Static micro flapping-wing air vehicle

Abstract

The invention discloses an electrostatic micro flapping-wing air vehicle which comprises a wing mechanism, a lever mechanism, a supporting mechanism and a driving mechanism. A lever mechanism and a driving mechanism are arranged in the supporting mechanism; the lever mechanism is movably connected with the supporting mechanism, and the wing mechanism is arranged on the lever mechanism; the driving mechanism drives the lever mechanism to rotate in an electrostatic mode, and the output torque is amplified through the lever mechanism so as to drive the wing mechanism to rotate. On the basis of the electrostatic driving technology, the lever mechanism is adopted to amplify the output torque generated by electrostatic force, so that the lever mechanism meets the lift force required by flight of the flapping-wing micro-aircraft, and the technical bottleneck that a traditional electrostatic flapping-wing micro-aircraft is insufficient in driving force is broken through.

Description

Technical Field

[0001] The invention belongs to the technical field of bionic flapping-wing aircraft, and in particular relates to an electrostatic micro flapping-wing aircraft. Background Art

[0002] A micro flapping-wing aircraft is a micro-aircraft designed to mimic the flight principles of birds and insects. Its core principle is to generate lift and propulsion through the periodic flapping of its wings. Its unique biomimetic flapping-wing design offers significant advantages over traditional fixed-wing and rotary-wing aircraft in terms of aerodynamic efficiency, maneuverability, and environmental adaptability. This aircraft not only possesses exceptional maneuverability, efficiently performing complex maneuvers such as rapid takeoff, instant acceleration, and hovering, but its compact size also makes it suitable for a variety of complex scenarios, including military reconnaissance, ecological monitoring, and minimally invasive medical interventions. Within the micro flapping-wing aircraft structure, the drive unit is a core component, much like the human heart. Its technical characteristics directly impact the overall performance of the aircraft, including maneuverability, energy efficiency, and applicable scenarios. Consequently, technological innovation and engineering applications related to flapping-wing aircraft drive units remain a frontier focus for both research institutions and industry, attracting numerous researchers to pursue breakthroughs.

[0003] Micro flapping-wing aircraft generally consist of a drive unit, wings, and an external frame. Due to the miniaturization of the aircraft body, the design of the micro drive unit is very important. The current mainstream solutions for micro drive units include electrostatic drive, electromagnetic drive, thermal drive, shape memory alloy drive, and piezoelectric drive. Electrostatic drive uses the electrostatic force between electrodes to generate deformation to drive the wings to flap. It has the advantages of fast response time and high drive frequency, but it has the problem of insufficient driving force. When faced with slightly larger aircraft, it seems powerless and difficult to provide sufficient power support. Electromagnetic drive generates driving force through electromagnetic induction or the interaction of permanent magnets. Common forms include micro motors and electromagnetic coil drives. It has the advantages of high output torque and can drive larger wings, but its working stability is easily affected by electromagnetic environment interference. Thermal drive relies on the thermal expansion or phase change effect of materials caused by temperature changes to generate driving force. It has the advantages of simple structure and low cost. It can also achieve larger deformation. The heating and cooling processes both take a certain amount of time and there is a significant response hysteresis phenomenon. , the driving frequency is low, which is difficult to meet the high-frequency drive required for flapping-wing flight; shape memory alloy drive relies on solid-state phase transformation caused by temperature changes (such as heating and contraction, cooling and recovery), namely the austenite-martensite phase transformation, to achieve contraction and extension. It has the characteristics of high driving force density, but the thermal conductivity of the material is low, resulting in poor heat dissipation efficiency and limited high-frequency response rate; piezoelectric drive is widely used in the design of micro flapping-wing aircraft due to its good performance in output torque and driving frequency. However, one of the shortcomings of piezoelectric drive is that its control circuit and high-voltage AC power supply are limited by volume and weight constraints and cannot be integrated into the micro flapping-wing aircraft, resulting in the need for wires to connect the control signals and driving energy, which seriously restricts the operating radius and application potential of the micro flapping-wing aircraft.

