CN210592408U

CN210592408U - Multi-rotor aircraft

Info

Publication number: CN210592408U
Application number: CN201921551757.4U
Authority: CN
Inventors: 张焱
Original assignee: Shenzhen Feima Robotics Co ltd
Current assignee: Shenzhen Pegasus Robotics Co ltd
Priority date: 2019-09-18
Filing date: 2019-09-18
Publication date: 2020-05-22
Anticipated expiration: 2029-09-18

Abstract

The utility model discloses a many rotor crafts, it belongs to aerospace vehicle technical field, including frame, wing and adjustment mechanism. The adjusting mechanism comprises an adjusting part fixed on the rack and a telescopic part connected with the adjusting part; the adjustment section is configured to: when the multi-rotor aircraft vertically takes off and lands, the adjusting part drives the telescopic part to contract along a first direction; when the multi-rotor aircraft flies horizontally, the adjusting part drives the telescopic part to extend along the second direction. The utility model provides a multi-rotor aircraft, when the horizontal flight, can increase the lift of the multi-rotor aircraft, make the multi-rotor aircraft have better flight ability; when the multi-rotor aircraft vertically takes off and lands, the resistance of the multi-rotor aircraft in the ascending or descending process can be reduced, so that the flight efficiency of the multi-rotor aircraft is higher.

Description

Multi-rotor aircraft

Technical Field

The utility model relates to an aerospace vehicle technical field especially relates to a many rotor crafts.

Background

The multi-rotor aircraft has the characteristics of capability of taking off and landing vertically, flexibility, mobility, high speed and efficiency and the like, and is widely applied to crowded urban areas and scenes such as field patrol, monitoring and the like with complex terrain.

In the horizontal flight process of the aircraft, the lift force generated by the wings influences the overall performance of the aircraft, the larger the lift force generated by the wings is, the less electric energy is consumed in the unit time of the aircraft, and the longer the endurance time is. In the related art, the lift generated by the wing is increased by adding the wing to the fuselage, so as to improve the performance of the aircraft.

However, with the increase of wings in the aircraft, the drag area of the aircraft is too large in the vertical take-off and landing process, and the wind resistance is larger, so that the flight efficiency and stability of the aircraft are lower.

SUMMERY OF THE UTILITY MODEL

The utility model aims at providing a multi-rotor aircraft, which can have better flight capability when the aircraft flies horizontally; in vertical take-off and landing, the device can have less resistance in the process of ascending or descending.

As the conception, the utility model adopts the technical proposal that:

a multi-rotor aircraft is provided, comprising:

a frame;

the wings are fixed on the frame;

the adjusting mechanism comprises an adjusting part fixed on the rack and a telescopic part connected with the adjusting part;

the adjustment section is configured to: when the multi-rotor aircraft vertically takes off and lands, the adjusting part drives the telescopic part to contract along a first direction; when many rotor crafts horizontal flight, the regulation part drive the pars contractilis extends along the second direction, first direction with the second direction is opposite.

Preferably, the adjusting mechanism is located above the frame, and/or the adjusting mechanism is located below the frame.

Preferably, the adjusting part comprises a fixing part fixed on the rack, a pull rod connected with the fixing part in a sliding manner, and a support rod connected with the pull rod in a rotating manner;

the telescopic part is provided with a support shaft, the support rod is fixed on the telescopic part, and one end of the support rod is rotatably connected to the support shaft;

the tie rod is configured to: when the pull rod slides on the fixing piece, the support rod can be driven to rotate around the support shaft, so that the support rod drives the telescopic part to contract or extend.

Preferably, the fixing part comprises a connecting frame fixed on the rack, a screw rod rotationally connected with the connecting frame and a sliding block in threaded connection with the screw rod, and the pull rod is connected with the sliding block; when the screw rod rotates, the sliding block can move along the screw rod.

Preferably, the pull rod is connected with the middle position of the support rod, the adjusting portion comprises two support rods and two pull rods, the two support rods are respectively located on two sides of the fixing member, and the two pull rods are respectively located on two sides of the fixing member.

Preferably, the adjusting portion further includes a driving member, and the driving member is connected to the screw rod and is configured to drive the screw rod to rotate.

Preferably, the driving piece is a driving motor or a steering engine.

