Vertical take-off and landing electric helicopter

Abstract

The utility model relates to the technical field of helicopters, in particular to a vertical take-off and landing electric helicopter which comprises a helicopter body, a plurality of groups of lift propellers are arranged on the front side and the rear side of the helicopter body respectively, a plurality of groups of lift propellers are arranged on the left side and the right side of the helicopter body respectively, the lift propellers are driven by a motor, and the motor is powered by a battery pack. The lifting force paddles arranged on the left side and the right side of the machine body are folding type lifting force paddles. By arranging a plurality of groups of folding lift propellers on the left side and the right side of the helicopter body, 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. Due to the fact that the foldable lift force paddles are adopted, the foldable lift force paddles are unfolded during sailing and folded before landing or after landing, the flexible structural performance is embodied, and the foldable lift force paddles can take off and land on a single lane and the roadside and are high in adaptive capacity. After the folding lift propellers are folded, the size of the helicopter in the width direction and the length direction is similar to the size of a common automobile, and the helicopter can be parked in a single parking space.

Description

Technical Field

[0001] This utility model relates to the field of helicopter technology, specifically to a vertical take-off and landing electric helicopter. Background Technology

[0002] Currently, rotorcraft helicopters have been widely used since their utility model was put into service. Their core advantages are that they can achieve vertical take-off and landing, hover in the air, and move horizontally, vertically, horizontally, and forward and backward, as well as roll. They are used in both military and civilian fields. Although the advantages are significant, the disadvantages are also prominent. Take-off and landing require dedicated sites. In addition, existing helicopters have a large external structure and require a large dedicated site for parking after landing, which is very unfavorable for the promotion of helicopters. Utility Model Content

[0003] One of the main objectives of this invention is to overcome at least one defect in the prior art and provide a vertical take-off and landing electric helicopter.

[0004] To achieve the above technical solution, the present invention adopts the following technical solution:

[0005] According to one aspect of the present invention, a vertical take-off and landing electric helicopter is provided, including a fuselage, a plurality of lifting rotors are respectively arranged on the front and rear sides of the fuselage, and a plurality of lifting rotors are respectively arranged on the left and right sides of the fuselage. The lifting rotors are driven by a motor to generate upward lift, and the motor is powered by a battery pack.

[0006] The lift propellers located on the left and right sides of the fuselage are folding lift propellers. These folding lift propellers can extend outwards to increase the pitch, improve the aircraft's resistance to crosswinds, and enhance its safety.

[0007] According to one embodiment of the present invention, each set of lifting propellers consists of a coaxial positive propeller and a negative propeller, also known as a coaxial dual propeller, with a double-layer structure; the coaxial dual propeller includes an upper lifting propeller and a lower lifting propeller arranged coaxially, controlled by a drive motor; specifically, the upper lifting propeller and the lower lifting propeller are each controlled by a drive motor.

[0008] According to one embodiment of the present invention, the lift propellers disposed on the front and rear sides of the body are mounted on the body by means of fixed brackets; the lift propellers disposed on the left and right sides of the body are each mounted on the body 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.

[0009] The lift propellers located on the left and right sides of the fuselage are arranged horizontally and staggered with the lift propellers located on the front and rear sides of the fuselage to reduce the length of the fuselage after folding.

[0010] 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; 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.

[0011] 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.

[0012] According to one embodiment of the present invention, the machine body is generally provided with two seats, which are arranged in front of each other or side by side.

[0013] 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.

[0014] 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.

[0015] According to one embodiment of the present invention, the motor is connected to the lead screw via a coupling.

[0016] According to one embodiment of the present invention, the vertical take-off and landing electric helicopter, after being folded up, can take off and land in a single lane and park in a single parking space.

[0017] According to one embodiment of the present invention, the vertical take-off and landing electric helicopter can take off and land on a single lane or roadside to adapt to various applications.

[0018] 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.

[0019] According to one embodiment of the present invention, an electric aircraft tire is provided at the bottom of the fuselage to facilitate movement and parking after landing.

