A single duct aircraft

Abstract

The application discloses a single duct aircraft, which comprises a ring-shaped duct, a propeller and a propeller driving motor, the axis of the duct is vertically arranged, the propeller driving motor is a shaftless motor, the stator of the shaftless motor is fixed on the inner wall of the duct, and a plurality of blades of the propeller are fixed on the annular rotor of the shaftless motor. The propeller of the application is installed on the annular rotor of the shaftless motor, so that a support does not need to be installed in the duct, the internal resistance of the duct is small, the power of the duct aircraft is large, and the efficiency is high.

Description

[Technical Field]

[0001] This invention relates to ducted aircraft, and more particularly to a single-ducted aircraft. [Background Technology]

[0002] Ductless fan aircraft possess advantages such as compact structure, good maneuverability, and strong environmental adaptability, and their application scope has expanded to three major fields: military, civilian, and scientific research. Due to their increasingly promising development prospects, they have gradually attracted the attention of researchers. The structure of a ducted fan UAV includes: a ring wing (ducted fan), a propeller disk, a tail rudder, and a fuselage. Among these, the ring wing and the fan play crucial roles in the forward flight of the ducted fan UAV, providing the entire aircraft's flight propulsion. When a ring-wing UAV takes off from the vertical plane, the reaction force of the propeller against the air and the additional thrust of the ring wing work together; yaw, pitch, and roll during the forward flight of the ducted fan aircraft are achieved by the action of control surfaces.

[0003] A single-ducted jet aircraft is an independent aircraft that can fly independently.

[0004] Application number CN202011461817.0 discloses a deployable single-ducted aircraft, belonging to the field of aircraft design. The deployable single-ducted aircraft includes a ring-shaped duct, a propeller, and an equipment compartment. The ring-shaped duct includes a main duct wall, a deployable duct wall A, and a deployable duct wall B, which are connected by a rotary actuator and a hinge. The propeller and equipment compartment are both mounted on the central axis of the duct. The propeller provides forward thrust. A cruciform tail fin is fixed between the equipment compartment and the main duct wall, deployable duct wall A, and deployable duct wall B. In fixed-wing mode, deployable duct walls A and B deploy and are mechanically locked to the main duct wall. In ducted mode, the cruciform tail fin is mechanically locked to deployable duct walls A and B. The propeller in this invention is mounted on the central axis, which requires support brackets, increasing airflow disturbance and drag within the duct, thus reducing the efficiency and power of the single-ducted aircraft. [Summary of the Invention]

[0005] The technical problem to be solved by the present invention is to provide a single-ducted aircraft with low air resistance and high efficiency.

[0006] To solve the above-mentioned technical problems, the technical solution adopted by the present invention is a single-ducted aircraft, including an annular duct, a propeller and a propeller drive motor. The axis of the duct is arranged vertically. The propeller drive motor is a shaftless motor. The stator of the shaftless motor is fixed on the inner wall of the duct, and a plurality of blades of the propeller are fixed on the annular rotor of the shaftless motor.

[0007] In the single-ducted aircraft described above, the outer radial end of the propeller blade is fixed to the annular rotor of the shaftless motor, and the inner end is cantilevered; the inner wall of the duct includes an annular groove, the stator of the shaftless motor is embedded in the annular groove, and the rotor of the shaftless motor is mounted in the stator through bearings.

[0008] The single-ducted duct aircraft described above includes landing gear and a plurality of mounting boxes for installing batteries and control circuits. The landing gear is fixed to the lower part of the duct and includes multiple outriggers, which are arranged separately along the circumference of the duct. The mounting boxes are fixed to the top of the landing gear and are symmetrical about the axis of the duct. The longitudinal section of the duct wall adopts a NACA airfoil, with the leading edge of the NACA airfoil facing upward, and the diameter of the duct at the leading edge is larger than the diameter of the duct at the trailing edge.

[0009] The single-duct aircraft described above includes four dual-jet actuators, which are distributed at the bottom of the duct and evenly distributed along the circumference of the duct; the two nozzles of the dual-jet actuators face downwards.

[0010] The single-duct aircraft described above has four grooves with inner and lower openings on the bottom of the duct inner wall, and the dual-jet exciter is embedded in the groove at the bottom of the duct inner wall.