Preferably, the telescopic part comprises a folding cloth or a folding plate;

when the multi-rotor aircraft vertically takes off and lands, the folding cloth or the folding plate is in a folding state; when the multi-rotor aircraft flies horizontally, the folding cloth or the folding plate is in an unfolded state.

Preferably, the shape of the folding cloth or the folding plate is a polygon.

The beneficial effects of the utility model include at least:

the utility model provides a many rotor crafts includes adjustment mechanism, and the regulating part among the adjustment mechanism can be when many rotor crafts horizontal flight, and the drive pars contractilis extends along the second direction to increase many rotor crafts's lift, make many rotor crafts have better flight ability, and can also improve many rotor crafts's time of endurance owing to the increase of lift. And, the regulating part can also drive the pars contractilis along first direction shrink when many rotor crafts fly in vertical direction to reduce many rotor crafts at the resistance of rising or decline in-process, make many rotor crafts's flight efficiency higher, stability is better.

Drawings

Fig. 1 is a schematic structural diagram i of a multi-rotor aircraft according to a first embodiment of the present invention;

fig. 2 is a schematic structural diagram of an adjusting portion and an expansion portion according to a first embodiment of the present invention;

fig. 3 is a schematic structural diagram ii of a multi-rotor aircraft according to a first embodiment of the present invention;

fig. 4 is a schematic structural diagram three of the multi-rotor aircraft according to the first embodiment of the present invention.

In the figure:

1. a frame; 2. an adjustment mechanism; 21. an adjustment section; 211. a pull rod; 212. a support bar; 213. a connecting frame; 214. a screw; 215. a slider; 216. a drive member; 217. a first bracket; 218. a second bracket; 219. a third support; 22. a telescopic part; 3. a windward plate.

Detailed Description

In order to make the technical problem solved by the present invention, the technical solution adopted by the present invention and the technical effect achieved by the present invention clearer, the technical solution of the present invention will be further explained by combining the drawings and by means of the specific implementation manner. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting of the invention. It should be further noted that, for the convenience of description, only some but not all of the elements related to the present invention are shown in the drawings.

In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance. Wherein the terms "first position" and "second position" are two different positions.

In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection or a removable connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.

The present embodiment provides a multi-rotor aircraft, referring to fig. 1 to 4, which includes a frame 1, wings (not shown), and an adjusting mechanism 2.

Wherein, the wing is fixed on the frame 1, and the frame 1 can include a frame main body and a plurality of supports. The adjusting mechanism 2 may include an adjusting portion 21 fixed to the frame body and a telescopic portion 22 connected to the adjusting portion 21. The adjusting portion 21 is configured to: when the multi-rotor aircraft vertically takes off and lands, the adjusting part 21 is used for driving the telescopic part 22 to contract along the first direction, so that the telescopic part 22 is finally in a contracted state; when the multi-rotor aircraft is flying horizontally, adjustment portion 21 is used to drive telescopic portion 22 to extend in a first direction, which is opposite to the second direction, so that telescopic portion 22 is finally in an extended state.

It should be noted that the telescopic part in this embodiment may be a folding cloth or a folding plate, and when the multi-rotor aircraft vertically takes off and lands, the folding cloth or the folding plate is in a folded state; when the multi-rotor aircraft flies horizontally, the folding cloth or the folding plate is in an unfolded state. And, multi-rotor aircraft VTOL means that multi-rotor aircraft flies in the vertical direction. And, the first direction and the second direction may be perpendicular to the vertical direction.

In conclusion, the multi-rotor aircraft that this embodiment provided includes adjustment mechanism 2, and adjustment portion 21 among adjustment mechanism 2 can drive flexible portion 22 when multi-rotor aircraft is in horizontal flight to extend along the second direction, so as to increase multi-rotor aircraft's lift for multi-rotor aircraft has better flight ability, and can also improve multi-rotor aircraft's time of endurance owing to the increase of lift. In addition, the adjusting portion 21 can also drive the telescopic portion 22 to contract along the first direction when the multi-rotor aircraft flies in the vertical direction, so as to reduce the resistance of the multi-rotor aircraft in the ascending or descending process, so that the multi-rotor aircraft has high flying efficiency and good stability.