[0020] As can be seen from the above technical solution, this utility model possesses at least one of the following advantages and positive effects:

[0021] In this application, by setting several sets of folding lift rotors on the left and right sides of the fuselage, the rotor pitch of the helicopter is increased, the helicopter's resistance to crosswinds is improved, and the safety performance of the aircraft is enhanced.

[0022] Thanks to its retractable lift rotor, which unfolds during flight and folds up before or after landing, the helicopter exhibits highly flexible structural performance and strong adaptability. When the retractable lift rotor is folded up, 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 it to take off and land on single-lane roads or roadside areas.

[0023] 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

[0024] To more clearly illustrate the technical solutions in the embodiments of this utility model 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.

[0025] Figure 1 This is a top view of a vertical take-off and landing electric helicopter according to the present invention, wherein the foldable lift rotors located on the left and right sides of the fuselage are in the deployed state.

[0026] Figure 2 for Figure 1 Another top view of a vertical takeoff and landing electric helicopter, in which the foldable lift rotors located on the left and right sides of the fuselage are in the folded state.

[0027] Figure 3 for Figure 2 A front view of a vertical takeoff and landing electric helicopter;

[0028] Figure 4 This is a perspective view of a vertical take-off and landing electric helicopter according to the present invention.

[0029] Figure 5 This is a schematic diagram of the folding mechanism described in this utility model, wherein the folding mechanisms located on the left and right sides of the machine body are in a semi-open state.

[0030] The annotations in the attached figures are explained as follows:

[0031] 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. Detailed Implementation

[0032] In the description of this utility model, 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 this utility model 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 this utility model.

[0033] In the description of this utility model, 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 utility model according to the specific circumstances.

[0034] It should be noted that the terms "first," "second," etc., used in the specification, claims, and accompanying drawings of this utility model 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 this utility model described herein.

[0035] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments.

[0036] See appendix Figures 1-5 As shown, this application discloses a vertical takeoff and landing electric helicopter, including a fuselage 1, lift rotors 2, a fixed support 3, a folding mechanism 4, and aircraft tires 5. 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 motor to generate upward lift, and the motor is powered by a battery pack.

[0037] 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. Specifically, the upper lift propeller 21 and the lower lift propeller 22 are each controlled by a drive motor.

[0038] In this application, the lift rotors 2, located on the front and rear sides of the fuselage 1, are mounted on the fuselage 1 via fixed brackets 3. The lift rotors 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 rotors to achieve the folding and unfolding of the left and right lift rotors 2. The lift rotors on the left and right sides of the fuselage 1 are arranged horizontally and intersecting with those on the front and rear sides of the fuselage 1 to reduce the overall length of the aircraft after folding. The folding lift rotors can extend outwards to increase the pitch, improve the aircraft's crosswind resistance, and enhance aircraft safety. Figure 5 As shown, 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 43 can be converted into the linear motion of the lead screw nut 42, and then into a pulling or pushing force on the connecting rod 46 and the rotating arm 47.

[0039] In this application, the fuselage 1 is equipped with two seats, which can be 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, which is 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.

[0040] like Figure 5 As shown, Figure 5 This is a schematic diagram of the folding mechanism described in this utility model, wherein 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 and fixed to the rotating arm 47, and the other end is hinged and fixed to the end of the nut 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 respectively; when the nut 43 moves linearly, it will not rotate, ensuring that the connecting rod 46 and the rotating arm 47 are deployed safely and efficiently.

[0041] In the appendix Figure 5In this configuration, the dual-output shaft motor 44 can simultaneously deploy the rotating arms 47 on both 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 via a coupling 48. It should be noted that... Figure 5 The lead screws 42 on the upper side of the dual output shaft motor 44 are left-hand lead screws and right-hand lead screws, respectively. When the dual output shaft motor 44 rotates forward or reverse, it can drive the lead screws and nuts on both sides to rotate simultaneously, which is then converted into a pushing and pulling 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.

[0042] 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.

[0043] like Figures 1-4 As shown, 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.

[0044] 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.