[0011] The single-ducted aircraft described above, with its dual-jet exciter, includes an open shell, a cover plate, a jet adjustment plate, and a servo motor. The shell has a diaphragm in its middle, which divides the inner cavity of the shell into two open mouths. The cover plate covers the opening of the inner cavity of the shell, and the middle of the cover plate includes the jet nozzle. The jet nozzle communicates with the two open mouths. The jet adjustment plate is installed in the jet nozzle and is driven to rotate by the servo motor installed on the cover plate. The rotation axis of the jet adjustment plate is orthogonal to the plane of the diaphragm.

[0012] In the single-ducted duct aircraft described above, the diaphragm has a piezoelectric ceramic sheet in the center and a copper sheet around the perimeter.

[0013] In the single-duct aircraft described above, when the dual jet exciter is installed at the bottom of the duct, the rotation axis of the jet adjustment plate is arranged radially along the duct, and the plane where the vibrating diaphragm is located is arranged tangentially along the circumference of the duct.

[0014] The single-ducted jet aircraft described above adjusts the output of the dual-jet exciter by selectively controlling the frequency and amplitude of the vibration of the diaphragm of different dual-jet exciter; and adjusts the jet ejection direction of the dual-jet exciter by selectively controlling the angle of the jet adjustment plate of different dual-jet exciter, thereby changing the direction of the airflow generated by the propeller and causing it to deviate from the mainstream, thus changing the attitude angle and flight dynamics of the single-ducted jet aircraft.

[0015] The single-ducted jet aircraft described above can increase its lift by controlling the airflow of the synthetic jet exciter to concentrate towards the center of the aircraft, which can be combined with the propeller; and by controlling the airflow of the synthetic jet exciter to disperse outward, it can slow down the descent speed of the single-ducted jet aircraft.

[0016] The propeller of this invention is mounted on the annular rotor of a shaftless motor. No support is needed inside the duct, resulting in low resistance inside the duct and high power and efficiency of the ducted aircraft. [Image Description]

[0017] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments.

[0018] Figure 1 This is a front view of a single-ducted jet aircraft according to an embodiment of the present invention.

[0019] Figure 2 This is a top view of a single-ducted jet aircraft according to an embodiment of the present invention.

[0020] Figure 3 yes Figure 1 AA section view in the image.

[0021] Figure 4 This is a perspective view of a single-ducted jet aircraft according to an embodiment of the present invention.

[0022] Figure 5 This is a front view of the dual-jet exciter according to an embodiment of the present invention.

[0023] Figure 6 This is a top view of the dual-jet exciter according to an embodiment of the present invention.

[0024] Figure 7 This is a left view of the dual-jet exciter according to an embodiment of the present invention.

[0025] Figure 8 yes Figure 5 BB section view in the middle.

[0026] Figure 9 yes Figure 7 CC section view in the image.

[0027] Figure 10 This is a perspective view of the dual-jet exciter according to an embodiment of the present invention. [Detailed Implementation]

[0028] The structure of the single-ducted 10-type aircraft in this embodiment of the invention is as follows: Figures 1 to 10 As shown, it includes an annular duct 10, a propeller 20, a propeller 20 drive motor, a landing gear 40, and four dual-jet exciters 50.

[0029] The duct 10 has a vertically arranged axis, and the propeller 20 is driven by a shaftless motor 30. The inner wall of the duct 10 has an annular groove 11, in which the stator 31 of the shaftless motor 30 is embedded, and the rotor 32 of the shaftless motor 30 is mounted in the stator 31 through a bearing 33.

[0030] The multiple blades of the propeller 20 are fixed on the annular rotor 32 of the shaftless motor 30.

[0031] The outer ends of the three blades 21 of the propeller 20 are fixed radially to the annular rotor 32 of the shaftless motor 30, and the inner ends of the three blades 21 of the propeller 20 are cantilevered.

[0032] The longitudinal section of the sidewall of duct 10 adopts the NACA4418 airfoil. The leading edge 12 of the NACA4418 airfoil faces upward, and the diameter D1 of duct 10 at the leading edge 12 is larger than the diameter D2 of duct 10 at the trailing edge 13.

[0033] The landing gear 40 is fixed to the lower part of the outer periphery of the duct 10 and includes four outriggers 41, which are evenly distributed along the circumference of the duct 10.

