CN210822751U - Electric ducted fan fixed wing aircraft capable of achieving short-distance/vertical take-off and landing - Google Patents
Electric ducted fan fixed wing aircraft capable of achieving short-distance/vertical take-off and landing Download PDFInfo
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- CN210822751U CN210822751U CN201921490602.4U CN201921490602U CN210822751U CN 210822751 U CN210822751 U CN 210822751U CN 201921490602 U CN201921490602 U CN 201921490602U CN 210822751 U CN210822751 U CN 210822751U
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Abstract
The utility model discloses an electric ducted fan fixed wing aircraft that can take off and land by short distance/VTOL, including fuselage and the wing at the anterior duck wing of fuselage and fuselage rear portion of connection, the both ends of duck wing respectively fixed arrangement have a first electric ducted fan thrust unit, respectively be provided with an actuating mechanism that verts in the fuselage left and right sides wing, every second electric ducted fan thrust unit of actuating mechanism drive that verts, and the mounted position of second electric ducted fan thrust unit is the wing point department that is located the wing both sides and expandes, second electric ducted fan thrust unit can vert under actuating mechanism's the drive of verting between the fuselage direction of perpendicular to aircraft and the aircraft fuselage direction of level. The utility model discloses fuse many rotor crafts and fixed wing aircraft's characteristics, realized the function of fixed wing aircraft short distance/VTOL and the high-speed flight of many rotor crafts.
Description
Technical Field
The utility model relates to an aircraft technical field, concretely relates to but electric duct fan fixed wing aircraft of short distance/VTOL.
Background
The general multi-rotor aircraft adopts integral forward tilting to achieve the purpose of forward flight, has limited speed in a flat flight state, has large speed difference with a fixed-wing aircraft, and cannot achieve the purpose of rapid transportation.
SUMMERY OF THE UTILITY MODEL
Based on the not enough of prior art, the utility model provides an but electric duct fan fixed wing aircraft of short distance/VTOL to satisfy the performance that many rotor crafts high speed was flown horizontally.
The technical scheme of the utility model is that:
the utility model provides an electricity duct fan fixed wing aircraft that can short distance/VTOL, includes the fuselage and connects duck wing and the wing at the fuselage rear portion in the fuselage forepart, and the fuselage is the volume chamber of aircraft for hold necessary relevant equipment and the load of aircraft, duck wing and wing provide necessary lift for the aircraft when horizontal flight, and the both ends of duck wing are each fixed arrangement has an electricity duct fan thrust unit, its characterized in that: the aircraft comprises an aircraft body, and is characterized in that wings on the left side and the right side of the aircraft body are respectively provided with a tilting actuator, each tilting actuator drives a second electric ducted fan thrust device, the mounting position of each second electric ducted fan thrust device is located at the wing tip part expanded on the two sides of each wing, and the second electric ducted fan thrust devices can tilt between the direction perpendicular to the aircraft body and the direction horizontal to the aircraft body under the driving of the tilting actuators.
Furthermore, tilting actuator includes bearing structure and drive structure, bearing structure includes front beam, back beam, banding rib and stiffening rib, front beam, back beam, banding rib and stiffening rib are fixed into the fixed frame structure of a chinese character kou font. The drive structure includes motor, motor drive axle, reduction gear and worm gear, the motor is fixed to be set up on the stiffening rib, the input shaft of reduction gear and motor drive axle's end connection, the reduction gear output shaft is connected with worm one end, relative position all is provided with a via hole on banding rib and the stiffening rib, the other end meshing of worm has the worm wheel, the center of the side of worm wheel is fixed with the rotation axis, just the rotation axis is located between front-bearer and the back-bearer, and passes the via hole and the activity of left strengthening rib and middle part strengthening rib and take and establish on two via holes, the other end of rotation axis with the shell of second electric ducted fan thrust device is fixed.