[0004] In summary, existing drive unit solutions for micro flapping-wing aircraft all have certain drawbacks, making it difficult to simultaneously meet the stringent requirements of miniaturization, high drive performance, and autonomy, and thus facing numerous limitations in practical applications. Therefore, to further develop micro flapping-wing aircraft technology and meet the application needs of diverse fields, it is urgent to develop a new drive technology to address these issues, break through existing technological bottlenecks, and achieve comprehensive improvements in micro flapping-wing aircraft performance. Summary of the Invention

[0005] The present invention aims to address the above-mentioned shortcomings by providing an electrostatic micro-flapping-wing aircraft. Based on electrostatic drive technology, this invention employs a lever mechanism to amplify the output torque generated by the electrostatic force, thereby overcoming the technical bottleneck of insufficient driving force in conventional electrostatic micro-flapping-wing aircraft. To achieve this objective, the present invention provides the following technical solutions: An electrostatic micro flapping-wing aircraft comprises a wing mechanism, a lever mechanism, a support mechanism and a drive mechanism; the support mechanism is provided with a lever mechanism and a drive mechanism; the lever mechanism is movably connected to the support mechanism and is provided with a wing mechanism; the drive mechanism electrostatically drives the lever mechanism to rotate, amplifying the output torque through the lever mechanism to drive the wing mechanism to rotate.

[0006] Furthermore, the support mechanism includes a fuselage plate and a bearing seat arranged in front and behind; the two fuselage plates are parallel to each other, and bearing seats are respectively provided on both sides between the two fuselage plates; the bearing seat is movably connected to the lever mechanism.

[0007] Furthermore, the lever mechanism includes a rotating rod and a rotating shaft; the bearing seat includes support blocks arranged upper and lower; the two support blocks are parallel to each other and are located between the two fuselage panels; a rotatable rotating shaft is provided between the two support blocks; a rotating rod is provided on the fixed sleeve outside the rotating shaft; one end of the rotating rod is located between the two fuselage panels and is connected to the driving mechanism, and the other end is connected to the wing mechanism.

[0008] Furthermore, the support block is provided with a groove; a bearing is provided in the groove; and both ends of the rotating shaft are fixed in the inner ring of the bearing.

[0009] Furthermore, the wing mechanism includes a horizontal bracket, a vertical bracket and a wing surface; a horizontal bracket and a vertical bracket are provided at one end of the rotating rod away from the fuselage panel; the horizontal bracket and the vertical bracket are perpendicular to each other; the adjacent two sides of the wing surface are respectively fixed on the horizontal bracket and the vertical bracket, and are unfolded through the horizontal bracket and the vertical bracket.

[0010] Furthermore, the driving mechanism includes a gold-plated foam ball, a capacitor and an electrode sheet; a ring bracket is provided at one end of the rotating rod located between the two fuselage panels; the gold-plated foam ball is fixed on the ring bracket; a support plate is provided on the top of the fuselage panel; a capacitor is fixed on the support plate; an electrode sheet is provided on the side of the fuselage panel facing the other fuselage panel; the capacitor and the electrode sheet are connected by a wire.

[0011] Furthermore, the bearing seat, support plate, fuselage plate, support leg and rotating rod are made of lightweight non-conductive materials.

[0012] Furthermore, the electrode sheet is a conductive foil.

[0013] Furthermore, a conductive layer is provided on the outer surface of the gold-plated foam ball.

[0014] Furthermore, support legs are provided at the bottom of the fuselage panel.

[0015] The beneficial effects of the present invention are: The present invention discloses an electrostatic micro flapping-wing aircraft, comprising a wing mechanism, a lever mechanism, a support mechanism, and a drive mechanism. The support mechanism is provided with a lever mechanism and a drive mechanism. The lever mechanism is movably connected to the support mechanism and is provided with a wing mechanism. The drive mechanism electrostatically drives the lever mechanism to rotate, amplifying the output torque through the lever mechanism to drive the wing mechanism to rotate. Based on electrostatic drive technology, the present invention employs a lever mechanism to amplify the output torque generated by the electrostatic force, thereby providing the lift required for flight of the micro flapping-wing aircraft. This overcomes the technical bottleneck of insufficient driving force in conventional electrostatic micro flapping-wing aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 Schematic diagram of the three-dimensional structure of the electrostatic flapping-wing micro aircraft of the present invention; Figure 2 A schematic diagram of the three-dimensional structure of the electrostatic flapping-wing micro aircraft of the present invention, omitting one fuselage panel; Figure 3 Schematic diagram of the disassembly of the gold-plated foam ball, lever mechanism and wing mechanism of the present invention; Figure 4 A schematic diagram of the three-dimensional structure of the bearing seat of the present invention; Figure 5 Schematic diagram of the three-dimensional structure of the electrode sheet and fuselage plate of the present invention; Figure 6 Schematic diagram of the three-dimensional structure of the capacitor and support plate of the present invention; Figure 7 Schematic diagram of the present invention; In the accompanying drawings: 1-wing mechanism, 11-horizontal bracket, 12-vertical bracket, 13-wing surface, 2-lever mechanism, 21-rotating rod, 22-rotating shaft, 3-support mechanism, 31-fuselage plate, 32-bearing seat, 321-support block, 33-support leg, 4-driving mechanism, 41-gold-plated foam ball, 42-capacitor, 43-electrode sheet, 44-ring bracket, 45-support plate, 55-wire, 5-bearing. DETAILED DESCRIPTION

