Power arm of composite wing unmanned aerial vehicle

Abstract

The utility model discloses a composite wing unmanned aerial vehicle power arm, belongs to the technical field of unmanned aerial vehicles, and solves the problems that an existing power arm is redundant in structure, large in weight and high in cost. And the upper skin comprises a plurality of layers of mutually attached twill carbon cloth. The lower skin comprises a plurality of layers of mutually attached twill carbon cloth, and two motor base installation grooves are formed in the lower skin. The main force bearing framework comprises a motor base beam, four beams and a plurality of power arm frames. And the four beams are arranged in a rectangular array. The multiple power arm frames are arranged in the inner space formed by the four beams at intervals in the length direction of the beams, and each power arm frame is connected with the four beams. The two ends of the two beams connected with the lower skin are each connected with a motor base beam. And the shape of the motor base beam is matched with the outer wall of the motor base mounting groove. And a motor mounting seat is mounted in each motor seat mounting groove. The structure redundancy phenomenon is avoided, the weight of the power arm is reasonably distributed, and the weight and cost of the power arm are reduced.

Description

Technical Field

[0001] The present application relates to the technical field of unmanned aerial vehicles, and in particular to a composite wing unmanned aerial vehicle power arm. Background Art

[0002] UAVs are unmanned aircraft controlled by radio remote control equipment and self-contained program control devices. They can be divided into military and civilian applications. At present, composite-wing UAVs have the advantages of vertical take-off and landing capabilities and long flight time, so composite-wing UAVs have gradually become the focus of the UAV field.

[0003] At present, the power arm of composite wing UAV usually adopts the method of hard shell skin paving, and local thickening is done in the main load-bearing area of ​​the power to ensure the load requirements of the UAV. However, due to the large difference in local loads of the power arm, the power arm paved with hard shell skin not only has structural redundancy, but also makes the power arm heavy and costly. Utility Model Content

[0004] The embodiment of the present application solves the problems of redundant structure, heavy weight and high cost of existing power arms by providing a composite wing UAV power arm.

[0005] The utility model embodiment provides a composite wing UAV power arm, which comprises an upper skin, a lower skin, a motor mounting seat and a main load-bearing frame; the upper skin comprises multiple layers of twill carbon cloth bonded to each other; the lower skin comprises multiple layers of twill carbon cloth bonded to each other, and two motor mounting grooves are arranged on the lower skin; the upper skin and the lower skin are connected to form a sealed space, and the main load-bearing frame is located in the sealed space; the main load-bearing frame comprises a motor seat beam, four beams and a plurality of power arm frames; the four beams are arranged in a rectangular array; a plurality of power arm frames are arranged at intervals along the length direction of the beams in the internal space formed by the four beams, and each power arm frame is connected to the four beams; the two ends of the two beams connected to the lower skin are respectively connected to a motor seat beam; the shape of the motor seat beam matches the outer wall of the motor seat mounting groove; and a motor mounting seat is respectively installed in each motor seat mounting groove.

[0006] In a possible implementation, the upper skin includes four layers of twill carbon cloth bonded to each other; the angle between the fiber direction of the first layer of twill carbon cloth and the main force direction of the power arm is 45°; the angle between the fiber direction of the second layer of twill carbon cloth and the main force direction of the power arm is 0°; the angle between the fiber direction of the third layer of twill carbon cloth and the main force direction of the power arm is 0°; the angle between the fiber direction of the fourth layer of twill carbon cloth and the main force direction of the power arm is 45°.

[0007] In a possible implementation, the lower skin includes four layers of twill carbon cloth bonded to each other; the angle between the fiber direction of the first layer of twill carbon cloth and the main force direction of the power arm is 45°; the angle between the fiber direction of the second layer of twill carbon cloth and the main force direction of the power arm is 0°; the angle between the fiber direction of the third layer of twill carbon cloth and the main force direction of the power arm is 0°; the angle between the fiber direction of the fourth layer of twill carbon cloth and the main force direction of the power arm is 45°.

[0008] In a possible implementation, the lower skin also includes a first thickened twill carbon cloth and a second thickened twill carbon cloth; the first thickened twill carbon cloth and the second thickened twill carbon cloth are both arranged at the installation position of the motor mounting seat; the first thickened twill carbon cloth and the second thickened twill carbon cloth are bonded to each other, and the first thickened twill carbon cloth and the second thickened twill carbon cloth are located between the second layer of twill carbon cloth and the third layer of twill carbon cloth; the angle between the fiber direction of the first thickened twill carbon cloth and the main force direction of the power arm is 45°; the angle between the fiber direction of the second thickened twill carbon cloth and the main force direction of the power arm is 45°.

[0009] In a possible implementation, the angle between the motor mounting surface of the motor mounting seat and the horizontal plane is 4°.

