Vertical take-off and landing electric helicopter with composite wings

Abstract

The invention relates to the technical field of helicopters, in particular to a vertical take-off and landing electric helicopter with composite wings. The vertical take-off and landing electric helicopter comprises a helicopter body, multiple sets of lift propellers are arranged on the front side and the rear side of the helicopter body correspondingly, multiple sets of lift propellers are arranged on the left side and the right side of the helicopter body correspondingly, a front push propeller is arranged on the rear side of the helicopter body, and the front push propeller and the lift propellers are driven by motors; rotary wings are arranged at the top of the aircraft body and controlled through a wing rotating mechanism. The foldable lift propellers are arranged on the left side and the right side of the helicopter body, so that the propeller pitch of the helicopter is increased, the crosswind resistance of the helicopter is improved, and the safety performance of the helicopter is improved; the rotating direction of the wings is controlled through the wing rotating mechanism, and the wings are locked and positioned. After the folding type lifting force paddles and the rotary type wings are folded, the helicopter can be parked in a single parking space and can take off and land on a single lane and the roadside of a road; when the wings are unfolded, the wings generate lift force, and the front propellers provide thrust.

Description

Technical Field

[0001] The invention relates to the technical field of helicopters, and in particular to a vertical take-off and landing electric helicopter with composite wings. Background Art

[0002] At present, rotor-type helicopters have been widely used since their invention. Their core advantages are that they can take off and land vertically, hover at a fixed point in the air, and move up and down, left and right, front and back, and roll, etc. They are used in both military and civilian fields. Although the advantages are significant, the disadvantages are also prominent. Special venues are required for takeoff and landing. In addition, existing helicopters have a large external structure and also require a large special venue for parking after landing, which is very unfavorable for the promotion of helicopters. Summary of the invention

[0003] A main purpose of the present invention is to overcome at least one defect in the prior art and provide a vertical take-off and landing electric helicopter with composite wings.

[0004] In order to realize the above technical solution, the present invention adopts the following technical solution:

[0005] According to one aspect of the present invention, there is provided a vertical take-off and landing electric helicopter with composite wings, comprising a fuselage, wherein a plurality of lift propellers are respectively arranged on the front and rear sides of the fuselage, and a plurality of lift propellers are respectively arranged on the left and right sides of the fuselage, wherein the lift propellers are driven by a motor and used to generate an upward lift; a forward propeller is arranged on the rear side of the fuselage, wherein the forward propeller is driven by a motor and used to generate a forward thrust; and the motor is powered by a battery pack;

[0006] Wherein, a rotary wing is arranged on the top of the fuselage, and the rotary wing is controlled by a wing rotating mechanism. The wing rotating mechanism can control the rotation direction of the wing, and simultaneously position and lock the wing.

[0007] According to one embodiment of the present invention, the wing rotation mechanism includes a support frame, an electric push rod is arranged in the support frame, the electric push rod is driven by a motor, a push rod end of the electric push rod is hingedly fixed to the wing swing arm, and the other end of the wing swing arm is fixed to the wing;

[0008] When the push rod end of the electric push rod is extended, the wing arm rotates 90° around the rotation center of the wing under the action of the electric push rod, and the wing is perpendicular to the whole machine in the length direction; when the push rod end is retracted, the wing arm rotates 90° in the opposite direction around the rotation center of the wing under the action of the electric push rod to reset the wing; at this time, the wing is consistent with the whole machine in the length direction. The wing rotation mechanism realizes the rotation of the wing, and can also position and lock the wing.

[0009] According to one embodiment of the present invention, the support frame has a accommodating cavity, which can accommodate the motor, the electric push rod, the push rod end and the wing swing arm in the support frame.

[0010] According to one embodiment of the present invention, each group of lift propellers are coaxial forward propellers and reverse propellers with a double-layer structure; the coaxial double propellers include coaxially arranged upper lift propellers and lower lift propellers, which are controlled by a drive motor; specifically, the upper lift propellers and lower lift propellers are each controlled by a drive motor.

