CN109018342B - Cycloidal fan wing device, cycloidal fan wing tilting aircraft and control method - Google Patents
Cycloidal fan wing device, cycloidal fan wing tilting aircraft and control method Download PDFInfo
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- CN109018342B CN109018342B CN201810973022.4A CN201810973022A CN109018342B CN 109018342 B CN109018342 B CN 109018342B CN 201810973022 A CN201810973022 A CN 201810973022A CN 109018342 B CN109018342 B CN 109018342B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/36—Structures adapted to reduce effects of aerodynamic or other external heating
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/385—Variable incidence wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/10—All-wing aircraft
- B64C2039/105—All-wing aircraft of blended wing body type
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Abstract
The invention provides a tilting cycloidal fan blade device, a tilting cycloidal fan blade aircraft and a control method thereof. The present invention combines the advantages of both cross flow fan blades and cycloidal paddles. The fan blade in the present invention is also a cycloidal paddle blade that can be operated in a crossflow fan blade mode in a fan blade when the aircraft is flown forward by the steering mechanism and in a cycloidal paddle blade mode when the aircraft is hovered. Compared with the traditional crossflow fan wing aircraft, the front-flying fan blade is adjustable, can adapt to different flight conditions, has the capability of vertical take-off and landing and hovering, and has the advantages of high front-flying efficiency, heavy load and the like compared with the conventional cycloidal propeller (rolling wing) aircraft. The tilting fan wing aircraft is designed to be in a tilting four-wing mode, so that the contradiction between the hovering performance and the forward flying performance is overcome.
Description
Technical Field
The invention relates to the field of aircraft design, mechanical control systems and lift wings, in particular to a tilting cycloidal fan wing aircraft.
Background
The crossflow fan wing is a new type of device for generating aerodynamic lift, it uses the front rotary fan of wing profile to generate vortex lift and thrust to fly, and has the advantages of good low-speed performance, large load and large attack angle. The fan wing generates lift consisting of two parts: when the fan rotates, the flow velocity of the upper surface and the lower surface of the rear half part of the wing is different, so that the pressure difference of the upper surface and the lower surface of the wing is caused, and the lift force of the wing is formed; and the other part is that when the fan rotates, a strong eccentric vortex is generated in the fan, so that a strong eccentric vortex low-pressure area is formed, the upper surface and the lower surface of the arc-shaped area of the front half part of the wing generate a large pressure difference, and a larger part of wing lift force, namely the vortex force, is formed. The fan wing aircraft is in a research and starting stage soon after coming out, and the latest research results and project progress thereof about the fan wings are published at home and abroad.
The current tilting aircraft generally adopts the mode of tilting rotor, installs a pair of rotor promptly at the tip of wing, and during taking off, the rotor is on ground level, and the rotor rotation produces lift, and during the front flight, the rotor is tilted gradually until the level, and thrust is produced by the rotor, and the wing produces lift. Meanwhile, a general tilting aircraft adopts a transverse arrangement for tilting two rotors. Due to the fact that the pure rotor wings are adopted as lift force and thrust devices, and the rotor wings have different performances in hovering and forward flying, the general tilting aircraft is required to be in balance between hovering and forward flying performances, the hovering performance and the smooth flying performance of the aircraft are low, and efficiency is reduced. Currently, a tilting double-rotor mode is adopted, so that the aircraft is limited in voyage and endurance as well as load capacity.
Disclosure of Invention
Aiming at the technical problems, the invention provides a novel tilting cycloidal fan wing aircraft which simultaneously meets the requirements of vertical take-off and landing, hovering and high-altitude cruising and the working principle thereof, combines the advantages of a cross flow fan wing and a cycloidal propeller, designs the tilting aircraft into a tilting four-wing mode, overcomes the contradiction between hovering performance and front flying performance, and improves the hovering performance, flat flying performance, voyage endurance and load.
The invention provides a tilting cycloidal fan wing device, which comprises a cross flow fan wing 5 and a cycloidal paddle operating mechanism, wherein the cycloidal paddle structure is arranged at the front end of the cross flow fan wing 5, one end of the cycloidal paddle structure is fixed on an aircraft body, and the other end of the cycloidal paddle structure is connected with the front edge of a contractible fan wing on the cross flow fan wing; the cycloidal propeller structure controls the angle of the blades of the cycloidal propeller 1 through an operating mechanism formed by a steering engine, a steering engine connecting rod and a tilting device, so that the hovering or forward flying of the aircraft is controlled.