Further, thrust controllers are arranged inside the first and second electric ducted fan thrust devices, the thrust controllers are communicated with an attitude control circuit on the aircraft, the thrust controllers control the hovering and flying thrust provided by the electric ducted fan thrust devices by changing the rotating speed of the electric ducted fan thrust devices, and the attitude control circuit is used for changing the rolling, pitching and yawing moments of the aircraft.
Furthermore, at least one auxiliary reinforcing rib is arranged between the edge sealing rib and the reinforcing rib.
Further, the rotary shaft is a member that can transmit torque.
Further, the member may be a rigid shaft or at least one flexible shaft capable of transmitting torque.
The utility model has the advantages that: the two sides of a duck wing and two sides of a wing of the aircraft are respectively provided with an electric ducted fan thrust device, the first electric ducted fan thrust devices on the two sides of the duck wing are fixed, the second electric ducted fan thrust devices on the two sides of the wing can tilt, when the aircraft takes off vertically, the second electric ducted fan thrust devices on the wing and the first electric ducted fan thrust devices on the duck wing both push upwards vertically to provide power for taking off of the aircraft, after the aircraft leaves the ground, the second electric ducted fan thrust devices on the two sides of the wing slowly tilt and push the aircraft to fly forwards, and the aircraft is accelerated gradually, and the thrust controller controls the thrust of the first electric ducted fan thrust devices on the two sides of the duck wing, so that the aircraft is controlled in a required state. When the aircraft arrives at a destination, the aircraft decelerates gradually, the thrust controller controls the 2 second electric ducted fan thrust devices of the wings to slowly tilt, the generated thrust overcomes the weight of the aircraft through controlling the rotor speeds of the first electric ducted fan thrust devices of the wings and the canard and the second electric ducted fan thrust devices to realize slow landing of the aircraft, the flat flying speed of the multi-rotor aircraft is improved, other flight indexes are optimized, and guarantee is provided for stable and quick flight of the aircraft.
Drawings
Fig. 1 is a schematic structural view of the present invention;
fig. 2 is an enlarged view of the tilt actuator of the present invention.
Detailed Description
The present invention will be described in detail with reference to the accompanying drawings in conjunction with embodiments. It should be noted that the features of the following embodiments and examples may be combined with each other without conflict.
As shown in fig. 1-2, an electric ducted fan fixed wing aircraft capable of short-distance/vertical take-off and landing comprises a fuselage, a canard wing 1 connected to the front of the fuselage and a wing 2 connected to the rear of the fuselage, wherein the fuselage is a volume cavity of the aircraft and used for containing necessary related equipment and loads of the aircraft, the canard wing 1 and the wing 2 provide necessary lift force for the aircraft during horizontal flight, two ends of the canard wing 1 are respectively and fixedly provided with a first electric ducted fan thrust device 3, the first electric ducted fan thrust devices are fixed at a substantially vertical position, and provided airflow is substantially perpendicular to the fuselage direction of the aircraft so as to provide vertical thrust. The wings on the left side and the right side of the aircraft body are respectively provided with a tilting actuator, each tilting actuator drives one second electric ducted fan thrust device 6, the mounting position of each second electric ducted fan thrust device 6 is located at the wing tip expanded on the two sides of the wing, the second electric ducted fan thrust devices 6 can tilt between the direction perpendicular to the aircraft body and the direction horizontal to the aircraft body under the driving of the tilting actuators, and the provided air flow can tilt between the direction basically perpendicular to the aircraft body and the direction horizontal to the aircraft body. The first and second electrically ducted fan thrust devices derive power from a high power density battery disposed within the engine block. The battery may be rechargeable while the aircraft is on the ground.
Tilting actuator includes bearing structure 4 and drive structure 5, bearing structure 4 includes front beam 41, back beam 42, banding rib 43 and reinforcing rib 45, front beam 41, back beam 42, banding rib 43 and reinforcing rib 45 are fixed into the fixed frame structure of a chinese character kou. And 2 or more auxiliary reinforcing ribs 46 are arranged between the edge sealing rib 43 and the reinforcing rib 45, and the auxiliary reinforcing ribs can be obliquely arranged between the edge sealing rib 43 and the reinforcing rib 45. The front beam 41, the rear beam 42, the edge sealing rib 43, the reinforcing rib 45 and the auxiliary reinforcing rib 46 are all in a strip plate structure. And when the installation is carried out, the strip-shaped plate body is vertically installed.