[0011] According to one embodiment of the present invention, the lift propellers arranged on the front and rear sides of the body are mounted on the body through a fixing bracket; the lift propellers arranged on the left and right sides of the body, each of which is mounted on the body through a folding mechanism, constitute a foldable lift propeller, which can realize the folding and unfolding of the lift propellers on the left and right sides;

[0012] Among them, the lift propellers arranged on the left and right sides of the fuselage are arranged in a horizontal cross-staggered arrangement with the lift propellers arranged on the front and rear sides of the fuselage after being folded, so as to reduce the length of the entire machine after folding.

[0013] According to one embodiment of the present invention, a tail wing is arranged on a fixed bracket at the rear side of the fuselage, and the tail wing is provided with a steering gear; steering gears are also arranged at both ends of the rear side of the wing. The flight attitude of the aircraft can be controlled by the steering gears.

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

[0015] Through the transmission cooperation of the nut and the lead screw, 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 nut, and then converted into a pulling force or a thrust force 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 nut end.

[0017] According to one embodiment of the present invention, the driving motor of the screw is a dual-output shaft motor, the screw nuts on both sides cooperate, and the two sets of screw nuts have opposite thread rotation directions, which can simultaneously fold or unfold the rotating arms on the left and right sides of the body.

[0018] According to an embodiment of the present invention, two seats are generally arranged in the body, and the two seats are arranged front and back or side by side.

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

[0020] According to one embodiment of the present invention, electric aircraft tires are provided at the bottom of the aircraft body 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 fuselage, which enables safe landing in case of failure, thereby improving safety performance.

[0022] It can be seen from the above technical solution that the present invention has at least one of the following advantages and positive effects:

[0023] In the present application, by arranging a plurality of groups of foldable lift propellers on the left and right sides of the fuselage, when unfolded, the helicopter's ability to resist crosswinds is improved, thereby improving the safety performance of the aircraft.

[0024] Due to the use of foldable lift propellers and rotating wings, they can be unfolded during navigation and folded before or after landing, which shows a more flexible structural performance and strong adaptability. When the foldable lift propellers and wings are folded, the dimensions of the helicopter in the width and length directions are similar to those of ordinary cars. It can be parked in a single parking space and can take off and land on a single lane of a highway or on the roadside. The lift propellers set on the left and right sides of the fuselage can also be arranged horizontally cross-staggered with the lift propellers set on the front and rear sides of the fuselage after folding to reduce the length of the entire machine after folding. The wing rotation mechanism can control the rotation direction of the wing, and at the same time position and lock the wing; when the wing is unfolded in the width direction of the entire machine and perpendicular to the fuselage, the wing generates lift and the forward propeller provides thrust.

[0025] By setting a parachute on the top of the fuselage, a safe landing can be guaranteed, which improves the safety performance of the helicopter and enhances its ability to cope with emergencies. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, for ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0027] Figure 1 It is a top view of a vertical take-off and landing electric helicopter with composite wings according to the present invention, wherein the wings and the foldable lift blades on the left and right sides of the fuselage are in an unfolded state;

[0028] Figure 2 It is a top view of another use state of the vertical take-off and landing electric helicopter with composite wings of the present invention, wherein the wings and the foldable lift blades on the left and right sides are in a folded state;

[0029] Figure 3 for Figure 2 Bottom view of the helicopter;

[0030] Figure 4 for Figure 1 A front view of a vertical take-off and landing electric helicopter with composite wings;

[0031] Figure 5 A perspective view of a vertical take-off and landing electric helicopter with composite wings according to the present invention;

[0032] Figure 6 It is a structural schematic diagram of the folding mechanism of the present invention, wherein the folding mechanisms arranged on the left and right sides of the machine body are in a semi-expanded state;

[0033] Figure 7 for Figure 5 A bottom view of the middle wing and the wing rotation mechanism, in which the wing is in a state of being unfolded in the width direction of the entire aircraft and perpendicular to the fuselage.

