Vertical take-off and landing electric helicopter having compound wing

Abstract

A vertical take-off and landing electric helicopter having a compound wing, the vertical take-off and landing electric helicopter comprising a fuselage (1), wherein a plurality of groups of lift propellers (2) are respectively provided on the front and rear sides of the fuselage (1), and a plurality of groups of lift propellers (2) are respectively provided on the left and right sides of the fuselage; a forward propulsion propeller (6) is provided on the rear side of the fuselage, and the forward propulsion propeller (6) and the lift propellers (2) are driven by electric motors; and a rotary wing (7) is provided on the top of the fuselage, and is controlled by a wing rotation mechanism (8). By providing the foldable lift propellers (2) on the left and right sides of the fuselage, a propeller span of the helicopter is increased, the crosswind resistance of the helicopter is improved, and the safety performance of the helicopter is enhanced. The wing rotation mechanism (8) enables control of the rotation direction of the wing and locking and positioning of the wing. After the foldable lift propellers (2) and the rotary wing (7) are folded, the helicopter can be parked in a single parking space, and can take off and land on a single lane and roadside of a highway; and when the wing is deployed, the wing generates lift, and the forward propulsion propeller (6) provides thrust.

Description

Vertical take-off and landing electric helicopter with compound wings TECHNICAL FIELD

[0001] The present application relates to the technical field of helicopters, in particular to a vertical take-off and landing electric helicopter with compound wings. BACKGROUND

[0002] At present, the rotor type helicopter has been widely used since its invention, and its core advantage is that it can realize vertical take-off, hovering at a fixed point in the air, and can realize up, down, left, right, forward and backward translation, rolling, etc., and has applications in military and civilian fields. Although the advantages are obvious, the disadvantages are also very prominent. The take-off and landing requires a dedicated site. In addition, the existing helicopter has a large external structure, and also needs a large dedicated site for parking after landing, which is very unfavorable for the promotion of the helicopter. TECHNICAL PROBLEM

[0003] One of the main purposes of the present application is to overcome at least one of the defects in the prior art, and to provide a vertical take-off and landing electric helicopter with compound wings. TECHNICAL SOLUTION

[0004] In order to achieve the above technical scheme, the present application adopts the following technical scheme:

[0005] According to one aspect of the present application, a vertical take-off and landing electric helicopter with compound wings is provided, comprising a body, a plurality of groups of lift fans are arranged on the front and rear sides of the body, and a plurality of groups of lift fans are arranged on the left and right sides of the body. The lift fans are driven by motors and used to generate upward lift. The rear side of the body is provided with a front push fan, which is driven by a motor and used to generate forward thrust. The motor is powered by a battery pack.

[0006] The top of the body is provided with a rotating wing, and the rotating wing is controlled by a wing rotating mechanism. The wing rotating mechanism can control the rotating direction of the wing, and at the same time position and lock the wing.

[0007] According to an embodiment of the present application, the wing rotating mechanism comprises a support frame, an electric push rod is arranged in the support frame, the electric push rod is driven by a motor, the push rod end of the electric push rod is hingedly fixed with a wing rotating arm, and the other end of the wing rotating arm is fixed on the wing.

[0008] When the push rod end of the electric actuator extends, the wing rotor arm rotates 90° around the wing's rotation center under the action of the electric actuator, at which point the wing is perpendicular to the entire aircraft in the length direction. When the push rod end retracts, the wing rotor arm rotates 90° in the opposite direction around the wing's rotation center under the action of the electric actuator, returning the wing to its original position; at this point, the wing is aligned with the entire aircraft in the length direction. The wing rotation mechanism achieves wing rotation while simultaneously positioning and locking the wing.

[0009] According to one embodiment of the present invention, the support frame has a receiving cavity capable of accommodating the motor, electric push rod, push rod end and wing rotor arm within the support frame.

[0010] According to one embodiment of the present invention, each set of lift propellers consists of coaxial positive and negative propellers with a double-layer structure; the coaxial double propellers include an upper lift propeller and a lower lift propeller arranged coaxially, controlled by a drive motor; specifically, the upper lift propeller and the lower lift propeller are each controlled by a drive motor.

[0011] According to one embodiment of the present invention, the lift propellers disposed on the front and rear sides of the fuselage are mounted on the fuselage by means of fixed brackets; the lift propellers disposed on the left and right sides of the fuselage are each mounted on the fuselage by means of a folding mechanism, forming a folding lift propeller, which can realize the folding and unfolding of the lift propellers on the left and right sides.