Further, the cycloidal propeller structure comprises a cycloidal propeller rotating part, wherein the cycloidal propeller rotating part comprises a cycloidal propeller fixing plate 2, cycloidal propellers 1 and a transmission shaft 3; the cycloidal propeller fixing plates 2 are positioned at two ends of the cycloidal propeller 1 and used for fixing the cycloidal propeller 1; the cycloidal propeller rotating component comprises a plurality of cycloidal propellers 1, wherein the cycloidal propellers 1 are circumferentially fixed on a cycloidal propeller fixing plate 2 at equal angles; the transmission shaft 3 penetrates through the center of the cycloidal propeller, and power is transmitted to the cycloidal propeller 1 through the cycloidal propeller fixing plate 2, so that the cycloidal propeller 1 rotates around the transmission shaft 3.
Further, the operating mechanism comprises a connecting plate 12, a tilting device 14, a tilting device connecting rod, a cycloidal paddle connecting rod, an L-shaped rod, a steering engine connecting rod and a steering engine fixing device, one end of the transmission shaft 3 protrudes out of the cycloidal paddle fixing plate 2, the connecting plate 12 is fixed at the end part of the transmission shaft protruding out of one end of the cycloidal paddle fixing plate 2, and the transmission shaft 3 is connected with the steering engine fixing device; the steering mechanism comprises a plurality of steering gears, the steering gears are uniformly distributed on the transmission shaft through steering gear fixing devices, and each steering gear is connected to the inclinator 14 through steering gear connecting rods; the recliner 14 controls the movement of the cycloidal propeller links through the cooperative movement of the recliner links with the L-shaped bar, thereby controlling the variation of the installation angle of each cycloidal propeller.
Further, the crossflow fan wing 5 includes a retractable leading edge 18, a cycloidal propeller 1, and a cycloidal propeller steering mechanism, which are devices for generating lift when the aircraft flies forward.
Preferably, the cycloidal propeller rotating part consists of eight cycloidal propeller blades; the eight cycloidal propeller blades are circumferentially arranged at equal angles.
Further, three identical steering engines are arranged in the cycloidal propeller control mechanism to provide control force, and the automatic inclinator 14 is used for respectively controlling the total pitch and the periodic pitch changing operation of eight cycloidal propeller blades.
The invention also provides a tilting cycloidal fan wing aircraft adopting the double-number fan wings, wherein four tilting cycloidal fan wing devices are arranged on the aircraft, are symmetrically arranged on two sides of the aircraft, and are in a form that a cycloidal paddle structure is behind a front cross flow fan wing; when the aircraft flies vertically, the wing 5 of the cross flow fan tilts to be close to the ground, the blades work in a cycloidal paddle mode, and the aircraft generates upward lifting force; when the aircraft is flown horizontally, the cross flow fan wing 5 is tilted parallel to the ground, the blades operate in a cross flow fan mode, and the aircraft generates forward thrust.
The invention also provides a control method of the tilting cycloidal fan wing aircraft, which is characterized in that the control method controls the posture of the tilting device through the steering engine, and then the tilting device drives the several stages of connecting rods to convert the posture change into the inclination angle change of cycloidal propeller blades, and the tilting of the cross-flow fan wing is matched to control the flight mode of the aircraft;
when the inclinator performs periodic pitch-changing operation, the periodic pitch-changing of the blades works in a cycloidal propeller mode; the size and direction of aerodynamic force of the cycloidal propeller can be adjusted by changing the periodical pitch-changing control direction.
When the total distance adjustment operation is performed on the inclinator without periodic distance change, the angles of all blades are the same, and the inclinator works in a cross flow fan mode at the moment; the size of the total distance is changed, and the angle of the cross flow fan blade is adjusted to adjust the aerodynamic force or adapt to different flight conditions, so that higher aerodynamic efficiency can be maintained.
The invention has the beneficial effects that:
1. the tilting cycloidal fan wing aircraft overcomes the defect that the conventional fan wing aircraft cannot take off and land vertically and hover in the air, and expands the application range of the aircraft.