[0010] One or more technical solutions provided in the embodiments of the present utility model have at least the following technical effects or advantages:

[0011] The utility model provides a composite wing UAV power arm, which includes an upper skin, a lower skin, a motor mounting seat and a main load-bearing frame. The upper skin includes multiple layers of twill carbon cloth that are bonded to each other. The lower skin includes multiple layers of twill carbon cloth that are bonded to each other, and two motor mounting grooves are arranged on the lower skin. After the upper skin and the lower skin are connected, a sealed space is formed, and the main load-bearing frame is located in the sealed space. The main load-bearing frame includes a motor seat beam, four beams and a plurality of power arm frames. The four beams are arranged in a rectangular array. A plurality of power arm frames are arranged at intervals in the internal space formed by the four beams along the length direction of the beams, and each power arm frame is connected to the four beams. The two ends of the two beams connected to the lower skin are respectively connected to a motor seat beam. The shape of the motor seat beam matches the outer wall of the motor seat mounting groove. A motor mounting seat is respectively installed in each motor seat mounting groove. In actual application, the upper and lower skins are first made by mold paving, and then the lower skin and the two beams are connected by glue, and then the motor seat beam is installed, and then the power arm frame is installed, and then the remaining two beams are installed, and finally the upper skin and the lower skin are connected by glue and the motor mounting seat is installed. This application reduces the thickness of the power arm skin, and at the same time strengthens the concentrated load position of the power arm with the power arm frame, expanding the application of the power arm in composite wing UAVs. At the same time, this application avoids the phenomenon of structural redundancy, makes the weight of the power arm reasonably distributed, and reduces the weight and cost of the power arm. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] In order to more clearly illustrate the technical solutions of the embodiments of the utility model, the drawings required for use in the description of the embodiments of the utility model will be briefly introduced below. Obviously, the drawings described below are some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0013] Figure 1 An exploded view of a composite wing UAV power arm provided in an embodiment of the present application;

[0014] Figure 2 A schematic diagram of the structure of the lower skin, beam, motor seat beam and power arm frame provided in the embodiment of the present application;

[0015] Figure 3 A schematic diagram of the structure of a composite wing UAV power arm provided in an embodiment of the present application;

[0016] Figure 4 for Figure 3 AA section view in the figure;

[0017] Figure 5 A schematic diagram of the structure of the power arm frame provided in an embodiment of the present application.

[0018] Icon: 1-upper skin; 2-lower skin; 21-motor seat mounting groove; 3-beam; 4-motor seat beam; 5-power arm frame; 6-motor mounting seat. DETAILED DESCRIPTION

[0019] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0020] In the description of the embodiments of the present utility model, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inside", "outside", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the embodiments of the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present utility model. The terms "first", "second", and "third" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance. In addition, the terms "installed", "connected", and "connected" 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 it can be indirectly connected through an intermediate medium, or it can be a connection between the two elements. For ordinary technicians in this field, the specific meanings of the above terms in the embodiments of the present utility model can be understood according to specific circumstances.

[0021] like Figures 1 to 5 As shown, an embodiment of the utility model provides a composite wing UAV power arm, which includes an upper skin 1, a lower skin 2, a motor mounting seat 6 and a main load-bearing frame. The upper skin 1 includes multiple layers of twill carbon cloth that are bonded to each other. The lower skin 2 includes multiple layers of twill carbon cloth that are bonded to each other, and two motor seat mounting grooves 21 are provided on the lower skin 2. The upper skin 1 and the lower skin 2 are connected to form a sealed space, and the main load-bearing frame is located in the sealed space. In actual applications, the upper skin 1 and the lower skin 2 are paved and manufactured on a mold.

[0022] like Figure 1 As shown, the main load-bearing skeleton includes a motor seat beam 4, four beams 3 and a plurality of power arm frames 5. The four beams 3 are arranged in a rectangular array. In practical applications, the beams 3 can resist tension and transfer loads to evenly transfer force to the power arm. The beams 3 are cut and formed from 3K carbon fiber square tube profiles with a thickness of 1 mm and a size of 15 mm × 15 mm.

[0023] In the embodiment of the present application, a plurality of power arm frames 5 are arranged in the inner space formed by four beams 3 at intervals along the length direction of the beam 3, and each power arm frame 5 is connected to the four beams 3. The four corners of the power arm frame 5 are provided with limit slots for clamping the beam 3, and the beam 3 is clamped into the limit slot and clamped with the power arm frame 5, and then glue is filled between the power arm frame 5 and the beam 3. Specifically, the power arm frame 5 is an aluminum alloy machined part. In actual application, the power arm frame 5 is arranged at a position where the beam 3 is subjected to greater force.