[0012] The lift propellers located on the left and right sides of the fuselage are arranged in a horizontally staggered manner with the lift propellers located on the front and rear sides of the fuselage after folding, so as to reduce the overall length of the fuselage after folding.

[0013] According to one embodiment of the present invention, a tail fin is provided on a fixed bracket at the rear of the fuselage, and a servo motor is provided on the tail fin; servo motors are also provided at both ends of the upper rear side of the wing. The servo motors enable control of the aircraft's flight attitude.

[0014] According to one embodiment of the present invention, the folding mechanism includes: support tubes respectively disposed on the left and right sides of the machine body; a lead screw and a lead screw cooperating with the lead screw are disposed inside the support tubes; the lead screw is driven by a motor; and a lead screw end is provided at one end of the lead screw away from the lead screw; the lead screw end moves within an anti-rotation guide groove in the support tube; the anti-rotation guide groove can prevent the lead screw from rotating; the outer end of the support tube is hinged to a rotating arm; and the lead screw end is movably connected to the rotating arm through a connecting rod.

[0015] Through the transmission and cooperation of the lead screw and lead nut, as well as the anti-rotation function of the anti-rotation guide groove, the rotational motion of the lead screw can be converted into the linear motion of the lead nut, and then into the tension or thrust on the connecting rod and the rotating arm.

[0016] According to one embodiment of the present invention, the connecting rod is preferably an L-shaped connecting rod; one end of the connecting rod is hinged and fixed to the rotating arm, and the other end is hinged and fixed to the end of the nut.

[0017] According to one embodiment of the present invention, the drive motor of the lead screw is a dual-output shaft motor, with lead screws and nuts on both sides engaging, and the two sets of lead screws and nuts having opposite thread directions, which can simultaneously fold or unfold the rotating arms on the left and right sides of the machine body.

[0018] According to one embodiment of the present invention, the machine body is generally provided with two seats, which are arranged one in front of the other or side by side.

[0019] According to one embodiment of the present invention, the vertical take-off and landing electric helicopter, when folded up, can be parked in a single parking space and can take off and land on a single lane or roadside.

[0020] According to one embodiment of the present invention, electric aircraft tires are provided at the bottom of the fuselage to facilitate movement and parking after landing.

[0021] According to one embodiment of the present invention, a parachute is provided on the top of the aircraft body, which can safely land in the event of a malfunction, thereby improving safety performance. Beneficial effects

[0022] In this application, by installing several sets of foldable lift rotors on the left and right sides of the fuselage, the helicopter's resistance to crosswinds is improved when deployed, thereby enhancing the aircraft's safety performance.

[0023] Thanks to its folding lift rotors and rotating wings, the helicopter can deploy during flight and fold down before or after landing, demonstrating highly flexible structural performance and strong adaptability. When the folding lift rotors and wings are folded, the helicopter's dimensions in both width and length are similar to those of a regular car, allowing it to fit in a single parking space and enabling takeoff and landing on single-lane highways or roadsides. Furthermore, the lift rotors located on the left and right sides of the fuselage can be arranged in a horizontally staggered manner with those located on the front and rear sides after folding, further reducing the overall length of the helicopter when folded. The wing rotation mechanism controls the wing's rotation direction and simultaneously positions and locks the wing; when the wing is deployed across the width of the helicopter and perpendicular to the fuselage, the wing generates lift, while the pusher rotor provides thrust.

[0024] By installing a parachute on the top of the fuselage, a safe landing can be ensured, improving the helicopter's safety performance and enhancing its ability to respond to emergencies. Attached Figure Description

[0025] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, for those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0026] Figure 1 is a top view of a vertical take-off and landing electric helicopter with a compound wing according to the present invention, wherein the foldable lift rotors on the left and right sides of the wings and fuselage are in the deployed state.

[0027] Figure 2 is a top view of another usage state of the vertical take-off and landing electric helicopter with compound wings according to the present invention, wherein the wings and the foldable lift rotors on the left and right sides are in the folded state.

[0028] Figure 3 is a bottom view of the helicopter in Figure 2;

[0029] Figure 4 is a front view of a vertical takeoff and landing electric helicopter with a compound wing as shown in Figure 1.

[0030] Figure 5 is a perspective view of a vertical takeoff and landing electric helicopter with a compound wing according to the present invention.