Optionally, in this embodiment, the surface of the expansion part 22 may be a plane or a curved surface, which is not limited in this embodiment, and when the surface of the expansion part 22 is a curved surface, the expansion part 22 may have a stronger lifting force.

Referring to fig. 2, the shape of the folding cloth or the folding plate may be polygonal, so that when the multi-rotor craft flies in different directions, both the folding cloth and the folding plate can have streamlines with smaller resistance and can generate larger lift force.

In this embodiment, the multi-rotor aircraft may include one or more adjusting mechanisms 2, and when the multi-rotor aircraft includes one adjusting mechanism 2, the one adjusting mechanism 2 may be located above the airframe 1, or the one adjusting mechanism 2 may also be located below the airframe 1, which is not limited in this embodiment. When the multi-rotor aircraft includes a plurality of adjustment mechanisms 2, the plurality of adjustment mechanisms 2 may include an adjustment mechanism 2 located above airframe 1 and an adjustment mechanism 2 located below airframe 1, and may further include an adjustment mechanism 2 located in front of or behind airframe 1, which is not limited in this embodiment. Fig. 1 is a schematic view of a multi-rotor aircraft including one adjustment mechanism 2, and the one adjustment mechanism 2 is located above a airframe 1. Wherein, the upper part of the frame 1 can include the right upper part, the left upper part, the right upper part, the front upper part or the back upper part of the frame 1, etc.; the lower side of the rack 1 may include a right lower side, a left lower side, a right lower side, a front lower side, a rear lower side, or the like of the rack 1.

Further, adjustment mechanism 2 can be located directly over frame 1 or under, and at this moment, adjustment mechanism 2 and frame 1 are located same vertical direction for many rotor crafts can be less because of the windage area that installation adjustment mechanism 2 increased, and then make the resistance that many rotor crafts increase when VTOL can be less, has improved many rotor crafts's flight efficiency.

Alternatively, referring to fig. 2, the adjusting portion 21 may include a fixing member fixed on the frame 1, a pull rod 211 slidably connected to the fixing member, and a support rod 212 rotatably connected to the pull rod 211. The telescopic part 22 is provided with a supporting shaft which is rotatably connected with one end of the supporting rod, and the supporting rod is fixed on the telescopic part 22. Alternatively, as shown in fig. 2, the pull rod 211 is rotatably connected to the middle of the support rod 212, and the adjusting mechanism 2 provided in this embodiment includes two pull rods 211 and two support rods 212, the two pull rods 211 are distributed on two sides of the fixing member, the two support rods 212 are also distributed on two sides of the fixing member, and one end of each of the two support rods 212 is rotatably connected to the support shaft, that is, the two support rods 212 are disposed in a V shape, and the fixing member is located at the opening position of the two support rods 212.

For example, a U-shaped bracket may be disposed in the middle of the supporting rod 212, a first through hole is disposed on two supporting plates of the U-shaped bracket, a second through hole is disposed at one end of the pull rod 211 for connecting to the supporting rod 212, and a pin passes through the first through hole and the second through hole to enable the pull rod 211 to be rotatably connected to the supporting rod 212, so that the pull rod 211 can rotate relative to the supporting rod 212.

Optionally, two windward plates 3 are further disposed on the telescopic portion, the two windward plates 3 are disposed in a V shape, and the support shaft 212 is located in a space enclosed by the two windward plates 3 and fixed to the two windward plates 3.

Further, the tie rod 211 is configured to: when the pull rod 211 slides on the fixing member, the support rod 212 can be driven to rotate around the support shaft, so that the support rod 212 drives the telescopic portion 22 to contract or extend. For example, when the pull rod 211 slides to one end of the fixing member, the support rod 212 located at one side of the fixing member can be driven to rotate clockwise, and the support rod 212 located at the other side of the fixing member can rotate counterclockwise, so as to drive the telescopic portion 22 to contract; when the pull rod 211 slides to the other end of the fixing member, the support rod 212 on one side of the fixing member can be driven to rotate counterclockwise, and the support rod 212 on the other side of the fixing member can rotate clockwise, so as to drive the expansion part 22 to extend. Therefore, when the multi-rotor aircraft vertically takes off and lands, the pull rod 211 can be controlled to slide towards one end of the fixing piece, so that the telescopic part 22 is contracted, and the wind resistance of the multi-rotor aircraft is reduced. When the multi-rotor aircraft flies horizontally, the pull rod 211 can be controlled to slide towards the other end of the fixing piece, so that the telescopic part 22 is extended to increase the lift force of the multi-rotor aircraft.