2. When the aircraft flies forwards, the angle of the cross flow fan blades on the fan wings can be adjusted, and the aerodynamic force can be changed or the aircraft can adapt to different flight conditions, so that higher forward flying aerodynamic efficiency can be kept.
3. The fan wings and the cycloidal propeller are effectively combined, so that the aircraft has higher hovering and forward flying efficiency and excellent comprehensive performance.
4. The design of tilting four wings overcomes the contradiction between hovering and forward flying, and effectively improves hovering efficiency and forward flying performance. And has great improvement in the aspects of load capacity and voyage and endurance.
The tilting cycloidal fan wing aircraft can be used for aerial operations such as aerial photography and geological exploration, and can be used for investigation tasks such as fire investigation, ground target positioning and submarine searching. The tilting cycloidal fan wing aircraft disclosed by the invention has the characteristics of a helicopter and a fixed wing aircraft, so that the tilting cycloidal fan wing aircraft has a greater advantage compared with a traditional unmanned aerial vehicle in task execution capacity.
Drawings
Fig. 1 is a schematic diagram of the overall structure of a cycloidal propeller and cycloidal propeller operating mechanism.
Fig. 2 is a schematic diagram of a tilting cycloidal fan wing aircraft.
Fig. 3 is a left side view of the cycloidal propeller steering mechanism.
Fig. 4 is a right side view of the cycloidal propeller steering mechanism.
Fig. 5 is a schematic diagram of a tilting cycloidal fan wing aircraft hovering/vertical flight condition.
Fig. 6 is a schematic diagram of a tilting cycloidal fan wing aircraft in a horizontal flight condition.
Fig. 7 is a tilting cycloidal fan wing aircraft hover/vertical flight opportunity wing condition.
Fig. 8 shows the wing of the tilting cycloidal fan wing aircraft in a forward flight.
Fig. 9 is a schematic diagram of air flow near a wing of a tilting cycloidal fan wing aircraft hovering/vertical flight opportunity.
Fig. 10 is a schematic diagram of air flow near the wing of a tilting cycloidal fan wing aircraft during forward flight.
In the figure, a cycloidal propeller 1, a cycloidal propeller fixing plate 2, a transmission shaft 3, a fuselage 4, a crossflow fan wing 5, a cycloidal propeller connecting rod 6, an L-shaped rod 7, a recliner connecting rod 8, a steering engine 9, a steering engine fixing plate 10, a steering engine 11, a connecting plate 12, a steering engine 13, a recliner 14, a connecting rod 15, a steering engine fixing plate 16, a blade rib 17, a retractable fan wing front edge 18, a vertical fin 19, a rudder 20, a fan wing front edge retracting mechanism gear 21 and a fan wing front edge retracting mechanism rack 22.
Detailed Description
The invention is further described below with reference to the drawings and the detailed description.
The cycloidal propeller is a novel device for generating aerodynamic lift force, the blades revolve around the cycloidal propeller rotating shaft and do pitching oscillation motion around the hinge, lift force is provided by periodically changing the attack angles of the blades at different positions in the rotating blade system, the net vector pulling force direction is changed by changing the phase angle of the periodic pitch variation of the blades, and due to the unsteady flow characteristic caused by the periodic rotation of the cycloidal propeller, the stall attack angle of the blades is increased, so that the cycloidal propeller has the characteristics of high efficiency, low noise, rapid vector thrust change and the like.
Example 1
As shown in fig. 1 to 4, the present invention provides a tilting cycloidal fan wing device, comprising a cycloidal propeller 1 and a cross-flow fan wing 5 connected by an operating mechanism, wherein the cycloidal fan wing structure mainly comprises a cycloidal propeller operating mechanism, a cycloidal propeller rotating part and the cross-flow fan wing 5. Combines the advantages of both the crossflow fan blade and the cycloidal propeller.
The cycloidal propeller rotating part is characterized in that eight or more cycloidal propellers 1 with the same angle are circumferentially fixed through the cycloidal propeller fixing plate 2, and power is transmitted to the cycloidal propellers 1 through the cycloidal propeller fixing plate 2 by the transmission shaft 3, so that the eight cycloidal propellers 1 rotate around the transmission shaft 3.