[0017] Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although exemplary embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be limited by the embodiments described herein. Rather, these embodiments are provided to enable a more thorough understanding of the present disclosure and to fully convey the scope of the present disclosure to those skilled in the art.

[0018] It should be understood that the terms used herein are for the purpose of describing specific example embodiments only and are not intended to be limiting. Unless the context clearly indicates otherwise, the singular forms "one", "an" and "said" as used herein may also be meant to include plural forms. The terms "comprise", "include", "contain" and "have" are inclusive and therefore specify the presence of the stated features, steps, operations, elements and / or parts, but do not exclude the presence or addition of one or more other features, steps, operations, elements, parts and / or combinations thereof. The method steps, processes, and operations described herein are not to be construed as necessarily requiring them to be performed in the specific order described or illustrated, unless the order of execution is clearly indicated. It should also be understood that additional or alternative steps may be used.

[0019] Although the terms first, second, third, etc. can be used in the text to describe multiple elements, components, regions, layers and / or sections, these elements, components, regions, layers and / or sections should not be limited by these terms. These terms can only be used to distinguish an element, component, region, layer or section from another region, layer or section. Unless the context clearly indicates otherwise, terms such as "first", "second" and other numerical terms do not imply order or sequence when used in the text. Therefore, the first element, component, region, layer or section discussed below can be referred to as the second element, component, region, layer or section without departing from the teachings of the example embodiments.

[0020] For ease of description, spatially relative terms may be used herein to describe the relationship of one element or feature relative to another element or feature as shown in the figures, such as "inside," "outside," "inside," "outside," "below," "beneath," "above," and the like. Such spatially relative terms are intended to encompass different orientations of the device in use or operation other than the orientation depicted in the figures. For example, if the device in the figures is flipped, an element described as "below" or "beneath" another element or feature would subsequently be oriented "above" or "above" the other element or feature. Thus, the example term "below" may encompass both above and below orientations. The device may be otherwise oriented (rotated 90 degrees or in other orientations) and the spatially relative descriptors used herein should be interpreted accordingly.

[0021] A piston engine, also known as a reciprocating engine, uses one or more pistons to convert pressure into rotational kinetic energy. A piston engine is a type of heat engine, powered by fuels such as gasoline and diesel. A piston engine primarily consists of a cylinder, piston, connecting rod, crankshaft, and valvetrain. Piston aircraft engines evolved from automotive piston engines and are mostly four-stroke engines, meaning one cylinder completes one operating cycle, and the piston undergoes four strokes within the cylinder: intake, compression, expansion, and exhaust. In addition to its primary components, an engine requires several auxiliary systems to operate. In addition to traditional piston engines, rotary internal combustion engines have been developed in recent years, offering distinct characteristics from traditional piston engines.

