Aleron assembly applied to wing of unmanned aerial vehicle

Abstract

The utility model discloses an aileron component applied to a wing of an unmanned aerial vehicle, the aileron component comprises an aileron and a steering engine for driving the aileron to turn over, one side of the wing is provided with a notch for accommodating the aileron component, and the wing is also provided with a mounting groove for accommodating the steering engine; the aileron assembly further comprises an end cover used for sealing the mounting groove, and a gap is formed between the rear end face of the steering engine and the rear side wall of the mounting groove and used for allowing the steering engine to move backwards in the mounting groove to be separated from the connecting end of the aileron. The lower end face of the end cover is provided with a protruding block extending into the gap and used for limiting the steering engine from moving backwards in the assembling state. According to the technical scheme, the steering engine is convenient to disassemble, assemble and maintain, the aileron assembly can be replaced without disassembling the whole aileron assembly from the wing, meanwhile, the aileron assembly can be prevented from being disengaged backwards in the assembling state, and therefore the structural stability and safety are better, the overall structure is simple, and implementation is easy.

Description

TECHNICAL FIELD

[0001] The utility model relates to unmanned aerial vehicle accessory technical field especially, it relates to a kind of aileron assembly applied to unmanned aerial vehicle wing. BACKGROUND

[0002] Aileron assembly on unmanned aerial vehicle wing is mainly used for roll control, and roll torque is generated by deflection in different directions, so that unmanned aerial vehicle can roll, and unmanned aerial vehicle can turn freely in the air, and it is more flexible and flexible. In the usual design, aileron assembly usually includes aileron and rudder connected by transmission, aileron is reversibly embedded in one side of wing, and rudder is embedded and installed by slotting on wing, and rudder is electrically connected to control system in fuselage by wire. But it is troublesome to assemble and take out rudder in installation slot, especially when rudder is maintained and replaced, aileron assembly needs to be removed from wing as a whole, and it is inconvenient. UTILITY MODEL CONTENTS

[0003] In view of the above problems existing in the prior art, the present application provides an aileron assembly applied to unmanned aerial vehicle wing, which can conveniently remove rudder for maintenance and replacement, to overcome the above technical defects.

[0004] The specific technical scheme is as follows:

[0005] An aileron assembly applied to unmanned aerial vehicle wing, aileron assembly includes aileron and rudder for driving aileron to reverse, one side of wing has a gap for accommodating aileron assembly, and installation slot for accommodating rudder is formed on wing.

[0006] Aileron assembly further includes an end cover for closing installation slot, and gap is formed between rear end surface of rudder and rear side wall of installation slot, to allow rudder to move in backward direction in installation slot and remove connection end of aileron. And the lower end surface of end cover has protrusion extending into gap, to limit rudder from moving backward in assembled state.

[0007] Preferably, left and right sides of rudder further protrude to form clamping block, and left and right side walls in installation slot further have clamping groove opposite to the position of clamping block, and the width of clamping groove in front and back direction is greater than the width of clamping block, so that clamping block can move in front and back direction in clamping groove and has front and back direction limit position.

[0008] Preferably, the front and back sides of lower end of protrusion are formed as inclined surface converging in downward direction.

[0009] Preferably, in assembled state, the front end surface of protrusion abuts against the rear end surface of rudder.

[0010] Preferably, the end surface of end cover facing rudder is concave and has concave surface structure matched with the shape of rudder.

[0011] Preferably, the wing comprises a frame, and a mounting seat is formed on the frame, a mounting slot is formed on the mounting seat, and the end cover is detachably mounted on the mounting seat by fasteners and closes the mounting slot.

[0012] Preferably, the aileron is provided with a connecting shaft at each of the two ends in the length direction, and the wing is provided with connecting slots opposite to the positions of the connecting shafts, so that the aileron can be reversibly mounted in the notch, and one of the connecting slots is adjacent to the mounting slot and contains a connecting sleeve, the connecting shaft extends into the connecting sleeve in the rear direction, and the output shaft of the steering engine extends into the connecting sleeve in the front direction, so that the steering engine drives the aileron.

[0013] Preferably, the inner wall of the connecting sleeve is provided with an inner tooth groove extending in the front-rear direction, and the connecting shaft and the output shaft of the steering engine are both provided with an outer gear ring matched with the shape of the inner tooth groove.

[0014] Preferably, the wing is reversibly assembled on the fuselage of the unmanned aerial vehicle.