[0031] Figure 6 is a schematic diagram of the folding mechanism of the present invention, wherein the folding mechanism provided on the left and right sides of the machine body is in a semi-expanded state;

[0032] Figure 7 is a bottom view of the wing and wing rotation mechanism in Figure 5, in which the wing is spread out in the width direction of the whole aircraft and perpendicular to the fuselage.

[0033] The annotations in the attached figures are explained as follows:

[0034] 1-Aircraft fuselage; 2-Lift propeller; 21-Upper lift propeller; 22-Lower lift propeller; 3-Fixed bracket; 4-Folding mechanism; 41-Support tube; 411-Anti-rotation guide groove; 42-Lead screw; 43-Lead nut; 44-Dual output shaft motor; 45-Lead nut end; 46-Connecting rod; 47-Rotating arm; 48-Coupling; 49-Support tube end; 5-Aircraft tire; 6-Front pusher propeller; 7-Wing; 8-Wing rotation mechanism; 81-Support frame; 82-Electric push rod; 83-Push rod end; 84-Wing rotor arm; 9-Tail. The best embodiment of the present invention

[0035] In the description of this invention, unless otherwise stated, "a plurality of" means two or more. The terms "inner," "outer," "upper," "lower," etc., indicate the orientation or state relationship based on the orientation or state relationship shown in the drawings, and are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention.

[0036] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation" and "connection" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art will understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0037] It should be noted that the terms "first," "second," etc., used in the specification, claims, and accompanying drawings of this invention are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate for the embodiments of the invention described herein.

[0038] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments.

[0039] Referring to Figures 1-7, this application discloses a vertical takeoff and landing electric helicopter with a compound wing, comprising a fuselage 1, lift rotors 2, a fixed support 3, a folding mechanism 4, aircraft tires 5, a thrust rotor 6, a rotary wing 7, a wing rotation mechanism 8, and a tail 9. Two sets of lift rotors 2 are respectively arranged on the front and rear sides of the fuselage 1, and two sets of lift rotors 2 are respectively arranged on the left and right sides of the fuselage 1. The lift rotors 2 are driven by a drive motor to generate upward lift. A thrust rotor 6 is arranged on the rear side of the fuselage 1, and the thrust rotor is driven by a drive motor to generate forward thrust. The drive motor is powered by a battery pack. A rotary wing 7 is arranged on the top of the fuselage, and the rotary wing 7 is controlled by the wing rotation mechanism 8.

[0040] Furthermore, the wing rotation mechanism 8 includes a support frame 81, within which an electric push rod 82 is disposed. The push rod end 83 of the electric push rod 82 is hinged and fixed to the wing rotor arm 84, and the other end of the wing rotor arm 84 is fixed to the wing 7. When the push rod end 83 of the electric push rod extends, the wing rotor arm 84 rotates 90° around the rotation center of the wing 7 under the action of the electric push rod 82, at which point the wing 7 is spatially perpendicular to the fuselage 1. When the push rod end 83 of the electric push rod retracts, the wing rotor arm 84 rotates 90° in the opposite direction around the rotation center of the wing 7 under the action of the electric push rod 82, causing the wing to return to its original position; at this point, the wing 7 and the fuselage 1 are on the same straight line. The wing rotation mechanism 8 realizes the rotation of the wing 7 and simultaneously positions and locks the wing 7. Specifically, the support frame 81 has a receiving cavity that can accommodate the electric push rod 82, the push rod end 83, and the wing rotor arm 84 within the support frame 81.

[0041] Each set of lift propellers 2 consists of a coaxial positive and negative propeller, also known as a coaxial dual propeller, and adopts a double-layer structure. The coaxial dual propeller includes an upper lift propeller 21 and a lower lift propeller 22 arranged coaxially, that is, the upper lift propeller 21 is arranged on the upper side and the lower lift propeller 22 is arranged on the lower side.