With continued reference to fig. 2, the fixing member may include a connecting frame 213 fixed on the frame 1, a screw 214 rotatably connected to the connecting frame 213, and a sliding block 215 threadedly connected to the screw 214, and the pull rod 211 is rotatably connected to the sliding block 215. When the screw 214 rotates, the slider 215 can move along the screw 214. At this time, the screw 214 is controlled to rotate, so that the pull rod 211 connected with the slider 215 slides on the screw 214, and the pull rod 211 slides relative to the fixed member.

For example, the matching relationship between the sliding block 215 and the screw 214 may be: when the screw 214 rotates clockwise, the slider 215 slides towards one end of the screw 214 (e.g. the right end of the screw 214 in fig. 2), and the two support rods 212 move towards each other under the action of the pull rod 211 due to the rotational connection of the pull rod 211 and the support rods 212, so that the telescopic part 22 contracts; when the screw 214 rotates counterclockwise, the slider 215 slides toward the other end of the screw 214 (e.g., the left end of the screw 214 in fig. 2), and the two support rods 212 move away from each other under the action of the pull rod 211 due to the rotational connection between the pull rod 211 and the support rods 212, so that the telescopic part 22 is extended.

Optionally, in the present embodiment, referring to fig. 2, the adjusting portion 21 further includes a driving member 216, and the driving member 216 is connected to the screw 214 and is used for driving the screw 214 to rotate. The driving member 216 can drive the screw 214 to rotate forward or backward, that is, the screw 214 can rotate clockwise or counterclockwise. The drive 216 can be wirelessly connected to a controller at the surface so that the controller can control how and when the drive 216 rotates.

Continuing with the above example, when the multi-rotor aircraft is vertically raised, the controller may control actuator 216 to apply a clockwise force to screw 214, thereby causing retraction 22 to retract. When the multi-rotor aircraft is flying horizontally, the controller may control actuator 216 to apply a force to screw 214 that causes it to rotate counterclockwise, thereby extending telescoping section 22. The automatic control of the adjusting mechanism 2 of the multi-rotor aircraft is realized, and the flexibility of the multi-rotor aircraft is increased. The driving member 216 may be a driving motor, a steering engine, or other device capable of driving the screw to rotate.

Alternatively, the drive member 216 may be controlled without a controller. Illustratively, the driving member 216 includes a regulating unit, a detecting unit electrically connected to the regulating unit, and a driving unit connected to the regulating unit and the screw 214. The detection unit is used for detecting the direction of force exerted on the multi-rotor aircraft by air. When the direction of the force exerted on the multi-rotor aircraft by the air is the vertical direction, it indicates that the multi-rotor aircraft is in a vertical take-off and landing state, and at this time, the detection unit transmits the signal to the control unit, so that the control unit controls the driving unit to drive the screw 214 to rotate clockwise, so that the telescopic portion 22 is contracted. When the direction of the force exerted on the multi-rotor aircraft by the air is the horizontal direction, it indicates that the multi-rotor aircraft is in the horizontal flight state, and at this time, the detection unit transmits the signal to the control unit, so that the control unit controls the driving unit to drive the screw 214 to rotate counterclockwise, so that the expansion part 22 extends.

Further, referring to fig. 1 to 3, the connection frame 213 may include a first support 217, a second support 218, and a third support 219, and one end of the first support 217 is connected to the rack 1, and the other end is connected to the second support 218. The second bracket 218 is used for fixing the driving member 216 and the screw 214, and illustratively, one end of the screw 214 is rotatably connected with the second bracket 218, and the other end of the screw 214 is connected with the driving member 216. The third bracket 219 is coupled to the second bracket 218, and one end of the third bracket 219 is coupled to the support shaft.

Optionally, the multi-rotor aircraft in this embodiment may be a multi-rotor drone, a multi-rotor aircraft, or the like.

