotating centrifugal impeller forms airflow which horizontally shoots towards the guide cover, and the airflow can change the direction after shooting towards the guide cover and sprays towards the right lower side, so that upward reaction force is generated on the guide cover, and therefore, the lifting force generated by the whole lifting device is composed of two parts: the first part is the lift generated by the air pressure difference above and below the lift disc, and the second part is the upward reaction force formed by the downward jet airflow.
Compared with the prior art, the invention has at least one of the following beneficial effects:
the lifting device of the invention has the advantages that through structural improvement, the centrifugal impeller and the transmission shaft are only responsible for pushing air above the supporting part to the periphery of the lifting disc, and the centrifugal impeller and the transmission shaft do not bear lifting force, so that the lifting force is exerted on the supporting part and the guide cover, the defect of 'a dead suspension shaft' that a body is suspended on blades through the transmission shaft rotating at high speed when a traditional rotor wing type aircraft flies is overcome, the stress state of the transmission shaft is greatly improved, and the safety of the aircraft is improved.
The lift device is used for vertical take-off and landing of an aircraft, the lift can directly act on the aircraft body, the transmission shaft only drives the blades to rotate, the weight of the aircraft body and load is not borne, the safety and the reliability of the helicopter and the rotor type unmanned aerial vehicle are greatly improved, the lift device can be applied to vertical take-off and landing of a fixed wing aircraft, and the application scenes of the helicopter, the fixed wing aircraft and the unmanned aerial vehicle are expanded more widely.
The lifting device is simple in structure and high in reliability.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a top view of a lift device for vertical takeoff and landing of an aircraft according to a preferred embodiment of the present invention;
FIG. 2 is a side view of a lift device for vertical takeoff and landing of an aircraft according to a preferred embodiment of the present invention;
FIG. 3 is an exploded view of a lift device for vertical takeoff and landing of an aircraft according to a preferred embodiment of the present invention;
FIG. 4 is a schematic structural view of a dish-shaped sightseeing vehicle according to a preferred embodiment of the invention;
FIG. 5 is a schematic structural view of a lift device for VTOL of a fixed-wing aircraft according to a preferred embodiment of the present invention;
the scores in the figure are indicated as: the device comprises a centrifugal impeller 1, a transmission shaft 2, a power device 3, a disc-shaped part 4, a connecting piece 5, a guide cover 6, a side nozzle 7, a guide plate 8, a sightseeing cabin 101, a machinery cabin 102, wheels 103, a body 201, wings 202, a horizontal tail wing 203, a first lift device 204, a second lift device 205, a third lift device 206 and a fourth lift device 207.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications can be made by persons skilled in the art without departing from the spirit of the invention. All falling within the scope of the present invention.
Example 1
Referring to fig. 1, the present embodiment provides a lift device for vertical take-off and landing of an aircraft, including: a support member, a centrifugal impeller 1, a power unit 3 and a guide housing 6.
The centrifugal impeller 1 is mounted above the support member. The centrifugal impeller 1 is driven by the power device 3 to rotate, and blades of the centrifugal impeller 1 rotate to push air to move from the center to the periphery of the supporting part.
The power device 3 is a power module of the whole lift device and provides power for driving the centrifugal impeller 1 to rotate. The power means 3 may be an electric motor. Referring to fig. 2, the power unit 3 is mounted below the support member and fixed to the machine body 201 (aircraft). The power device 3 is connected with the centrifugal impeller 1 through the transmission shaft 2, the power device 3 drives the centrifugal impeller 1 to rotate through the transmission shaft 2, air above the supporting part is pushed to the periphery of the supporting part by the rotating centrifugal impeller 1, a negative pressure area is formed above the supporting part, and because the air pressure below the supporting part is higher than that above the supporting part, upward lifting force is generated on the supporting part to form a first part of the lifting force; at the same time, the air pushed toward the periphery of the support member by the rotating centrifugal impeller 1 forms an air flow, which is horizontally directed toward the guide cover 6.