[0034] Four mounting boxes 42 for installing batteries and control circuits are fixed to the top of the landing gear 40. Similarly, the four mounting boxes 42 for batteries and control circuits are also evenly distributed along the circumference of the duct 10 and arranged symmetrically with respect to the axis of the duct 10, which can maintain the balance of the aircraft.

[0035] Four dual-jet exciters 50 are distributed at the bottom of the duct 10, with their nozzles 521 facing downwards. These four dual-jet exciters 50 control the yaw, pitch, and roll of the single-ducted aircraft during forward flight. Simultaneously, utilizing the rectifying effect of the combined dual-jet exciters, the torque generated by the propeller itself is dynamically offset according to its attitude angle, preventing the single-ducted aircraft from spinning during flight.

[0036] like Figure 3 As shown, the bottom of the inner wall of the duct 10 has four grooves 14 with inner and lower openings. Four dual-jet exciters 50 are embedded in the grooves 14 at the bottom of the inner wall of the duct 10 and are evenly distributed along the circumference of the duct 10.

[0037] The dual-jet actuator 50 includes an open housing 51, a cover plate 52, a diaphragm 53, a jet adjustment plate 54, and two servo motors 55. The diaphragm 53 is sandwiched between two halves of the housing 51, dividing the inner cavity of the housing 51 into two open mouths 511. The cover plate 52 covers the opening of the inner cavity of the housing 51, and has a jet port 521 in the middle. The jet port 521 communicates with the inner cavity of the housing 51, i.e., the two open mouths 511.

[0038] The jet adjustment plate 54 is installed in the injection port 521 and is driven to rotate by two servo motors 55 installed in the cover plate 52. The rotation axis of the jet adjustment plate 54 is orthogonal to the plane where the vibrating diaphragm 53 is located. The servo motors 55 drive the jet adjustment plate 54 to rotate, which can adjust the flow rate and angle of the jet of the dual jet exciter 50.

[0039] When the dual jet exciter 50 is installed at the bottom of the duct, the rotation axis of the jet adjustment plate 54 is arranged radially along the duct 10, and the plane where the vibrating diaphragm 53 is located is arranged tangentially along the circumference of the duct 10.

[0040] The vibrating diaphragm 53 has a piezoelectric ceramic sheet 531 in the center and a copper sheet 532 around the periphery. The vibrating diaphragm 53 is composed of piezoelectric ceramic and copper sheet. The jet flow rate of the injection port 521 is controlled by controlling the frequency and amplitude of the vibration of the vibrating diaphragm.

[0041] The above embodiments of the present invention control the frequency and amplitude of the vibration of the diaphragm, and then use the servo motor installed on the top cover to control the angle of the jet adjustment plate through the PID algorithm to adjust the size and direction of the jet of the dual jet exciter 50.

[0042] When the jet trimmer deflects, and the exit areas of the two combined jets at the nozzle are unequal, the combined jet will deflect towards the side with the larger exit area. This change in exit area alters the momentum ratio of the two jets. When the jet from the side with lower momentum is in the blow-off direction, it is almost completely drawn into the other side. When the jet from the side with higher momentum is ejected, it is deflected towards the side with lower momentum due to the influence of the low-pressure area on the other side. This achieves the function of changing the jet direction, using a controllable jet ejected from the nozzle to alter the direction of the airflow generated by the propeller, thus deflecting it towards the main flow.

[0043] When a single-ducted jet aircraft needs to move forward, backward, left, or right in any direction, the airflow in the opposite direction is selectively controlled from each synthetic jet exciter to deflect the main flow, causing the aircraft's attitude angle to change. The aircraft tilts as a whole in the set direction and is simultaneously thrust in that direction, thus moving forward in that direction.

[0044] By controlling the airflow of the synthetic jet exciter to concentrate towards the center of the aircraft, the lift of the single-ducted jet aircraft can be increased in conjunction with the propeller; by controlling the airflow of the synthetic jet exciter to diverge outward, the descent speed of the single-ducted jet aircraft can be reduced, making the landing of the single-ducted jet aircraft more stable.

[0045] The control mechanism of the synthetic dual-jet exciter causing the main flow to deviate is: (1) the pressure gradient caused by the operation of the synthetic dual-jet exciter; (2) the entrainment effect of the synthetic dual-jet exciter and the vortices generated by the operation on the surrounding fluid; (3) the mutual coupling effect between the vortices generated by the operation of the synthetic dual-jet exciter and the free shear layer of the main flow.