[0042] In this application, the lift propellers 2 located on the front and rear sides of the fuselage 1 are mounted on the fuselage 1 via fixed brackets 3; the lift propellers 2 located on the left and right sides of the fuselage 1 are each mounted on the fuselage 1 via a folding mechanism 4, forming folding lift propellers to achieve the folding and unfolding of the left and right lift propellers 2; wherein, after being folded, the lift propellers located on the left and right sides of the fuselage 1 are arranged in a horizontally staggered manner with the lift propellers located on the front and rear sides of the fuselage 1 to reduce the overall length of the aircraft after folding; the folding mechanism 4 can extend outward to increase the propeller pitch, improve the aircraft's resistance to crosswinds, and enhance the aircraft's safety. As shown in Figure 5, specifically, the folding mechanism 4 includes: support tubes 41 respectively disposed on the left and right sides of the body 1; a lead screw 42 and a lead screw nut 43 cooperating with the lead screw 42 are disposed in the support tubes 41; the lead screw 42 is driven by a dual-output shaft motor 44; a lead screw end 45 is connected to the end of the lead screw nut 43 away from the lead screw 42; the lead screw end 45 moves in the anti-rotation guide groove 411 of the support tube 41, and the anti-rotation guide groove 411 can prevent the lead screw nut 43 from rotating; the outer end of the support tube is hinged to the rotating arm; the lead screw end 45 is movably connected to the rotating arm 47 through a connecting rod 46; through the transmission cooperation of the lead screw 42 and the lead screw nut 43, the rotational motion of the lead screw 42 can be converted into the linear motion of the lead screw nut 43, and then into a pulling or pushing force on the connecting rod and the rotating arm.

[0043] In this application, a tail fin 9 is mounted on a fixed bracket at the rear of the fuselage 1, and a servo motor is mounted on the tail fin 9; servo motors are also mounted at both ends of the rear side of the wing 7. The servo motors enable control of the aircraft's flight attitude.

[0044] In this application, the fuselage 1 is equipped with two seats, which are arranged one in front of the other or side by side, suitable for two-person travel. Of course, provided that the load capacity of the fuselage 1 allows, four seats can be arranged, in two rows one in front of the other, with two seats on each side of each row, especially suitable for a family of three or four. This application's vertical take-off and landing electric helicopter, when folded, can be parked in a single parking space and can take off and land on a single lane or roadside, adapting to various applications and facilitating the promotion and home use of small helicopters.

[0045] As shown in Figure 5, which is a schematic diagram of the folding mechanism described in this invention, the lifting propellers located on the left and right sides of the machine body are in a semi-deployed state. The connecting rod 46 is an L-shaped connecting rod; one end of the connecting rod 46 is hinged to the rotating arm 47, and the other end is hinged to the nut end 45. The nut 43 moves linearly along the axis of the support tube 41. An anti-rotation guide groove 411 is provided on the support tube 41, and both ends of the nut end 45 extend from the anti-rotation guide groove 411. When the nut 43 moves linearly, it will not rotate, ensuring the safe and efficient deployment of the connecting rod 46 and the rotating arm 47.

[0046] In Figure 5, the dual-output shaft motor 44 can simultaneously unfold the rotating arms 47 on both sides of the machine body 1. Specifically, the dual-output shaft motor 44 is connected to the lead screws 42 on both sides via a coupling 48. It should be noted that the lead screws 42 on both sides in Figure 5 are left-handed and right-handed lead screws, respectively. When the dual-output shaft motor 44 rotates forward or in reverse, it can simultaneously drive the lead screws and nuts on both sides to rotate, thereby converting them into a pushing and pulling force on the connecting rod 46 and the rotating arms 47, realizing the unfolding and folding of the rotating arms 47 on both sides of the machine body 1. Embodiments of the present invention

[0047] To cope with emergencies, a parachute is installed on the top of the fuselage. In case of weather conditions or aircraft malfunction, the parachute can ensure a safe landing, thus improving the helicopter's safety performance.

[0048] As shown in Figures 1-4, electrically powered aircraft tires 5 are installed at the bottom of the fuselage 1. After landing, the aircraft tires 5 move the aircraft to a parking space or designated location for easy movement and parking.

[0049] In addition, a protective cover can be installed around the propeller to prevent injury to people and property, and to effectively block foreign objects such as birds and flying plastic bags. Industrial applicability

[0050] In summary, this application, by arranging several sets of folding lift rotors on the left and right sides of the fuselage and incorporating rotating wings, achieves several advantages. When folded, the overall width of the helicopter is small, facilitating parking in a single parking space and enabling takeoff and landing on single-lane highways or roadsides. When the folding lift rotors are deployed, the pitch of the rotor blades on both sides of the helicopter is increased, improving the helicopter's resistance to crosswinds and enhancing its safety performance. When the wings are deployed in the width direction and perpendicular to the fuselage, the wings generate lift, while the pusher rotor provides thrust. Due to the use of folding lift rotors and rotating wings, the helicopter can deploy during flight and fold before or after landing, demonstrating a highly flexible structural performance and strong adaptability. Furthermore, the wing rotation mechanism allows for control of the wing's rotation direction, as well as positioning and locking of the wing. Sequence List Free Content

[0051] It should be understood that the application of this invention is not limited to the detailed structure and arrangement of the components presented herein. The invention can have other embodiments and can be implemented and performed in various ways. The foregoing variations and modifications fall within the scope of this invention. It should be understood that the invention disclosed and defined herein extends to all alternative combinations of two or more individual features mentioned or apparent in the text and / or drawings. The embodiments described herein illustrate the best known mode for carrying out the invention and will enable those skilled in the art to utilize the invention.