Referring to fig. 1 and 3, the guide cover 6 is disposed on the periphery of the support member, and the inner wall of the guide cover 6 and the outer wall of the support member are connected as a whole by a connecting member 5; the air pushed to the periphery of the support member by the centrifugal impeller 1 forms an airflow horizontally directed toward the guide hood 6, and the airflow is redirected by the guide hood 6 to be ejected directly downward, thereby generating an upward reaction force on the guide hood 6, constituting a second part of the lift. Preferably, the guide cover 6 is a truncated cone-shaped member, and an angle between a side surface and a bottom surface of the truncated cone-shaped member is 45 °, and when the angle is 45 °, a direction of the airflow directed to the guide cover 6 in a horizontal direction is changed to be vertically downward.
The centrifugal impeller 1 of the above-described lift device is only responsible for pushing the air above the support element towards the periphery of the support element and does not bear the lift force exerted on the support element and on the two non-moving parts of the guide cowl 6. Therefore, when the lift device is used for providing lift for vertical take-off and landing of an aircraft, the lift can directly act on the body 201 of the aircraft, the transmission shaft 2 only drives the blades to rotate, the weight of the body 201 and load is not borne, and the safety and reliability of the helicopter and the rotor type unmanned aerial vehicle can be greatly improved. The lift device can be applied to vertical take-off and landing of the fixed-wing aircraft, and the application scenes of the helicopter, the fixed-wing aircraft and the unmanned aerial vehicle are expanded more widely.
In other partially preferred embodiments, as shown in fig. 1, the support member is a disc-shaped member 4, and the disc-shaped member 4 is provided with a central through hole for passing through the drive shaft 2, and the central through hole penetrates through the thickness direction of the disc-shaped member 4. The drive shaft 2 can rotate about its axial direction. The upper end of the transmission shaft 2 is connected with the centrifugal impeller 1 positioned above the disc-shaped part 4, and the lower end of the transmission shaft 2 is connected with the power device 3 positioned below the disc-shaped part 4.
In other preferred embodiments, referring to fig. 1, the connecting members 5 are uniformly distributed on the outer wall of the disc-shaped member 4 along the circumferential direction thereof, and the connecting members 5 extend outward along the outer wall of the disc-shaped member 4, so that a gap is left between the outer wall of the disc-shaped member 4 and the inner wall of the guide housing 6. The gap between the inner wall of the guide housing 6 and the disc-shaped member 4 provides a passage for the downward ejection of the air flow, so that the air flow is ejected downward through the gap. Preferably, the number of connecting elements 5 is 4. The connecting piece 5 may be a strip-like member.
In another preferred embodiment, the guide cover 6 is a truncated cone-shaped member with a notch, and the notch is a side jet 7 for the air flow, so that part of the air flow is jetted sideward through the side jet 7.
The side nozzle 7 is provided with a guide plate 8, and the guide plate 8 can cover the whole side nozzle 7; the opening angle of the guide plate 8 is controlled, so that the size and the direction of the side jet flow are adjusted, and the jet direction of the air flow is changed to generate torque in the opposite direction of the driving torque, so that the driving torque is balanced to keep the torque balance of the whole lift device.
In the specific implementation, the side nozzles 7 on the truncated cone-shaped component can be arranged according to the specific situation: when only one lifting device is used, the circular truncated cone-shaped component is provided with the side nozzles 7; when one aircraft uses two lifting devices, the torque balance can be achieved through the reverse rotation of the impellers of the two lifting devices. The number of the side nozzles 7 can be adjusted according to actual requirements.
In other partially preferred embodiments, the truncated cone shaped member is provided with two symmetrical notches, the guide plate 8 in each notch being independently controllable.
In other partially preferred embodiments, the guide plate 8 is a plate-like member, one side of which is rotatably connected to one side of the side nozzle 7, and the other side of which is a free end and is rotatable around one side of the plate-like member.
Example 2
Referring to fig. 4, the present embodiment provides a dish-shaped sightseeing aircraft, which includes a lift device for vertically taking off and landing an aircraft, a sightseeing cabin 101, a machinery cabin 102 and landing gears.