[0034] The following are the descriptions of the reference numerals:

[0035] 1- 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- nut; 44- dual output shaft motor; 45- nut end; 46- connecting rod; 47- swing arm; 48- coupling; 49- support tube end; 5- aircraft tire; 6- forward propeller; 7- wing; 8- wing rotation mechanism; 81- support frame; 82- electric push rod; 83- push rod end; 84- wing swing arm; 9- tail wing. DETAILED DESCRIPTION

[0036] In the description of the present invention, unless otherwise specified, "plurality" means two or more. The terms "inside", "outside", "upper", "lower", etc., indicating positions or state relationships, are based on the positions or state relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific position, be constructed and operate in a specific position, and therefore cannot be understood as limiting the present invention.

[0037] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installation" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. For ordinary technicians in this field, the specific meanings of the above terms in the present invention will be understood according to specific circumstances.

[0038] It should be noted that the terms "first", "second", etc. in the specification and claims of the present invention and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the numbers used in this way can be interchanged under appropriate circumstances to facilitate the embodiments of the present invention described herein.

[0039] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific implementation modes.

[0040] See attached Figures 1 to 7 As shown, the present application is a vertical take-off and landing electric helicopter with composite wings, including a fuselage 1, a lift propeller 2, a fixed bracket 3, a folding mechanism 4, an aircraft tire 5, a forward propeller 6, a rotary wing 7, a wing rotation mechanism 8, and a tail 9. Two groups of lift propellers 2 are respectively arranged on the front and rear sides of the fuselage 1, and two groups of lift propellers 2 are respectively arranged on the left and right sides of the fuselage 1. The lift propellers 2 are driven by a driving motor to generate an upward lift; the rear side of the fuselage 1 is provided with a forward propeller 6, which is driven by a driving motor to generate a forward thrust; the driving motor is powered by a battery pack; wherein, a rotary wing 7 is arranged on the top of the fuselage, and the rotary wing 7 is controlled by a wing rotation mechanism 8.

[0041] Furthermore, the wing rotation mechanism 8 includes a support frame 81, in which an electric push rod 82 is arranged, and a push rod end 83 of the electric push rod 82 is hingedly fixed to a wing swing arm 84, and the other end of the wing swing arm 84 is fixed to the wing 7. When the push rod end 83 of the electric push rod is extended, the wing swing arm 84 is rotated 90° with the rotation center of the wing 7 under the action of the electric push rod 82, and the wing 7 is vertical to the body 1 in space; when the push rod end 83 of the electric push rod is retracted, the wing swing arm 84 is reversely rotated 90° with the rotation center of the wing 7 under the action of the electric push rod 82, so that the wing is reset; at this time, the wing 7 and the body 1 are on the same straight line. The rotation of the wing 7 is realized by the wing rotation mechanism 8, and the wing 7 can be positioned and locked at the same time. Specifically, the support frame 81 has a receiving cavity, which can receive the electric push rod 82 , the push rod end 83 and the wing swing arm 84 in the support frame 81 .

[0042] Each group of lift propellers 2 is a coaxial forward propeller and a reverse propeller, also known as a coaxial double propeller, and adopts a double-layer structure; the coaxial double propeller includes an upper lift propeller 21 and a lower lift propeller 22 coaxially arranged, 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.

[0043] In the present application, the lift propellers 2 arranged on the front and rear sides of the fuselage 1 are mounted on the fuselage 1 through a fixing bracket 3; the lift propellers 2 arranged on the left and right sides of the fuselage 1, each of which is mounted on the fuselage 1 through a folding mechanism 4, forming a folding lift propeller to realize the folding and unfolding of the lift propellers 2 on the left and right sides; wherein the lift propellers arranged on the left and right sides of the fuselage 1 are arranged horizontally crosswise and staggered with the lift propellers arranged on the front and rear sides of the fuselage 1 after folding, so as to reduce the length of the whole machine after folding; the folding mechanism 4 can extend outward to increase the pitch, improve the aircraft's ability to resist crosswinds, and improve the safety of the aircraft. Figure 5 As shown, specifically, the folding mechanism 4 includes: a support tube 41 respectively arranged on the left and right sides of the body 1, a lead screw 42 and a nut 43 cooperating with the lead screw 42 are arranged in the support tube 41, the lead screw 42 is driven by a dual-output shaft motor 44, and a nut end 45 is connected to the end of the nut 43 away from the lead screw 42; the nut 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 nut 43 from rotating; the outer end of the support tube is hinged to the rotating arm, and the nut 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 nut 43, the rotational motion of the lead screw 42 can be converted into a linear motion of the nut 43, and then converted into a pulling force or a thrust force on the connecting rod and the rotating arm.