[0015] The beneficial effects of the above technical scheme are:

[0016] The aileron assembly applied to the wing of the unmanned aerial vehicle comprises an aileron, a steering engine, and an end cover, the wing is provided with a notch and a mounting slot, the end cover closes the mounting slot, and the steering engine can move in the rear direction in the mounting slot to disengage the aileron, the lower end surface of the end cover is provided with a protrusion, and the steering engine is limited by the protrusion, so that the steering engine is convenient to disassemble, maintain, and replace without disassembling the aileron assembly from the wing as a whole, and the steering engine can be prevented from disengaging in the rear direction in the assembled state, so that the structural stability and safety are better, the overall structure is simple, and the aileron assembly is easy to realize. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 It is an exploded view of the aileron assembly and the wing of the unmanned aerial vehicle;

[0018] Figure 2 It is an exploded view of the steering engine, the end cover, and the wing frame in the aileron assembly applied to the wing of the unmanned aerial vehicle;

[0019] Figure 3 It is an assembly schematic view of the steering engine in the aileron assembly applied to the wing of the unmanned aerial vehicle;

[0020] Figure 4 It is an exploded view of the steering engine and the end cover in the aileron assembly applied to the wing of the unmanned aerial vehicle;

[0021] Figure 5 It is a perspective view of the steering engine and the frame in the aileron assembly applied to the wing of the unmanned aerial vehicle;

[0022] Figure 6The utility model discloses a specific application schematic drawing of the aileron assembly applied to the wing of the unmanned plane. DETAILED DESCRIPTION

[0023] In order to make the technical means, creation features, purposes and effects of the utility model easy to understand, the following embodiments are combined with the drawings to make a specific description of the utility model. One side of the rudder 5 connected with the aileron 4 is defined as the front side direction of the rudder 5.

[0024] Referring to Figures 1 to 6 The utility model discloses a specific application schematic drawing of the aileron assembly applied to the wing of the unmanned plane.

[0025] The aileron assembly 3 further comprises an end cover 6 for closing the mounting groove 7, and the rear end face of the rudder 5 and the rear side wall of the mounting groove 7 have a gap 16 for allowing the rudder 5 to move in the backward direction in the mounting groove 7 to disengage the connecting end of the aileron 4; and the lower end face of the end cover 6 has a protrusion 13 extending into the gap 16 for limiting the backward movement of the rudder 5 in the assembled state.

[0026] Based on the above technical scheme, the aileron assembly 3 applied to the wing of the unmanned plane comprises the aileron 4, the rudder 5 and the end cover 6, the wing 2 is provided with the gap and the mounting groove 7, the end cover 6 closes the mounting groove 7, the rudder 5 can move in the backward direction in the mounting groove 7 to disengage the aileron 4, the lower end face of the end cover 6 has the protrusion 13 for limiting the rudder 5, so that the rudder 5 is convenient to disassemble and maintain, the aileron assembly 3 can be replaced without disassembling the whole aileron assembly 3 from the wing 2, and the rudder 5 can be prevented from moving backward in the assembled state, so that the structure stability and safety are better, the overall structure is simple, and the utility model is easy to realize.

[0027] In a preferred embodiment, the left and right sides of the rudder 5 further respectively protrude to form a clamping block 9, and the left and right side walls in the mounting groove 7 are further respectively provided with a clamping groove 10 opposite to the position of the clamping block 9, and the width of the clamping groove 10 in the front and rear directions is greater than the width of the clamping block 9, so that the clamping block 9 can move in the front and rear directions in the clamping groove 10 and has the maximum stroke limit in the front and rear directions. The clamping block 9 and the clamping groove 10 can simultaneously play the roles of positioning and limiting.

[0028] As a further preferred embodiment, the front and rear sides of the lower end surface of the protrusion 13 are each formed as a downwardly converging inclined surface 14, so that during the process of closing the end cover 6, the inclined surface 14 can act as a guide surface to push the rudder 5 to move in a direction facing the aileron 4. Further, in the assembled state, the front end surface of the protrusion 13 abuts against the rear end surface of the rudder 5. Further, the end surface of the end cover 6 facing the rudder 5 is concave and has a concave surface structure 15 matching the shape of the rudder 5. Further, the wing 2 includes a frame 11, and the frame 11 has a mounting seat 12 formed thereon, and the mounting groove 7 is formed in the mounting seat 12. The end cover 6 is detachably mounted on the mounting seat 12 by fasteners to close the mounting groove 7. Specifically, the end cover 6 can be fixed by screws, but can also be fixed by a clamping structure, and is not limited thereto.

[0029] In a preferred embodiment, the two ends of the aileron 4 in the length direction each have a connecting shaft formed thereon, and the wing 2 has connecting grooves 17 formed opposite the positions of the connecting shafts, so that the aileron 4 can be installed in the gap in a flip manner, and one of the connecting grooves 17 is adjacent to the mounting groove 7 and contains a connecting shaft sleeve 8. The connecting shaft extends into the connecting shaft sleeve 8 in a rearward direction, and the output shaft 18 of the rudder 5 extends into the connecting shaft sleeve 8 in a forward direction, so that the rudder 5 drives the aileron 4. Thus, the aileron 4 is driven to flip by the rudder 5.