The cycloidal propeller operating mechanism is characterized in that the transmission shaft 3 is connected with the steering engine fixing plate 10 through the connecting plate 12, the steering engine 9, the steering engine 13 and the steering engine 11 are fixed through the steering engine fixing plate 10 and the steering engine fixing plate 16, the steering engine 13 controls the tilting device 14 to move through the steering engine connecting rod 15, the tilting device 14 controls the cycloidal propeller connecting rod 6 to move through the matching movement of the tilting device connecting rod 8 and the L-shaped rod 7, so that the attack angle change of cycloidal propellers is controlled, and the steering engine 9 and the steering engine 11 respectively control the tilting device 14 and the cycloidal propeller connecting rod to move in the same mode. The cycloidal propeller control mechanism mainly comprises three identical steering engines 9, 11 and 13 for providing control force, and a recliner 14 for controlling eight cycloidal propellers to perform collective pitch and periodic pitch-changing operation. The cycloidal propeller operating mechanism has a simple structure, and each mechanism has no clamping stagnation, so compared with other existing operating mechanisms, the cycloidal propeller operating mechanism has the advantages of higher operating efficiency, quick response and light weight.
The main function of the cross-flow fan wing 5 is to fix the cycloidal propeller 1 and the cycloidal propeller control mechanism, and also to be an aircraft lift force generating device.
Example 2
Based on the tilting cycloidal fan wing device, as shown in fig. 5 to 8, the invention also provides a tilting cycloidal fan wing aircraft, wherein the tilting cycloidal fan wing devices are symmetrically arranged on two sides of the aircraft in a mode that a cycloidal paddle structure is behind a front cross flow fan wing; when the aircraft flies vertically, the wing 5 of the cross flow fan tilts to be close to the ground, the blades work in a cycloidal paddle mode, and the lifting force generated by the aircraft faces upwards; when the aircraft is flown horizontally, the cross flow fan wing 5 tilts parallel to the ground, the blades operate in a cross flow fan mode, and forward thrust is generated by the aircraft.
The control method comprises the steps of controlling the posture of the inclinator through a steering engine, driving a plurality of stages of connecting rods through the inclinator to convert the change of the posture of the inclinator into the inclination angle of cycloidal propeller blades, and controlling the flight mode of the aircraft in cooperation with the inclination of the wings of the cross flow fans;
when the inclinator performs periodic pitch-changing operation, the periodic pitch-changing of the blades works in a cycloidal propeller mode; the size and direction of aerodynamic force of the cycloidal propeller can be adjusted by changing the periodical pitch-changing control direction.
When the total distance adjustment operation is performed on the inclinator without periodic distance change, the angles of all blades are the same, and the inclinator works in a cross flow fan mode at the moment; the angle of the cross flow fan blade can be adjusted by changing the total distance so as to adjust the aerodynamic force or adapt to different flight conditions, so that higher aerodynamic efficiency can be maintained.
The cross flow fan wing 5 can tilt; the crossflow fan wing leading edge rounded portion 18 is able to retract inside the wing 5 to reduce aerodynamic interference with the cycloidal paddles when the aircraft is hovering. The tilting fan wing aircraft can realize hovering, vertical flight and horizontal flight.
The wing tilting mechanism can adopt the scheme in the patent CN 105799934A.
Example 3
The invention also provides a control method of the tilting cycloidal fan wing aircraft, which is characterized in that the control method controls the posture of the tilting device through the steering engine, and then the tilting device drives the several stages of connecting rods to convert the posture change into the inclination angle change of cycloidal propeller blades, and the tilting of the cross-flow fan wing is matched to control the flight mode of the aircraft;
when the inclinator performs periodic pitch-changing operation, the periodic pitch-changing of the blades works in a cycloidal propeller mode; the size and direction of aerodynamic force of the cycloidal propeller can be adjusted by changing the periodical pitch-changing control direction.
When the total distance adjustment operation is performed on the inclinator without periodic distance change, the angles of all blades are the same, and the inclinator works in a cross flow fan mode at the moment; the size of the total distance is changed, and the angle of the cross flow fan blade is adjusted to adjust the aerodynamic force or adapt to different flight conditions, so that higher aerodynamic efficiency can be maintained.