The left side and the right side of the guide cover 6 are respectively provided with a side nozzle, and the opening angle and the direction of the guide plate 8 are controlled, so that power is provided for movement of the disc-shaped aircraft while the torque of the impeller is balanced.
A sightseeing cabin 101 for accommodating passengers (visitors), the sightseeing cabin 101 being arranged below the support members of the lift device. The disc-shaped part 4, the centrifugal impeller 1 and the guide cover 6 of the lift device are positioned above the sightseeing cabin 101, and the disc-shaped part 4 is installed at the top of the sightseeing cabin 101 and can be used as a top sealing plate of the sightseeing cabin 101. The sightseeing cabin 101 can be a cylindrical space with the periphery made of transparent materials and the top opened, and the transmission shaft 2 penetrates through the central axis of the sightseeing cabin 101 from bottom to top. The visitor can view the scenery around the inside of the sightseeing cabin 101 through the transparent outer wall.
The machinery chamber 102 is disposed at the lower part of the sightseeing chamber 101, and the machinery chamber 102 is a space similar to a semi-ellipsoid for installing the power device 3 and storing other required materials. The bottom of the machinery bay 102 is provided with landing gear. Landing gear is the support and movement system of the dish aircraft over the ground. The landing gear may be formed from 3 wheels 103 and a coupling member which function to provide support for the dish aircraft when it lands on the ground, whilst allowing the aircraft to move over the ground.
Example 3
Referring to fig. 5, the present embodiment provides a fixed-wing aircraft that includes four aircraft vertical take-off and landing lift devices (i.e., a first lift device 204, a second lift device 205, a third lift device 206, and a fourth lift device 207) to provide lift for vertical take-off and landing of the fixed-wing aircraft. A first lift device 204, a second lift device 205, a third lift device 206 and a fourth lift device 207 are respectively arranged on two wings 202 and two horizontal tail wings 203 of the body 201. When the fixed-wing aircraft takes off and lands, the fixed-wing aircraft can be stably lifted up or dropped down by adjusting the lift force of the 4 lift force devices.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention.
Claims (10)
1. A lift device for vertical take-off and landing of an aircraft, comprising:
a support member;
a centrifugal impeller disposed above the support member;
the power device is arranged below the supporting part, is connected with the centrifugal impeller through a transmission shaft, and drives the centrifugal impeller to rotate through the transmission shaft, so that air above the supporting part is pushed to the periphery of the supporting part by blades of the centrifugal impeller, a negative pressure area is formed above the supporting part, and upward lifting force is generated on the supporting part to form a first part of the lifting force;
the guide cover is arranged on the periphery of the supporting component, and the inner wall of the guide cover is connected with the outer wall of the supporting component through a connecting piece; the air pushed to the periphery of the support part by the centrifugal impeller forms airflow and is shot to the inner wall of the guide cover in the horizontal direction, the direction of the airflow is changed by the guide cover and is shot to the right lower side, and therefore upward reaction force is generated on the guide cover, and the second part of the lifting force is formed.
2. The aircraft VTOL lift device of claim 1,
the supporting component is a disc-shaped component, the disc-shaped component is provided with a central through hole used for penetrating through the transmission shaft, and the transmission shaft can rotate around the axial direction of the transmission shaft.
3. The aircraft VTOL lift device of claim 2,
the connecting piece is the bar part, the bar part is followed the circumference evenly distributed of disc part on the outer wall of disc part, just the bar part is followed the outer wall of disc part outwards extends, makes the outer wall of disc part with leave the clearance between the inner wall of direction cover, for the air current downwardly spray provide the passageway, make the air current pass through the clearance and spray downwards.
4. The aircraft VTOL lift device of claim 3, wherein the number of connectors is 4.
5. The aircraft VTOL lift device of claim 3, wherein the guide cap is a truncated cone shaped part with a side surface forming an angle of 45 ° with the bottom surface.