[0022] Example 1 See attached Figures 1 to 6 . The electrostatic micro flapping-wing aircraft of the present invention includes a wing mechanism 1, a lever mechanism 2, a support mechanism 3 and a drive mechanism 4, wherein the support mechanism 3 is the main frame of the entire aircraft, provides support for various components, and bears the installation load of various components. A lever mechanism 2 and a drive mechanism 4 are provided in the support mechanism 3, and the lever mechanism 2 is movably connected to the support mechanism 3. The wing mechanism 1 is connected to the lever mechanism 2, and the wing mechanism 1 is a direct execution component for the interaction between the aircraft and the air. By imitating the wings of birds or insects, the lift generation and propulsion of the aircraft are achieved. The drive mechanism 4 is used to electrostatically drive the lever mechanism 2 to rotate, and amplify the torque generated by the electrostatic force through the lever mechanism 2 to drive the wing mechanism 1 to rotate, so that the wing mechanism 1 obtains sufficient flapping torque, maximizes the utilization of limited electrostatic energy, and solves the problem of weak driving force inherent in electrostatic drive. The electrostatic micro flapping-wing aircraft of the present invention addresses the problem of low driving force of electrostatically driven micro flapping-wing aircraft. A lever mechanism 2 is used to amplify the torque of the electrostatic force acting on the flapping wing end so that it can meet the lift required for the flight of the micro flapping-wing aircraft, thus breaking through the technical bottleneck of insufficient driving force of traditional electrostatic micro flapping-wing aircraft.

[0023] Specifically, the support mechanism 3 includes two body plates 31 and two bearing seats 32, wherein the two body plates 31 are arranged front and back and parallel to each other, as shown in the attached figure. Figure 1 As shown. The two fuselage panels 31 are connected by a bearing seat 32. Two bearing seats 32 are provided between the two fuselage panels 31. The two bearing seats 32 are respectively located at the left and right end positions between the two fuselage panels 31 and are symmetrically arranged about the vertical center axis of the fuselage panels 31. Among them, the bearing seat 32 includes two support blocks 321. The two support blocks 321 are arranged up and down and parallel to each other. They are located between the two fuselage panels 31 and are perpendicular to the fuselage panels 31. The two ends of the support block 321 can be connected to the two fuselage panels 31 by snap fasteners. The fuselage panels 31 and the support blocks 321 together form the main support frame of the aircraft, as shown in the attached figure. Figure 1Two support legs 33 are provided at the bottom of one of the fuselage panels 31. The support legs 33 can be connected to the fuselage panel 31 by snaps. The support legs 33 prevent the wing mechanism 1 from flapping and touching the ground, reduce ground effect interference, and improve the stability and environmental adaptability of the aircraft through lightweight design and damping characteristics.

[0024] Specifically, the lever mechanism 2 includes a rotating rod 21 and a rotating shaft 22. A groove is provided at the connection between the rotating shaft 22 and the supporting block 321 on the supporting block 321. A bearing 5 is installed in the groove. Both ends of the rotating shaft 22 are fixed in the inner ring of the bearing 5. The rotating shaft 22 is perpendicular to the supporting block 321. Figure 4 As shown, the rotating shaft 22 is supported by the bearing 5 to reduce the friction between the rotating shaft 22 and the support block 321. A rotating rod 21 is installed on the rotating shaft 22. Figure 2 and attached Figure 3 As shown, the rotating rod 21 rotates with the rotation axis 22. A portion of the rotating rod 21 is located between the two fuselage panels 31 and connected to the drive mechanism 4, while the other end extends beyond the two fuselage panels 31 and connects to the wing mechanism 1. It should be understood that, with the rotating axis 22 as the dividing point, the length of the portion of the rotating rod 21 connected to the drive mechanism 4 should be shorter than the length of the portion connected to the wing mechanism 1. The support block 321, fuselage panels 31, support legs 33, and lever mechanism 2 of the present invention are constructed from lightweight, non-conductive materials, such as 3D-printed PLA.

[0025] Specifically, the wing mechanism 1 includes a horizontal bracket 11, a vertical bracket 12 and an airfoil 13. The horizontal bracket 11 and the vertical bracket 12 are provided at one end of the rotating rod 21 away from the fuselage plate 31. The horizontal bracket 11 and the vertical bracket 12 are perpendicular to each other. The airfoil 13 of the present invention is made of polyimide film by laser cutting to ensure the consistency of its area. The thickness is 5μm, the tensile strength reaches 130MPa, the elongation at break is 0.3%, and it has excellent fatigue resistance. The adjacent two sides of the airfoil 13 are respectively fixed on the horizontal bracket 11 and the vertical bracket 12, and are unfolded through the horizontal bracket 11 and the vertical bracket 12, as shown in the attached figure. Figure 3 As shown, a special epoxy resin adhesive can be used to secure the adjacent sides of the wing surface 13 to the horizontal bracket 11 and the vertical bracket 12, respectively, to ensure that it will not fall off during long-term high-frequency flapping. When the rotating rod 21 rotates along the rotating shaft 22, the horizontal bracket 11 and the vertical bracket 12 drive the wing surface 13 to produce a back and forth flapping motion.