Claims

1. A vertical takeoff and landing electric helicopter with a compound wing, comprising a fuselage, characterized in that, Several sets of lift propellers are respectively arranged on the front and rear sides of the fuselage, and several sets of lift propellers are respectively arranged on the left and right sides of the fuselage. The lift propellers are driven by motors. A forward thruster is arranged on the rear side of the fuselage. The forward thruster is driven by a motor and is used to generate forward thrust. The motor is powered by a battery pack. The top of the fuselage is equipped with a rotating wing, which is controlled by a wing rotation mechanism.

2. The vertical takeoff and landing electric helicopter with a compound wing according to claim 1, characterized in that, The wing rotation mechanism includes a support frame, within which an electric push rod is installed. The electric push rod is driven by a motor, and the push rod end is hinged and fixed to the wing rotor arm. The other end of the wing rotor arm is fixed to the wing.

3. A vertical takeoff and landing electric helicopter with a compound wing according to claim 1, characterized in that, Each set of lift propellers consists of a coaxial positive and negative propeller, also known as a coaxial dual propeller. The coaxial dual propeller includes an upper lift propeller and a lower lift propeller arranged coaxially, and is controlled by a drive motor.

4. A vertical takeoff and landing electric helicopter with a compound wing according to claim 1, characterized in that, The lift propellers located on the front and rear sides of the fuselage are mounted on the fuselage via fixed brackets; the lift propellers located on the left and right sides of the fuselage are each mounted on the fuselage via a folding mechanism to achieve the folding and unfolding of the lift propellers. The lift propellers located on the left and right sides of the fuselage and the lift propellers located on the front and rear sides of the fuselage can be arranged horizontally in a staggered manner to reduce the overall length of the fuselage after folding.

5. A vertical takeoff and landing electric helicopter with a compound wing according to claim 4, characterized in that, The folding mechanism includes: support tubes respectively disposed on the left and right sides of the machine body; a lead screw and a lead screw cooperating with the lead screw are disposed inside the support tubes; the lead screw is driven by a motor; a lead screw end is connected to the end of the lead screw away from the lead screw; the lead screw end moves in the anti-rotation guide groove of the support tube; the anti-rotation guide groove can prevent the lead screw from rotating; the outer end of the support tube is hinged to the rotating arm; the lead screw end is movably connected to the rotating arm through a connecting rod. Through the transmission and cooperation of the lead screw and lead nut, as well as the anti-rotation function of the anti-rotation guide groove, the rotational motion of the lead screw can be converted into the linear motion of the lead nut, and then into the tension or thrust on the connecting rod and the rotating arm.

6. A vertical takeoff and landing electric helicopter with a compound wing according to claim 5, characterized in that, The connecting rod is preferably an L-shaped connecting rod; one end of the connecting rod is hinged and fixed to the rotating arm, and the other end is hinged and fixed to the end of the nut.

7. A vertical takeoff and landing electric helicopter with a compound wing according to claim 5, characterized in that, The drive motor of the lead screw is a dual-output shaft motor, with lead screws and nuts on both sides cooperating. The threads of the two sets of lead screws and nuts are in opposite directions, which can simultaneously fold or unfold the rotating arms on the left and right sides of the machine body.

8. A vertical takeoff and landing electric helicopter according to any one of claims 1 to 7, characterized in that, The aircraft is equipped with electrically powered tires at the bottom of the fuselage, which facilitates movement and parking after landing.

9. A vertical takeoff and landing electric helicopter with a compound wing according to any one of claims 1 to 7, characterized in that, When folded, the vertical take-off and landing electric helicopter can take off and land in a single lane, on the roadside, and park in a single parking space.

10. A vertical takeoff and landing electric helicopter with a compound wing according to any one of claims 1 to 7, characterized in that, A tail fin is mounted on a fixed support at the rear of the fuselage, and a servo motor is mounted on the tail fin; servo motors are also mounted on both ends of the upper rear side of the wing, and the flight attitude of the aircraft is controlled by the servo motors.

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