[0044] In the present application, a tail wing 9 is arranged on a fixed bracket at the rear side of the fuselage 1, and a steering gear is arranged on the tail wing 9; steering gears are also arranged at both ends of the rear side of the wing 7. The flight attitude of the aircraft can be controlled by the steering gears.

[0045] In the present application, two seats are arranged in the body 1, and the two seats are arranged front and back or side by side, which is suitable for two people to travel. Of course, under the premise that the load of the body 1 allows, four seats can be arranged, arranged in two rows side by side, and two seats are arranged on the left and right of each row, which is particularly suitable for a family of three or four to travel. The present application provides a vertical take-off and landing electric helicopter that can be parked in a single parking space after being folded, and can take off and land on a single lane or roadside to adapt to the application of various occasions, which is conducive to accelerating the pace of promotion and home use of small helicopters.

[0046] like Figure 5 As shown, Figure 5The schematic diagram of the folding mechanism of the present invention is shown in FIG. 4 , wherein the lift paddles arranged on the left and right sides of the fuselage are in a semi-expanded state. The connecting rod 46 is an L-shaped connecting rod; one end of the connecting rod 46 is hingedly fixed to the rotating arm 47, and the other end is hingedly fixed to the nut end 45. The nut 43 moves linearly along the axis of the support tube 41, and an anti-rotation guide groove 411 is provided on the support tube 41, and the two ends of the nut end 45 extend from the anti-rotation guide groove 411 respectively; when the nut 43 moves linearly, it will not rotate, thereby ensuring that the connecting rod 46 and the rotating arm 47 are safely and efficiently deployed.

[0047] In the attached Figure 5 In the embodiment, the dual output shaft motor 44 can simultaneously expand the rotating arms 47 on the left and right sides of the machine body 1. Specifically, the dual output shaft motor 44 is connected to the lead screws 42 on both sides through a coupling 48. It should be noted that, Figure 5 The lead screws 42 on both sides are respectively left-handed and right-handed. When the dual-output shaft motor 44 rotates forward or reversely, it can simultaneously drive the lead screws and screw nuts on both sides to operate, and then convert into a push-pull force on the connecting rod 46 and the rotating arm 47, so as to realize the unfolding and folding of the rotating arms 47 on both sides of the machine body 1.

[0048] In order to cope with emergencies, a parachute is provided on the top of the body 1. In case of weather reasons or body failure, the parachute can ensure safe landing, thereby improving the safety performance of the helicopter.

[0049] like Figures 1 to 4 As shown, an electric aircraft tire 5 is provided at the bottom of the fuselage 1. After landing, the aircraft is moved to a parking space or a designated position by the aircraft tire 5 for easy movement and parking.

[0050] In addition, a protective cover can be installed on the periphery of the propeller to prevent injury to people and objects, and effectively block foreign objects such as birds and flying plastic bags. In summary, the present application sets a number of folding lift propellers on the left and right sides of the fuselage, and sets a rotating wing. When folded, the width of the whole machine is small, which is convenient for parking in a single parking space, and can take off and land on a single lane of a highway or on the roadside; when the folding lift propellers are deployed, the pitch of the left and right sides of the helicopter is increased, the helicopter's ability to resist crosswinds is improved, and the safety performance of the aircraft is improved; when the wings are deployed in the direction of the whole width of the machine and perpendicular to the fuselage, the wings generate lift, and the forward thrust propellers provide thrust; due to the use of folding lift propellers and rotating wings, they can be deployed during navigation and folded before or after landing, which embodies a more flexible structural performance and strong adaptability; and the wing rotation mechanism can control the rotation direction of the wing, and the wing can be positioned and locked at the same time.