[0026] Specifically, the driving mechanism 4 includes a gold-plated foam ball 41, a capacitor 42 and an electrode sheet 43. A support plate 45 is provided on the top of the fuselage plate 31. The two ends of the support plate 45 are fixed to the two fuselage plates 31 by buckles. Similarly, the support plate 45 is made of lightweight non-conductive material. A capacitor 42 is fixedly installed on the support plate 45. The capacitor 42 is a key energy storage component of the aircraft driving mechanism 4. Considering the aircraft's strict requirements for lightweight, high voltage tolerance and fast charging and discharging performance, the present invention can optionally use a multilayer chip ceramic capacitor 42. An electrode sheet 43 is provided on the side of the fuselage plate 31 facing the other fuselage plate 31, as shown in the attached figure. Figure 5 As shown, the electrode sheet 43 can be a conductive foil with adhesive backing such as aluminum or copper. Preferably, a copper foil with a thickness of 65 μm is used. The capacitor 42 is connected to the electrode sheet 43 through a wire 55 to provide direct current to the electrode sheet 43. Figure 6 As shown, an electrostatic field is generated between the two electrode sheets 43. An annular bracket 44 is provided at one end of the rotating rod 21 between the two fuselage panels 31, and a gold-plated foam ball 41 is fixed in the annular bracket 44. The gold-plated foam ball 41 of the present invention is surface-treated by a magnetron sputtering device to form a conductive layer on the surface, making it conductive, thereby realizing the induction and transfer of charge in the electrostatic field, so that the gold-plated foam ball 41 moves between the two electrode sheets 43. The magnetron sputtering device is used to treat the gold-plated foam ball 41 to improve its conductivity, thereby improving the surface charge induction and transfer effect of the gold-plated foam ball 41, effectively reducing the occurrence of adhesion problems with the electrode sheets 43 due to charge accumulation, and improving the stability of the aircraft. The present invention integrates the capacitor 42 on the aircraft, while maintaining the lightweight of the aircraft, effectively getting rid of the physical constraints of the wire 55 connection.

[0027] Example 2 The working principle of the electrostatic micro flapping-wing aircraft of the present invention is as follows: Figure 7 As shown. The capacitor 42 provides direct current to the electrode sheets 43 attached to the front and rear fuselage plates 31, so that a constant electrostatic field is formed between the front and rear electrode sheets 43. Figure 7 As shown in (i), the gold-plated foam ball 41 is in contact with the negatively charged electrode sheet 43 as the initial state. At this time, the negatively charged electrode sheet 43 will transfer the negative charge to the two gold-plated foam balls 41. The repulsive force between the same charges will cause the gold-plated foam balls 41 to rotate around the rotation axis 22, driving the lever mechanism 2 to move, and the wing mechanism 1 will move accordingly, as shown in FIG. Figure 7 (ii) As shown; when the gold-plated foam ball 41 rotates to the adjacent Figure 7 (iii), the negative charge on the gold-plated foam ball 41 is neutralized with the positively charged electrode 43, and the process is completed in a very short time; after the charge neutralization is completed, the positively charged electrode 43 transfers the positive charge to the two gold-plated foam balls 41, as shown in the attached figure. Figure 7 (iv) As shown; repulsion will occur between the same charges, causing the gold-plated foam ball 41 to rotate around the rotation axis 22, driving the lever mechanism 2 to move, and the wing mechanism 1 to move accordingly, as shown in the attached figure. Figure 7 (v) As shown; when the gold-plated foam ball 41 rotates to the adjacent Figure 7 During step (vi), the positive charge on the gold-plated foam ball 41 is neutralized and transferred to the negatively charged electrode 43. This reciprocating process causes the wing mechanism 1 to generate high-frequency vibrations, thereby enabling the electrostatic flapping micro aircraft of the present invention to fly.