[0030] As a further preferred embodiment, the inner wall of the connecting shaft sleeve 8 has an inner tooth groove extending in the forward and rearward directions, and the connecting shaft and the output shaft 18 of the rudder 5 each have an outer gear ring matching the shape of the inner tooth groove, so that the three are detachably connected in transmission. However, it is obvious that the output shaft 18 and the connecting shaft sleeve 8 can also be connected in a tight fit manner. In comparison, the toothed structure can make the rudder 5 less stressed during rearward disengagement.

[0031] In a preferred embodiment, in combination with the above-mentioned Figure 6 , the wing 2 can be foldably mounted on the fuselage 1 of the unmanned aerial vehicle to facilitate folding and storage, and Figure 6 , the unmanned aerial vehicle is of a compound wing structure, but the aileron assembly 3 in the present embodiment is also applicable to other types of unmanned aerial vehicles or aircrafts, and is not limited thereto. Further, the connecting shaft sleeve 8 also has a locking hole radially formed therein for screwing in a screw to facilitate the connecting shaft sleeve being fixed to the connecting shaft.

[0032] In addition, the rudder 5 is a special motor used to drive the aileron 4 to flip in the art, which is generally cuboid in shape and has wires electrically connected to a control panel in the fuselage 1 of the unmanned aerial vehicle. The wires can be routed through a hole slot formed in the rear end surface of the mounting groove 7, which is a technology well known to those skilled in the art, and thus is omitted here.

[0033] The above merely describes preferred embodiments of the present application, which are merely illustrative but not restrictive. Those skilled in the art understand that many changes, modifications, or even equivalences can be made to the present application within the spirit and scope of the present application as defined in the claims, and all will fall within the protection scope of the present application.

Claims

1. Aileron assembly applied to the wing of a UAV, the aileron assembly comprising an aileron (4) and a steering engine (5) for driving the aileron (4) to flip, the wing (2) having a notch on one side for accommodating the aileron assembly (3), and further having a mounting groove (7) for accommodating the steering engine (5); characterized in that the aileron assembly (3) further comprises an end cover (6) for closing the mounting groove (7), and there is a gap (16) between the rear end surface of the steering engine (5) and the rear side wall of the mounting groove (7) for allowing the steering engine (5) to move in the rear direction within the mounting groove (7) and to disengage the connecting end of the aileron (4); and the lower end surface of the end cover (6) has a protrusion (13) extending into the gap (16) for limiting the rearward movement of the steering engine (5) in the assembled state. The left and right sides of the steering engine (5) further respectively protrude a clamping block (9), and the left and right side walls within the mounting groove (7) further respectively have a clamping groove (10) opposite to the position of the clamping block (9), and the width of the clamping groove (10) in the front-rear direction is greater than the width of the clamping block (9), so that the clamping block (9) can move in the front-rear direction within the clamping groove (10) and has a front-rear direction maximum stroke limit.

2. The flap assembly for use on a drone wing of claim 1, wherein, The front and rear side surfaces of the lower end of the protrusion (13) are both formed as inclined surfaces (14) converging in the downward direction.

3. The flap assembly for use on a drone wing of claim 2, wherein, In the assembled state, the front end surface of the protrusion (13) abuts against the rear end surface of the steering engine (5).

4. The flap assembly for use on a drone wing of claim 3, wherein, The end surface of the end cover (6) facing the steering engine (5) further has a concave structure (15) matching the shape of the steering engine (5).

5. The flap assembly for use on a drone wing of claim 1, wherein, The wing (2) comprises a frame (11), and the frame (11) has a mounting seat (12) formed thereon, the mounting groove (7) is formed on the mounting seat (12), and the end cover (6) is detachably mounted on the mounting seat (12) by fasteners and closes the mounting groove (7).

6. The flap assembly for use on a drone wing of claim 1, wherein, The two ends of the aileron (4) in the length direction respectively have a connecting shaft formed thereon, the wing (2) has a connecting groove (17) opposite to the position of the connecting shaft, so that the aileron (4) can be flip-mounted in the notch, and one of the connecting grooves (17) is adjacent to the mounting groove (7) and accommodates a connecting shaft sleeve (8), the connecting shaft extends into the connecting shaft sleeve (8) in the rear direction, and the output shaft (18) of the steering engine (5) extends into the connecting shaft sleeve (8) in the front direction, so that the steering engine (5) is drivingly connected to the aileron (4).

7. The flap assembly for use on a drone wing of claim 1, wherein, The inner wall of the connecting shaft sleeve (8) has an inner gear groove extending in the front-rear direction, and the connecting shaft and the output shaft (18) of the steering engine (5) both have an outer gear ring matching the shape of the inner gear groove.

8. The flap assembly for use on a drone wing of claim 7, wherein, The wing (2) can be flip-mounted on the fuselage (1) of the UAV.

9. The flap assembly for use on a drone wing of claim 1, wherein, ​

Images