[0051] It should be understood that the present invention is not limited in its application to the detailed structure and arrangement of the components proposed herein. The present invention can have other embodiments and can be implemented and executed in a variety of ways. The aforementioned variations and modifications fall within the scope of the present invention. It should be understood that the present invention disclosed and defined herein extends to all alternative combinations of two or more individual features mentioned or evident in the text and / or the accompanying drawings. The embodiments described herein illustrate the best mode known for implementing the present invention and will enable those skilled in the art to utilize the present invention.

Claims

1. A vertical take-off and landing electric helicopter with composite wings, comprising a body, characterized in that: The front and rear sides of the body are respectively provided with a plurality of lift propellers, and the left and right sides of the body are respectively provided with a plurality of lift propellers, and the lift propellers are driven by a motor; the rear side of the body is provided with a forward propeller, and the forward propeller is driven by a motor to generate forward thrust; the motor is powered by a battery pack; Wherein, a rotating wing is arranged on the top of the fuselage, and the rotating wing is controlled by a wing rotating mechanism.

2. A vertical take-off and landing electric helicopter with composite wings according to claim 1, characterized in that: The wing rotating mechanism comprises a supporting frame, in which an electric push rod is arranged, the electric push rod is driven by a motor, a push rod end of the electric push rod is hingedly fixed to the wing swing arm, and the other end of the wing swing arm is fixed on the wing.

3. A vertical take-off and landing electric helicopter with composite wings according to claim 1, characterized in that: Each group of lift propellers is a coaxial forward propeller and a reverse propeller, also known as a coaxial double propeller. The coaxial double propeller includes an upper lift propeller and a lower lift propeller coaxially arranged, which are controlled by a drive motor.

4. A vertical take-off and landing electric helicopter with composite wings according to claim 1, characterized in that: The lift propellers arranged on the front and rear sides of the fuselage are mounted on the fuselage through a fixed bracket; the lift propellers arranged on the left and right sides of the fuselage, each of which is mounted on the fuselage through a folding mechanism to achieve folding and unfolding of the lift propellers; Among them, the lift propellers arranged on the left and right sides of the fuselage and the lift propellers arranged on the front and rear sides of the fuselage can be arranged horizontally in a cross-staggered manner to reduce the length of the entire machine after folding.

5. A vertical take-off and landing electric helicopter with composite wings according to claim 4, characterized in that: The folding mechanism comprises: support tubes respectively arranged on the left and right sides of the machine body, a nut and a lead screw matched with the nut are arranged in the support tube, the lead screw is driven by a motor, and a nut end is connected to the end of the nut away from the lead screw; the nut end moves in the anti-rotation guide groove of the support tube, and the anti-rotation guide groove can prevent the nut from rotating; the outer end of the support tube is hinged with the rotating arm, and the nut end is movably connected with the rotating arm through a connecting rod; Through the transmission cooperation of the nut and the lead screw, 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 nut, and then converted into a pulling force or a thrust force on the connecting rod and the rotating arm.

6. A vertical take-off and landing electric helicopter with composite wings 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 nut end.

7. A vertical take-off and landing electric helicopter with composite wings according to claim 5, characterized in that: The driving motor of the lead screw is a double-output shaft motor, the lead screws and nuts on both sides cooperate, and the thread rotation directions of the two sets of lead screws and nuts are opposite, which can fold or unfold the rotating arms on the left and right sides of the machine body at the same time.

8. A vertical take-off and landing electric helicopter according to any one of claims 1 to 7, characterized in that: Electric aircraft tires are installed at the bottom of the fuselage to facilitate movement and parking after landing.

9. A vertical take-off and landing electric helicopter with composite wings according to any one of claims 1 to 7, characterized in that: The vertical take-off and landing electric helicopter can take off and land in a single lane or on the roadside, and can be parked in a single parking space after being folded.

10. A vertical take-off and landing electric helicopter with composite wings according to any one of claims 1 to 7, characterized in that: A tail wing is arranged on a fixed bracket at the rear side of the fuselage, and the tail wing is provided with a steering gear; steering gears are also arranged at both ends of the rear side of the wing, and the flight attitude of the aircraft is controlled by the steering gears.

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