[0045] In summary, this application, by arranging several sets of folding lift rotors on both sides of the fuselage, reduces the overall width of the helicopter when folded, facilitating parking in a single parking space and enabling takeoff and landing on single-lane roads or roadside locations. When deployed, the folding lift rotors increase the rotor pitch on both sides of the helicopter, improving its resistance to crosswinds and enhancing its safety performance. The use of folding lift rotors, which can be deployed during flight and folded before or after landing, demonstrates a highly flexible structural design and strong adaptability.

[0046] It should be understood that this invention is not limited to the detailed structure and arrangement of the components presented herein. This 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 implementing this invention and will enable those skilled in the art to utilize this invention.

Claims

1. A vertical take-off and landing electrically powered helicopter comprising a fuselage, characterised in that, The body is provided with a plurality of groups of lift propellers on the front and rear sides, and a plurality of groups of lift propellers on the left and right sides, the lift propellers are driven by motors, and the motors are powered by a battery pack. The lift propellers provided on the left and right sides of the body are folding lift propellers.

2. A vertical take-off and landing electrically powered helicopter as claimed in claim 1 wherein, Each group of the lift propellers is a coaxial positive propeller and a coaxial negative propeller, also known as coaxial double propellers, and the coaxial double propellers include coaxially arranged upper lift propellers and lower lift propellers, which are controlled by a driving motor.

3. The vertical take-off and landing electrically powered helicopter of claim 1, wherein, The lift propellers provided on the front and rear sides of the body are mounted on the body by fixed supports, and the lift propellers provided on the left and right sides of the body are mounted on the body by folding mechanisms to realize folding and unfolding of the lift propellers. The lift propellers provided on the left and right sides of the body and the lift propellers provided on the front and rear sides of the body can be horizontally crossed and arranged in a staggered manner to reduce the length of the whole machine after folding.

4. A vertical take-off and landing electrically powered helicopter as claimed in claim 3 wherein, The folding mechanism includes support pipes provided on the left and right sides of the body, a nut and a lead screw matched with the nut arranged in the support pipes, the lead screw is driven by a motor, and the nut end is provided at one end of the nut away from the lead screw; the nut end moves in an anti-rotation guide groove of the support pipe, and the anti-rotation guide groove can prevent the nut from rotating; the outer end of the support pipe is hinged to a rotating arm, and the nut end is movably connected to the rotating arm through a connecting rod. Through the transmission cooperation of the nut and the lead screw, and the anti-rotation function of the anti-rotation guide groove, the rotary motion of the lead screw can be converted into the linear motion of the nut, and then converted into the pulling force or pushing force on the connecting rod and the rotating arm.

5. A vertical take-off and landing electrically powered helicopter as claimed in claim 4 wherein, The connecting rod is preferably an L-shaped connecting rod; one end of the connecting rod is hingedly fixed to the rotating arm, and the other end is hingedly fixed to the nut end.

6. A vertical take-off and landing electrically powered helicopter as claimed in claim 4 wherein, The driving motor of the lead screw is a double-output shaft motor, the lead screws on the two sides are matched with the nuts, the threads of the two groups of lead screw nuts are opposite, and the rotating arms on the left and right sides of the body can be folded or unfolded at the same time.

7. The vertical take-off and landing electrically powered helicopter of claim 1, wherein, Two seats are generally arranged in the body, and the two seats are arranged in front of and behind each other or side by side.

8. A vertical take-off and landing electrically powered helicopter as claimed in any one of claims 1 to 7, characterised in that, An electric airplane tire is arranged at the bottom of the body to facilitate movement and parking after landing.

9. A vertical take-off and landing electrically powered helicopter as claimed in any one of claims 1 to 7, characterised in that, The vertical take-off and landing electric helicopter can take off and land on a single lane, a roadside, and be parked in a single parking space after folding.

10. A vertical take-off and landing electrically powered helicopter as claimed in any one of claims 1 to 7, characterised in that, A parachute is arranged at the top of the body to ensure safe landing in case of failure, thereby improving safety performance.

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