[0046] The embodiments of the present invention utilize the rectification effect of the synthetic dual-jet exciter to dynamically cancel out the torque generated by the propeller itself according to its attitude angle, preventing the single-ducted aircraft from rotating during flight. Because it combines a shaftless motor-driven propeller with the synthetic dual-jet exciter, the characteristics of the shaftless propeller make the airflow generated after the propeller rotates more concentrated, thus facilitating the rectification effect of the synthetic dual-jet exciter and resulting in better control.

[0047] The above embodiments of the present invention have the following beneficial effects:

[0048] 1. The shaftless motor drives the propeller, which can provide greater torque, power and efficiency; it can stabilize the propeller at higher speeds, making the single-ducted jet aircraft move more stably.

[0049] 2. The single-ducted jet aircraft uses a synthetic dual-jet exciter instead of rudder blades to control the direction of airflow. During flight, the synthetic dual jet is used to quickly respond to and actively control the direction of flight, making the single-ducted jet aircraft more flexible and versatile, with stronger driving force, while also improving the disadvantage of slow response of rudder blade control.

Claims

1. A single duct aircraft comprising a ring duct, a propeller and a propeller drive motor, the axis of the duct being arranged vertically, characterized in that, The propeller driving motor is a shaftless motor, the stator of the shaftless motor is fixed on the inner wall of the duct, and the plurality of blades of the propeller are fixed on the annular rotor of the shaftless motor; the double jet exciters are dispersedly installed on the bottom of the duct and are uniformly distributed along the circumference of the duct; the jetting port of the double jet exciter faces downward, the double jet exciter comprises an open shell, a cover plate, a jet adjusting piece and a steering engine, the middle part of the shell comprises a diaphragm, the diaphragm separates the inner cavity of the shell into two open cavities, the cover plate covers the opening of the inner cavity of the shell, the middle part of the cover plate comprises the jetting port, the jetting port is in communication with the two open cavities, and the jet adjusting piece is installed in the jetting port and is driven to rotate by the steering engine installed on the cover plate.

2. The single duct aircraft of claim 1, wherein, The outer end of the propeller blade in the radial direction is fixed on the annular rotor of the shaftless motor, and the inner end is cantilevered; the inner wall of the duct comprises an annular groove, the stator of the shaftless motor is embedded in the annular groove, and the rotor of the shaftless motor is installed in the stator through a bearing.

3. The single duct aircraft of claim 1, wherein, The landing gear is fixed on the lower part of the duct and comprises a plurality of legs which are arranged separately along the circumference of the duct; the mounting box is fixed on the top of the landing gear and is symmetrical to the axis of the duct; the longitudinal section of the duct wall adopts a NACA airfoil shape, the leading edge of the NACA airfoil faces upward, and the diameter of the duct at the leading edge is greater than that at the trailing edge.

4. The single duct aircraft of claim 1, wherein, The bottom of the inner wall of the duct comprises four inner side and lower opening grooves, and the double jet exciters are embedded in the grooves at the bottom of the inner wall of the duct.

5. The single duct aircraft of claim 1, wherein, The middle part of the diaphragm is a piezoelectric ceramic piece, and the periphery is a copper piece.

6. The single duct aircraft of claim 5, wherein, When the double jet exciter is installed at the bottom of the duct, the rotary axis of the jet adjusting piece is arranged along the radial direction of the duct, and the plane where the diaphragm is located is arranged along the tangential direction of the circumferential direction of the duct.

7. The single duct aircraft of Claim 1, wherein, By selectively controlling the frequency and amplitude of the vibration of the diaphragm of different double jet exciters, the output of the double jet exciter is adjusted; by selectively controlling the angle of the jet adjusting piece of different double jet exciters, the jet injection direction of the double jet exciter is adjusted, the direction of the airflow generated by the propeller is changed, the main flow is deflected, and the attitude angle and flight power of the single-duct aircraft are changed.

8. The single duct aircraft of claim 7, wherein, Controlling the airflow of the synthetic jet exciter to concentrate on the center of the aircraft can improve the lift of the single-duct aircraft together with the propeller; controlling the airflow of the synthetic jet exciter to diverge outward can slow down the landing speed of the single-duct aircraft.

Images