6. The aircraft vertical take-off and landing lift device of claim 5, wherein the side wall of the circular truncated cone shaped member is provided with a notch, the notch is a side nozzle of the airflow, and part of the airflow is ejected towards the side through the side nozzle;
the side nozzle is provided with a guide plate, and the guide plate can cover the whole side nozzle; the opening angle of the guide plate is controlled, so that the size and the direction of side jet flow are adjusted, the jet direction of the air flow is changed to generate torque in the direction opposite to the driving torque, and the driving torque is balanced to keep the torque balance of the whole lift device.
7. The aircraft VTOL lift device of claim 6, wherein the truncated cone shaped element is provided with two symmetrical notches; the opening angle of the guide plate on each notch can be independently controlled.
8. The aircraft VTOL lift device of claim 6, wherein the guide plate is a plate-like member, one side of which is rotatably connected with one side of the side nozzle, and the other side of which is a free end rotatable around one side of the plate-like member.
9. A dish-shaped sightseeing vehicle comprising the aircraft VTOL lift device of any one of claims 1-8;
the sightseeing cabin is used for accommodating passengers and is arranged below the supporting component of the lift device;
the mechanical cabin is arranged below the sightseeing cabin and is used for installing a power device of the lift force device and storing required materials;
and the undercarriage is arranged at the bottom of the mechanical cabin.
10. A fixed wing aircraft comprising the aircraft VTOL lift device of any of claims 1-8; the left wing, the right wing, the left horizontal tail wing and the right horizontal tail wing of the body are all provided with the lift force device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110303884.8A CN112829925A (en) | 2021-03-22 | 2021-03-22 | Lift device for vertical take-off and landing of aircraft, aircraft and fixed-wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110303884.8A CN112829925A (en) | 2021-03-22 | 2021-03-22 | Lift device for vertical take-off and landing of aircraft, aircraft and fixed-wing aircraft |
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| Publication Number | Publication Date |
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| CN112829925A true CN112829925A (en) | 2021-05-25 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110303884.8A Withdrawn CN112829925A (en) | 2021-03-22 | 2021-03-22 | Lift device for vertical take-off and landing of aircraft, aircraft and fixed-wing aircraft |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113581462A (en) * | 2021-07-21 | 2021-11-02 | 杨金才 | Butterfly aircraft |
| CN113716036A (en) * | 2021-09-07 | 2021-11-30 | 西北工业大学 | Lifting/pushing integrated power system of fixed-wing vertical take-off and landing aircraft and control method |
| CN113942638A (en) * | 2021-08-11 | 2022-01-18 | 星逻人工智能技术(上海)有限公司 | Ducted unmanned aerial vehicle achieving steering through louver and control method |
| CN114735218A (en) * | 2022-04-12 | 2022-07-12 | 江苏信博建设项目管理有限公司 | Three-dimensional topography mapping device based on unmanned aerial vehicle |
-
2021
- 2021-03-22 CN CN202110303884.8A patent/CN112829925A/en not_active Withdrawn
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113581462A (en) * | 2021-07-21 | 2021-11-02 | 杨金才 | Butterfly aircraft |
| CN113942638A (en) * | 2021-08-11 | 2022-01-18 | 星逻人工智能技术(上海)有限公司 | Ducted unmanned aerial vehicle achieving steering through louver and control method |
| CN113942638B (en) * | 2021-08-11 | 2024-04-09 | 星逻人工智能技术(上海)有限公司 | Ducted unmanned aerial vehicle for realizing steering by utilizing transom and control method |
| CN113716036A (en) * | 2021-09-07 | 2021-11-30 | 西北工业大学 | Lifting/pushing integrated power system of fixed-wing vertical take-off and landing aircraft and control method |
| CN113716036B (en) * | 2021-09-07 | 2023-11-14 | 西北工业大学 | Lifting/pushing integrated power system of fixed wing vertical take-off and landing aircraft and control method |
| CN114735218A (en) * | 2022-04-12 | 2022-07-12 | 江苏信博建设项目管理有限公司 | Three-dimensional topography mapping device based on unmanned aerial vehicle |
| CN114735218B (en) * | 2022-04-12 | 2023-04-14 | 江苏信博建设项目管理有限公司 | Three-dimensional topography mapping device based on unmanned aerial vehicle |
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Application publication date: 20210525 |