The driving structure 5 comprises a motor 51, a motor driving shaft, a speed reducer 52, a worm wheel 53 and a worm 54, the motor 51 is fixedly arranged on the reinforcing rib 45, an input shaft of the speed reducer is connected with the end part of the driving shaft of the motor, an output shaft of the speed reducer is connected with one end of the worm 54, the speed reducer of the embodiment comprises a mechanism for reducing the speed of the output shaft, and the output end of the speed reducer is connected with the worm 54. The edge sealing rib 43 and the reinforcing rib 45 are provided with a through hole at opposite positions, the other end of the worm 54 is engaged with a worm wheel, a rotating shaft 55 is fixed at the center of the side face of the worm wheel, the rotating shaft is positioned between the front beam and the rear beam, penetrates through the through holes of the edge sealing rib 43 and the reinforcing rib 45 and is movably arranged on the two through holes, and the other end of the rotating shaft 55 is fixed with the shell of the second electric ducted fan thrust device 3. The axis of rotation 55 is parallel to the plane of the wing tips on either side of the rear of the wing. The motor 51 is used for driving the motor to drive the shaft to rotate at a constant speed, the drive shaft drives the input end of the speed reducer to rotate, the output end of the speed reducer drives the worm 54 to rotate, the worm 54 further pushes the worm wheel 53, the worm wheel further drives the rotating shaft 55 to rotate, and the rotating shaft 55 further drives the second electric ducted fan thrust device 6 to rotate. This tilting actuator can drive second electric ducted fan thrust device 6 at the uniform velocity and rotate, drives second electric ducted fan thrust device and just can satisfy the flight requirement at the fuselage direction of basic perpendicular to aircraft and the aircraft fuselage direction within range of level basically verts.
In the embodiment, two sides of a duck wing and two sides of a wing of an aircraft are respectively provided with an electric ducted fan thrust device, the first electric ducted fan thrust devices on the two sides of the duck wing are fixed, the second electric ducted fan thrust devices on the two sides of the wing can be tilted, when the aircraft takes off vertically, the second electric ducted fan thrust devices on the wing and the first electric ducted fan thrust devices on the duck wing are both vertically upward, power is provided for the aircraft to take off, after the aircraft leaves the ground, the second electric ducted fan thrust devices on the two sides of the wing slowly tilt, the aircraft is pushed to fly forwards, and the aircraft is accelerated gradually, a thrust controller controls the thrust of the first electric ducted fan thrust devices on the two sides of the duck wing, and the aircraft is controlled in a required state. When the aircraft arrives at a destination, the aircraft decelerates gradually, the thrust controller controls the 2 second electric ducted fan thrust devices of the wings to slowly tilt, the generated thrust overcomes the weight of the aircraft through controlling the rotor speeds of the first electric ducted fan thrust devices of the wings and the canard and the second electric ducted fan thrust devices to realize slow landing of the aircraft, the flat flying speed of the multi-rotor aircraft is improved, other flight indexes are optimized, and guarantee is provided for stable and quick flight of the aircraft.
The above embodiments are only intended to represent the concentrated embodiments of the present invention, and the description thereof is more specific and detailed, but it is not to be understood as the limitation of the scope of the present invention, and it should be noted that, for those skilled in the art, many variations and modifications can be made without departing from the concept of the present invention, and all of them belong to the protection scope of the present invention. Therefore, the protection scope of the present invention should be subject to the appended claims.