[0028] All technical features in this embodiment can be freely combined according to actual needs. The above embodiments are only used to illustrate the technical solutions of the present invention and are not limiting. Although the present invention is described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that the technical solutions of the present invention can be modified or replaced by equivalents without departing from the purpose and scope of the technical solutions of the present invention, which should be included in the scope of the claims of the present invention. The technology, shape, and structural parts not described in detail in the present invention are all well-known technologies.

[0029] The above embodiments are preferred implementation schemes of the present invention. In addition, other implementation schemes are also included. Any obvious replacement without departing from the concept of the present technical solution is within the protection scope of the present invention.

Claims

1. An electrostatic flapping-wing micro aircraft, characterized in that: The invention comprises a wing mechanism (1), a lever mechanism (2), a support mechanism (3) and a drive mechanism (4); the support mechanism (3) is provided with the lever mechanism (2) and the drive mechanism (4); the lever mechanism (2) is movably connected to the support mechanism (3), and the wing mechanism (1) is provided thereon; the drive mechanism (4) drives the lever mechanism (2) to rotate in an electrostatic manner, and amplifies the output torque through the lever mechanism (2) to drive the wing mechanism (1) to rotate.

2. The electrostatic flapping-wing micro-aircraft according to claim 1, characterized in that: The support mechanism (3) includes a body plate (31) and a bearing seat (32) arranged front and rear; the two body plates (31) are parallel to each other, and a bearing seat (32) is provided on both sides between the two body plates (31); the bearing seat (32) is movably connected to the lever mechanism (2).

3. The electrostatic flapping-wing micro-aircraft according to claim 2, characterized in that: The lever mechanism (2) includes a rotating rod (21) and a rotating shaft (22); the bearing seat (32) includes upper and lower support blocks (321); the two support blocks (321) are parallel to each other and are located between the two fuselage plates (31); a rotatable rotating shaft (22) is provided between the two support blocks (321); a rotating rod (21) is provided in a fixed sleeve outside the rotating shaft (22); one end of the rotating rod (21) is located between the two fuselage plates (31) and is connected to the driving mechanism (4), and the other end is connected to the wing mechanism (1).

4. The electrostatic flapping-wing micro-aircraft according to claim 3, characterized in that: The support block (321) is provided with a groove; a bearing (5) is provided in the groove; and both ends of the rotating shaft (22) are fixed in the inner ring of the bearing (5).

5. The electrostatic flapping-wing micro-aircraft according to claim 3, characterized in that: The wing mechanism (1) comprises a horizontal bracket (11), a vertical bracket (12) and an airfoil (13); the horizontal bracket (11) and the vertical bracket (12) are provided at one end of the rotating rod (21) away from the fuselage plate (31); the horizontal bracket (11) and the vertical bracket (12) are perpendicular to each other; the adjacent two sides of the airfoil (13) are respectively fixed to the horizontal bracket (11) and the vertical bracket (12), and are unfolded through the horizontal bracket (11) and the vertical bracket (12).

6. The electrostatic flapping-wing micro-aircraft according to claim 3, characterized in that: The driving mechanism (4) comprises a gold-plated foam ball (41), a capacitor (42) and an electrode sheet (43); an annular bracket (44) is provided at one end of the rotating rod (21) located between the two fuselage plates (31); the gold-plated foam ball (41) is fixed on the annular bracket (44); a support plate (45) is provided on the top of the fuselage plate (31); a capacitor (42) is fixed on the support plate (45); an electrode sheet (43) is provided on the side of the fuselage plate (31) facing the other fuselage plate (31); the capacitor (42) and the electrode sheet (43) are connected via a wire (55).

7. The electrostatic flapping-wing micro-aircraft according to claim 6, characterized in that: The outer surface of the gold-plated foam ball (41) is provided with a conductive layer.

8. The electrostatic flapping-wing micro-aircraft according to claim 6, characterized in that: The electrode sheet (43) is a conductive foil.

9. The electrostatic flapping-wing micro-aircraft according to claim 3, characterized in that: Support legs (33) are provided at the bottom of the fuselage panel (31).

10. The electrostatic flapping-wing micro-aircraft according to claim 9, characterized in that: The bearing seat (32), the fuselage plate (31), the rotating rod (21) and the supporting leg (33) are made of lightweight non-conductive materials.

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