The present embodiment provides a control method of a multi-rotor aircraft for controlling the multi-rotor aircraft in the above-described embodiments. The method comprises the following steps:

when the multi-rotor aircraft vertically takes off and lands, the control adjusting part 21 drives the telescopic part 22 to contract along the first direction, so that the telescopic part 22 is in a contracted state. When the multi-rotor aircraft flies horizontally, the control and adjustment part 21 drives the telescopic part 22 to extend along a second direction, which is opposite to the first direction, so that the telescopic part 22 is in an extended state.

For example, the present embodiment takes the multi-rotor aircraft in the first embodiment as an example, and a simple description is given to a manner of controlling the flight of the multi-rotor aircraft.

During vertical take-off and landing of the multi-rotor aircraft, the user can control the driving member 216 to rotate clockwise through the controller, and at this time, the screw 214 follows the driving member 216 to rotate clockwise. The sliding block 215 sleeved on the screw 214 slides towards one end of the screw 214 to drive the pull rod 211 to move towards one end of the screw 214, and further drive the two support rods 212 to move towards the direction close to each other, so that the folding cloth or the folding plate is folded.

During horizontal flight of the multi-rotor aircraft, the user can control the driving member 216 to rotate in the counterclockwise direction through the controller, and at this time, the screw 214 follows the driving member 216 to rotate in the counterclockwise direction. The sliding block 215 sleeved on the screw 214 slides towards the other end of the screw 214 to drive the pull rod 211 to move towards the other end of the screw 214, and further drive the two support rods 212 to move towards the direction away from each other, so that the folding cloth or the folding plate is unfolded.

The above embodiments have been described only the basic principles and features of the present invention, and the present invention is not limited by the above embodiments, and is not departing from the spirit and scope of the present invention. The scope of the invention is defined by the appended claims and equivalents thereof.

Claims

1. A multi-rotor aircraft, comprising:

a frame (1);

the wings are fixed on the frame (1);

the adjusting mechanism (2) comprises an adjusting part (21) fixed on the frame (1) and a telescopic part (22) connected with the adjusting part (21);

the adjustment section (21) is configured to: when the multi-rotor aircraft vertically takes off and lands, the adjusting part (21) drives the telescopic part (22) to contract along a first direction; when the multi-rotor aircraft flies horizontally, the adjusting part (21) drives the telescopic part (22) to extend along a second direction, and the first direction is opposite to the second direction.

2. Multi-rotor aircraft according to claim 1, wherein the adjustment mechanism (2) is located above the airframe (1) and/or wherein the adjustment mechanism (2) is located below the airframe (1).

3. The multi-rotor aircraft according to claim 2, wherein the adjustment portion (21) comprises a fixed member fixed to the frame (1), a tie rod (211) slidably connected to the fixed member, and a support rod (212) rotatably connected to the tie rod (211);

a support shaft is arranged on the telescopic part (22), the support rod (212) is fixed on the telescopic part (22), and one end of the support rod (212) is rotatably connected to the support shaft;

the tie rod (211) is configured to: when the pull rod (211) slides on the fixing piece, the support rod (212) can be driven to rotate around the support shaft, so that the support rod (212) drives the telescopic part (22) to contract or extend.

4. The multi-rotor aircraft according to claim 3, wherein the fixed part comprises a connecting frame (213) fixed to the frame (1), a threaded rod (214) rotatably connected to the connecting frame (213), and a sliding block (215) screwed to the threaded rod (214), the tie rod (211) being rotatably connected to the sliding block (215); when the screw rod (214) rotates, the sliding block (215) can move along the screw rod (214).

5. The multi-rotor aircraft according to claim 4, wherein the tie rod (211) is connected to a middle position of the support rod (212), and the adjustment portion (21) comprises two support rods (212) and two tie rods (211), the two support rods (212) being located on both sides of the fixed member, respectively, and the two tie rods (211) being located on both sides of the fixed member, respectively.

6. Multi-rotor aircraft according to claim 4 or 5, wherein the adjustment portion (21) further comprises a drive member (216), the drive member (216) being connected to the screw (214) for rotating the screw (214).

7. A multi-rotor aircraft according to claim 6, wherein the drive member (216) is a drive motor or a steering engine.

8. Multi-rotor aircraft according to any of claims 1 to 5, wherein the telescopic part (22) is a folded cloth or a folded plate;

9. The multi-rotor aerial vehicle of claim 8, wherein the folded cloth or the folded plate is polygonal in shape.