Claims (6)
1. The utility model provides an electricity duct fan fixed wing aircraft that can short distance/VTOL, includes the fuselage and connects duck wing and the wing at the fuselage rear portion in the fuselage forepart, and the fuselage is the volume chamber of aircraft for hold necessary relevant equipment and the load of aircraft, duck wing and wing provide necessary lift for the aircraft when horizontal flight, and the both ends of duck wing are each fixed arrangement has an electricity duct fan thrust unit, its characterized in that: the aircraft comprises an aircraft body, and is characterized in that wings on the left side and the right side of the aircraft body are respectively provided with a tilting actuator, each tilting actuator drives a second electric ducted fan thrust device, the mounting position of each second electric ducted fan thrust device is located at the wing tip part expanded on the two sides of each wing, and the second electric ducted fan thrust devices can tilt between the direction perpendicular to the aircraft body and the direction horizontal to the aircraft body under the driving of the tilting actuators.
2. The short/vtol electrically ducted fan fixed wing aircraft according to claim 1, wherein: the tilting actuating mechanism comprises a supporting structure and a driving structure, the supporting structure is a part of the internal structure of the wing, the supporting structure at least comprises a front beam, a rear beam, a sealing rib and a reinforcing rib, the front beam, the rear beam, the sealing rib and the reinforcing rib are fixed into a fixed frame structure in a shape like a Chinese character kou, the driving structure comprises a motor, a motor driving shaft, a speed reducer and a worm gear, the motor is fixedly arranged on the reinforcing rib, an input shaft of the speed reducer is connected with the end part of the motor driving shaft, an output shaft of the speed reducer is connected with one end of the worm, the opposite positions on the sealing rib and the reinforcing rib are respectively provided with a through hole, the other end of the worm gear is meshed with a worm wheel, the center of the side surface of the worm wheel is fixedly provided with a rotating shaft, the rotating shaft is positioned between the front beam and the rear beam, and passes through holes of, the other end of the rotating shaft is fixed with a shell of the second electric ducted fan thrust device.
3. The short/vtol electrically ducted fan fixed wing aircraft according to claim 1, wherein: the first and second electric ducted fan thrust devices are internally provided with thrust controllers, the thrust controllers are communicated with an attitude control circuit on the aircraft, the thrust controllers control the hovering and flying thrust provided by the electric ducted fan thrust devices by changing the rotating speed of the electric ducted fan thrust devices, and the attitude control circuit is used for changing the rolling, pitching and yawing moments of the aircraft.
4. The short/vtol electrically ducted fan fixed wing aircraft according to claim 2, wherein: at least one auxiliary reinforcing rib is arranged between the edge sealing rib and the reinforcing rib.
5. The short/vtol electrically ducted fan fixed wing aircraft according to claim 2, wherein: the rotating shaft is a member capable of transmitting torque.
6. The short/vtol electrically ducted fan fixed wing aircraft according to claim 5, wherein: the member is a rigid shaft or at least one flexible shaft capable of transmitting torque.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921490602.4U CN210822751U (en) | 2019-09-09 | 2019-09-09 | Electric ducted fan fixed wing aircraft capable of achieving short-distance/vertical take-off and landing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921490602.4U CN210822751U (en) | 2019-09-09 | 2019-09-09 | Electric ducted fan fixed wing aircraft capable of achieving short-distance/vertical take-off and landing |
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| Publication Number | Publication Date |
|---|---|
| CN210822751U true CN210822751U (en) | 2020-06-23 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201921490602.4U Active CN210822751U (en) | 2019-09-09 | 2019-09-09 | Electric ducted fan fixed wing aircraft capable of achieving short-distance/vertical take-off and landing |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| TWI782333B (en) * | 2020-09-29 | 2022-11-01 | 瑞鑑航太科技股份有限公司 | Flying vehicle |
| WO2023212788A1 (en) * | 2022-05-04 | 2023-11-09 | Carlos Pereira Filho Alberto | Wing tip thruster rotation system |
-
2019
- 2019-09-09 CN CN201921490602.4U patent/CN210822751U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| TWI782333B (en) * | 2020-09-29 | 2022-11-01 | 瑞鑑航太科技股份有限公司 | Flying vehicle |
| WO2023212788A1 (en) * | 2022-05-04 | 2023-11-09 | Carlos Pereira Filho Alberto | Wing tip thruster rotation system |
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