[0024] In the embodiment of the present application, two ends of the two beams 3 connected to the lower skin 2 are respectively connected to a motor seat beam 4. The shape of the motor seat beam 4 matches the outer wall of the motor seat mounting groove 21. The motor seat beam 4 is molded to conform to the motor mounting area of ​​the lower skin 2 to ensure that the shape of the motor seat beam 4 matches the outer wall of the motor seat mounting groove 21, so that the motor seat mounting groove 21 can transfer the force received to the motor seat beam 4, and the motor seat beam 4 transfers the force to the beam 3 to evenly transfer the force to the power arm to ensure that the power arm is evenly stressed. Specifically, the motor seat beam 4 adopts a 3K carbon fiber square tube with a thickness of 1 mm and a size of 17 mm × 17 mm. In actual applications, the motor seat beam 4 and the beam 3 are connected by viscose.

[0025] In the embodiment of the present application, a motor mounting seat 6 is respectively installed in each motor mounting groove 21. Specifically, the motor mounting seat 6 is an aluminum alloy machined part. The motor mounting seat 6 is connected to the motor mounting groove 21 by adhesive.

[0026] The utility model provides a composite wing UAV power arm, which includes an upper skin 1, a lower skin 2, a motor mounting seat 6 and a main load-bearing frame. The upper skin 1 includes multiple layers of twill carbon cloth that are bonded to each other. The lower skin 2 includes multiple layers of twill carbon cloth that are bonded to each other, and two motor seat mounting grooves 21 are arranged on the lower skin 2. After the upper skin 1 and the lower skin 2 are connected, a sealed space is formed, and the main load-bearing frame is located in the sealed space. The main load-bearing frame includes a motor seat beam 4, four beams 3 and a plurality of power arm frames 5. The four beams 3 are arranged in a rectangular array. A plurality of power arm frames 5 are arranged in an internal space formed by four beams 3 at intervals along the length direction of the beams 3, and each power arm frame 5 is connected to four beams 3. Two ends of the two beams 3 connected to the lower skin 2 are respectively connected to a motor seat beam 4. The shape of the motor seat beam 4 matches the outer wall of the motor seat mounting groove 21. A motor mounting seat 6 is respectively installed in each motor seat mounting groove 21. In actual application, the upper skin 1 and the lower skin 2 are first made by mold paving, and then the lower skin 2 and the two beams 3 are connected by glue, and then the motor seat beam 4 is installed, and then the power arm frame 5 is installed, and then the remaining two beams 3 are installed, and finally the upper skin 1 and the lower skin 2 are connected by glue and the motor mounting seat 6 is installed. This application reduces the thickness of the power arm skin, and at the same time strengthens the concentrated load position of the power arm with the power arm frame 5, expanding the application of the power arm in the composite wing UAV. At the same time, this application avoids the structural redundancy phenomenon, makes the weight of the power arm reasonably distributed, and reduces the weight and cost of the power arm.

[0027] In an embodiment of the present application, the upper skin 1 includes four layers of twill carbon cloth bonded to each other. The angle between the fiber direction of the first layer of twill carbon cloth and the main force direction of the power arm is 45°. The angle between the fiber direction of the second layer of twill carbon cloth and the main force direction of the power arm is 0°. The angle between the fiber direction of the third layer of twill carbon cloth and the main force direction of the power arm is 0°. The angle between the fiber direction of the fourth layer of twill carbon cloth and the main force direction of the power arm is 45°. Specifically, the twill carbon cloth uses T300 twill carbon cloth, and its thickness is 0.2 mm. By limiting the angle between the fiber directions of the four layers of twill carbon cloth, the laying strength of the upper skin 1 can be improved.

[0028] In an embodiment of the present application, the lower skin 2 includes four layers of twill carbon cloth bonded to each other. The angle between the fiber direction of the first layer of twill carbon cloth and the main force direction of the power arm is 45°. The angle between the fiber direction of the second layer of twill carbon cloth and the main force direction of the power arm is 0°. The angle between the fiber direction of the third layer of twill carbon cloth and the main force direction of the power arm is 0°. The angle between the fiber direction of the fourth layer of twill carbon cloth and the main force direction of the power arm is 45°. Specifically, the twill carbon cloth uses T300 twill carbon cloth, and its thickness is 0.2 mm. By limiting the angle between the fiber directions of the four layers of twill carbon cloth, the paving strength of the lower skin 2 can be improved.