FIG. 9 is a schematic representation of airflow near a tilting cycloidal fan wing aircraft hover/vertical flight opportunity wing while exercising control over the aircraft; fig. 10 is a schematic diagram of air flow near the wing of a tilting cycloidal fan wing aircraft during forward flight.
The tilting cycloidal fan wing aircraft overcomes the defect that the conventional fan wing aircraft cannot take off and land vertically and hover in the air, and expands the application range of the aircraft. When the aircraft flies forwards, the angle of the cross flow fan blades on the fan wings can be adjusted, and the aerodynamic force can be changed or the aircraft can adapt to different flight conditions, so that higher forward flying aerodynamic efficiency can be kept. The fan wings and the cycloidal propeller are effectively combined, so that the aircraft has higher hovering and forward flying efficiency and excellent comprehensive performance. The design of tilting four wings overcomes the contradiction between hovering and forward flying, and effectively improves hovering efficiency and forward flying performance. And has great improvement in the aspects of load capacity and voyage and endurance.
The tilting cycloidal fan wing aircraft can be used for aerial operations such as aerial photography and geological exploration, and can be used for investigation tasks such as fire investigation, ground target positioning and submarine searching. The tilting cycloidal fan wing aircraft disclosed by the invention has the characteristics of a helicopter and a fixed wing aircraft, so that the tilting cycloidal fan wing aircraft has a greater advantage compared with a traditional unmanned aerial vehicle in task execution capacity.
The present invention has been described in terms of the preferred embodiments thereof, and it should be understood by those skilled in the art that various modifications can be made without departing from the principles of the invention, and such modifications should also be considered as being within the scope of the invention.
Claims (6)
1. A tiltable cycloidal fan wing apparatus characterized by: the device comprises a cross flow fan wing (5) and a cycloidal propeller control mechanism, wherein the cycloidal propeller control mechanism is arranged at the front end of the cross flow fan wing (5), one end of the cycloidal propeller control mechanism is fixed on an aircraft body, and the other end of the cycloidal propeller control mechanism is connected with the front edge of a retractable fan wing on the cross flow fan wing; the cycloidal propeller control mechanism controls the angle of the blades of the cycloidal propeller (1) through a control mechanism formed by a steering engine, a steering engine connecting rod and a tilting device, so as to control the hovering or forward flying of the aircraft;
the structure of the cycloidal propeller (1) comprises a cycloidal propeller rotating part, wherein the cycloidal propeller rotating part comprises a cycloidal propeller fixing plate (2), cycloidal propeller blades and a transmission shaft (3); the cycloidal propeller fixing plates (2) are positioned at two ends of the cycloidal propeller blades and used for fixing the cycloidal propeller blades; the cycloidal propeller rotating part comprises a plurality of cycloidal propeller blades, and the cycloidal propeller blades are circumferentially fixed on a cycloidal propeller fixing plate (2) at equal angles; the transmission shaft (3) penetrates through the center of the cycloidal propeller, power is transmitted to the cycloidal propeller blades through the cycloidal propeller fixing plate (2), and the cycloidal propeller blades rotate around the transmission shaft (3);
the control mechanism comprises a connecting plate (12), a tilting device (14), a tilting device connecting rod, a cycloidal propeller connecting rod, an L-shaped rod, a steering engine connecting rod and a steering engine fixing device, one end of a transmission shaft (3) protrudes out of the cycloidal propeller fixing plate (2), the connecting plate (12) is fixed at the end part of the transmission shaft protruding out of one end of the cycloidal propeller fixing plate (2), and the transmission shaft (3) is connected with the steering engine fixing device; the steering mechanism comprises a plurality of steering gears, the steering gears are uniformly distributed on the transmission shaft through steering gear fixing devices, and each steering gear is connected to the inclinator (14) through steering gear connecting rods; the inclinator (14) controls the movement of the cycloidal propeller connecting rod through the cooperation movement of the inclinator connecting rod and the L-shaped rod, so as to control the change of the installation angle of each cycloidal propeller;
the crossflow fan wing (5) comprises a retractable fan wing front edge (18), cycloidal paddles (1) and a cycloidal paddle control mechanism, is a device for generating lifting force when an aircraft flies forward, and is characterized in that a servo motor drives two gears (21) to drive racks (22) on the fan wing front edge (18) meshed with the gears to realize the retraction and control of the fan wing front edge.