[0029] In the application embodiment, the lower skin 2 also includes a first thickened twill carbon cloth and a second thickened twill carbon cloth. The first thickened twill carbon cloth and the second thickened twill carbon cloth are both arranged at the installation position of the motor mounting seat 6. The first thickened twill carbon cloth and the second thickened twill carbon cloth are bonded to each other, and the first thickened twill carbon cloth and the second thickened twill carbon cloth are located between the second layer of twill carbon cloth and the third layer of twill carbon cloth. The angle between the fiber direction of the first thickened twill carbon cloth and the main force direction of the power arm is 45°. The angle between the fiber direction of the second thickened twill carbon cloth and the main force direction of the power arm is 45°. Since the installation position of the motor mounting seat 6 is subjected to greater force, six layers of twill carbon cloth are laid at the installation position of the motor mounting seat 6 to strengthen the lower skin 2, thereby reducing the laying cost of the lower skin 2 and reducing the weight of the lower skin 2 while ensuring the strength of the lower skin 2. Specifically, the first thickened twill carbon cloth and the second thickened twill carbon cloth are both T300 twill carbon cloth with a thickness of 0.2 mm.

[0030] In the embodiment of the present application, the angle between the motor mounting surface of the motor mounting seat 6 and the horizontal plane is 4°. In practical applications, the angle between the motor mounting surface of the motor mounting seat 6 and the horizontal plane is 4° to ensure that the airflow state is appropriate when the drone is in flight, thereby providing stable pulling force and thrust. Specifically, the motor mounting seat 6 and the motor mounting groove 21 are processed in a flat conformal manner.

[0031] The various embodiments in this specification are described in a progressive manner, and the same or similar parts between the various embodiments can be referenced to each other. Each embodiment focuses on the differences from other embodiments.

[0032] The above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit the present application. Although the present application has been described in detail with reference to the aforementioned embodiments, a person of ordinary skill in the art should understand that the technical solutions described in the aforementioned embodiments may still be modified, or some or all of the technical features thereof may be replaced by equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the present application.

Claims

1. A composite wing UAV power arm, characterized in that: It comprises an upper skin (1), a lower skin (2), a motor mounting seat (6) and a main load-bearing frame; The upper skin (1) comprises multiple layers of twill carbon cloth bonded to each other; The lower skin (2) comprises multiple layers of twill carbon cloth bonded to each other, and two motor seat mounting grooves (21) are provided on the lower skin (2); The upper skin (1) and the lower skin (2) are connected to form a sealed space, and the main load-bearing frame is located in the sealed space; The main load-bearing frame comprises a motor seat beam (4), four beams (3) and a plurality of power arm frames (5); The four beams (3) are arranged in a rectangular array; A plurality of power arm frames (5) are arranged at intervals in the internal space formed by the four beams (3) along the length direction of the beams (3), and each of the power arm frames (5) is connected to the four beams (3); The two ends of the two beams (3) connected to the lower skin (2) are respectively connected to a motor seat beam (4); the shape of the motor seat beam (4) matches the outer wall of the motor seat installation groove (21); One motor mounting seat (6) is respectively installed in each motor seat mounting groove (21).

2. The composite wing UAV power arm according to claim 1, characterized in that: The upper skin (1) comprises four layers of twill carbon cloth bonded to each other; The angle between the fiber direction of the first layer of twill carbon cloth and the main force direction of the power arm is 45°; The angle between the fiber direction of the second layer of twill carbon cloth and the main force direction of the power arm is 0°; The angle between the fiber direction of the third layer of twill carbon cloth and the main force direction of the power arm is 0°; The angle between the fiber direction of the fourth layer of twill carbon cloth and the main force direction of the power arm is 45°.

3. The composite wing UAV power arm according to claim 1, characterized in that: The lower skin (2) comprises four layers of twill carbon cloth bonded to each other; The angle between the fiber direction of the first layer of twill carbon cloth and the main force direction of the power arm is 45°; The angle between the fiber direction of the second layer of twill carbon cloth and the main force direction of the power arm is 0°; The angle between the fiber direction of the third layer of twill carbon cloth and the main force direction of the power arm is 0°; The angle between the fiber direction of the fourth layer of twill carbon cloth and the main force direction of the power arm is 45°.

4. The composite wing UAV power arm according to claim 3, characterized in that: The lower skin (2) further comprises a first thickened twill carbon cloth and a second thickened twill carbon cloth; The first thickened twill carbon cloth and the second thickened twill carbon cloth are both arranged at the mounting position of the motor mounting seat (6); The first thickened twill carbon cloth and the second thickened twill carbon cloth are bonded to each other, and the first thickened twill carbon cloth and the second thickened twill carbon cloth are located between the second layer of twill carbon cloth and the third layer of twill carbon cloth; The angle between the fiber direction of the first thickened twill carbon cloth and the main force direction of the power arm is 45°; The angle between the fiber direction of the second thickened twill carbon cloth and the main force direction of the power arm is 45°.

5. The composite wing UAV power arm according to claim 1, characterized in that: The included angle between the motor mounting surface of the motor mounting seat (6) and the horizontal plane is 4°.

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