2. The tiltable cycloidal fan wing apparatus of claim 1 wherein: the cycloidal propeller rotating part consists of eight cycloidal propeller blades; the eight cycloidal propeller blades are circumferentially arranged at equal angles.
3. The tiltable cycloidal fan wing apparatus of claim 2 wherein: three identical steering engines are arranged in the cycloidal propeller control mechanism to provide control force, and an automatic inclinator (14) is used for respectively controlling the total pitch and the periodic pitch-changing operation of eight cycloidal propeller blades.
4. The tilting cycloidal fan wing aircraft is characterized in that four tilting cycloidal fan wing devices as claimed in claim 3 are arranged on the aircraft, are symmetrically arranged on two sides of the aircraft, and are in a mode that cycloidal paddles are arranged behind a front cross flow fan wing; when the aircraft flies vertically, the wing (5) of the cross flow fan tilts to be close to the ground, the blades work in a cycloidal propeller mode, and the aircraft generates upward lifting force; when the aircraft is flown horizontally, the cross flow fan wings (5) are tilted parallel to the ground, the blades operate in a cross flow fan mode, and the aircraft generates forward thrust.
5. The control method of a tilting cycloidal fan wing aircraft according to claim 4, wherein: the control method comprises the steps of controlling the posture of the inclinator through a steering engine, driving a plurality of stages of connecting rods through the inclinator to convert the posture change into the inclination angle change of cycloidal propeller blades, and controlling the flight mode of the aircraft in cooperation with the inclination of the wings of the cross flow fan;
when the inclinator performs periodic pitch-changing operation, the periodic pitch-changing of the blades works in a cycloidal propeller mode; the size and direction of aerodynamic force of the cycloidal propeller can be adjusted by changing the periodical pitch-changing control direction.
6. The control method according to claim 5, characterized in that: when the total distance adjustment operation is performed on the inclinator without periodic distance change, the angles of all blades are the same, and the inclinator works in a cross flow fan mode at the moment; the size of the total distance is changed, and the angle of the cross flow fan blade is adjusted to adjust the aerodynamic force or adapt to different flight conditions, so that higher aerodynamic efficiency can be maintained.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810973022.4A CN109018342B (en) | 2018-08-24 | 2018-08-24 | Cycloidal fan wing device, cycloidal fan wing tilting aircraft and control method |
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| CN201810973022.4A CN109018342B (en) | 2018-08-24 | 2018-08-24 | Cycloidal fan wing device, cycloidal fan wing tilting aircraft and control method |
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| CN109018342A CN109018342A (en) | 2018-12-18 |
| CN109018342B true CN109018342B (en) | 2024-02-20 |
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| CN109649638A (en) * | 2019-01-02 | 2019-04-19 | 南京航空航天大学 | It is coaxial to turn double cycloid paddle together |
| CN110254711B (en) * | 2019-07-19 | 2021-01-08 | 苏州高博软件技术职业学院 | Two-horizontal four-vertical blade rotatable six-wheel type rotor unmanned aerial vehicle |
| CN111521365B (en) * | 2020-05-18 | 2021-06-08 | 南京航空航天大学 | Adjustable frequency and phase unsteady flow control experimental device based on rotary slot grating |
| WO2023021054A1 (en) * | 2021-08-17 | 2023-02-23 | Noraero As | A compact safe efficient multi-rotor evtol airborne craft |
| CN116238689B (en) * | 2023-05-12 | 2023-09-29 | 南京航空航天大学 | Perpendicular take-off and landing span medium aircraft based on propulsion wings and control system thereof |
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| CN207510704U (en) * | 2017-08-16 | 2018-06-19 | 莆田市双普信息科技有限公司 | A kind of cycloid propeller and propeller combination push structure |
| CN207510714U (en) * | 2017-08-16 | 2018-06-19 | 莆田市双普信息科技有限公司 | A kind of cycloid propeller propulsive mechanism using arc blade |
| CN108163195A (en) * | 2018-01-08 | 2018-06-15 | 南京航空航天大学 | A kind of four axis rolling rotor aircraft |
| CN209274896U (en) * | 2018-08-24 | 2019-08-20 | 南京航空航天大学 | One kind vert cycloid fan swing device, vert cycloid fan rotor aircraft |
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