Miniature static solar self-sustaining aircraft

Abstract

The invention discloses a miniature solar self-sustaining electrostatic aircraft, and belongs to the technical field of miniature aircrafts. The aircraft comprises a stator part, a rotor part, a solar power supply assembly and a rotor wing assembly driven by a rotor, and the rotor wing assembly is arranged below the rotor part. The core of the motor is that a damping assembly is installed on the stator component and comprises an annular support and a plurality of damping blades arranged in the circumferential direction, and the damping blades are connected with the annular support through an angle adjusting mechanism. The angle adjusting mechanism is arranged to be capable of responding to the rotating speed change of the stator component and passively adjusting the inclination angle of the damping blade, so that reverse pneumatic torque matched with the angle adjusting mechanism is dynamically provided, and rotation of the stator is restrained. Through a passive self-adaptive adjusting structure, the problem of stator instability caused by reaction torque in electrostatic driving is effectively solved, stable self-sustaining hovering of the aircraft under the natural light power supply condition is achieved, and the self-adaptive self-sustaining aircraft has the advantage of being high in self-adaption.

Description

Technical Field

[0001] This invention relates to the field of micro aircraft technology, specifically to a micro electrostatic solar-powered self-sustaining aircraft. Background Technology

[0002] Micro-aircraft have broad application prospects in fields such as environmental monitoring, reconnaissance, and communication relay, but their endurance and environmental adaptability are key bottlenecks. Electrostatic drive technology, with its advantages of simple structure, low power consumption, high efficiency, and almost no heat generation, provides a highly promising solution for the propulsion system of micro-aircraft. Electrostatic motors drive the rotor to rotate through an electrostatic field, thereby driving the rotor to generate lift, laying the technological foundation for realizing lightweight, long-endurance micro-aircraft.

[0003] However, electrostatic drive systems face an inherent challenge in practical applications: the electrostatic force driving the rotor to rotate generates an equal-magnitude but opposite-direction counter-torque on the stator. If not effectively balanced, this counter-torque will cause the stator, which carries the power supply system and auxiliary components, to continuously spin, severely compromising the aircraft's attitude stability and preventing it from achieving stable hovering or controllable flight.

[0004] To address the issues of energy supply and flight stability, existing technologies have proposed various solutions. For example, prior art 1 (CN118300240A) discloses a miniature high-voltage power conversion system and an electrostatic solar-powered aircraft utilizing it. This system powers an electrostatic motor through an innovative lightweight high-voltage circuit and demonstrates various aircraft configurations. However, this document primarily focuses on efficient, lightweight, and voltage-adjustable power supply systems, without providing specific solutions for the anti-torque balance and attitude stability issues of the aircraft body during hovering. Its aircraft configuration still relies on traditional layouts such as fixed-wing, multi-rotor, or supported frames, failing to effectively solve the fundamental stability problem caused by stator rotation in single-rotor electrostatic drive systems, thus making it difficult to achieve unrestricted, long-term stable hovering.

[0005] To explore sustainable energy sources independent of sunlight and to initially address stability issues, as shown in prior art 2 (CN121134080A), a solution utilizing atmospheric electric potential energy combined with a fixed self-stabilizing structure has emerged. This technology directly extracts energy from the atmospheric electric field through electrostatic collection needles and grounding components, while a fixed self-stabilizing frame and self-stabilizing blades are installed below the rotor. The blade angle of attack is opposite to that of the rotor, aiming to provide additional lift and passively offset some of the anti-torque. However, this solution has at least two limitations: First, its self-stabilizing blades use a fixed installation angle, which is a static compensation mechanism. It cannot adaptively adjust according to flight conditions (such as changes in stator speed due to power adjustments or airflow disturbances), and the damping torque is fixed. When the operating conditions deviate from the design point, its balance effect decreases, the stability margin is limited, and it is difficult to achieve robust self-stabilization across the entire operating range. Second, it adopts a "rotor on top, self-stabilizing structure below" layout. In this configuration, the downwash airflow of the rotor will directly act on the self-stabilizing blades below, which may interfere with their preset aerodynamic environment, affect their torque balancing effect, and may increase unnecessary aerodynamic drag.

[0006] In summary, although existing technologies have made progress in energy acquisition for electrostatic flight and introduced a simple torque balancing approach into the structure of single-rotor electrostatic aircraft, they still have shortcomings in terms of stability under various adaptive operating conditions. Therefore, this invention aims to further improve the ability of electrostatically driven micro-aircraft to adapt to various operating conditions and maintain good stability under various operating conditions. Summary of the Invention

[0007] To address the shortcomings of existing technologies, this invention provides a miniature electrostatic solar-powered self-sustaining aircraft. This can further improve the self-sustaining stability of the aircraft.

[0008] To achieve the above objectives, the present invention provides the following technical solutions.

[0009] A solar-powered self-sustaining electrostatic aircraft, comprising: The stator assembly and the rotor assembly coaxially passing through the stator assembly; A solar power supply component is used to supply power to the stator component; A rotor assembly, connected to the rotor component, is driven by the rotor component to generate lift; The aircraft is characterized in that the rotor assembly is arranged below the rotor component; the aircraft further includes: A damping assembly, mounted on the stator component, rotates synchronously with the stator component to counteract the rotation of the stator component caused by the counter torque; the damping assembly includes: a) A ring-shaped bracket, fitted onto the outside of the stator component; b) Multiple damping blades are arranged circumferentially on the annular support, and the angle of attack of each damping blade is opposite to that of the rotor blades of the rotor assembly. The damping blade is connected to the annular support via an angle adjustment mechanism, which is configured to passively adjust the tilt angle of the damping blade in response to the rotational speed of the stator component.

[0010] Furthermore, the angle adjustment mechanism includes: Multiple connecting shafts are fixedly connected to each of the damping blades; Multiple connecting bearings are fixed to the annular bracket for rotatably supporting the connecting shaft; An elastic reset element is connected between the connecting shaft and the annular bracket, and is used to apply a reset torque to the connecting shaft; When the rotational speed of the annular support exceeds a threshold, the aerodynamic resistance acting on the damping blade overcomes the reset torque of the elastic reset member and causes the damping blade to rotate in the direction of increasing angle of attack, so as to provide a greater reverse torque and suppress the further increase of the rotational speed of the stator component.

[0011] Furthermore, the elastic reset element is a torsion spring, which is sleeved on the part of the connecting shaft that passes through the connecting bearing. One end of the torsion spring is fixed to the connecting shaft, and the other end of the torsion spring axially extends beyond the end of the connecting shaft facing away from the damping blade and is fixed with an end cap. The end cap is detachably fixed to the annular bracket.

[0012] Furthermore, it also includes an angle limiting structure to restrict the rotation range of the damping blades.

[0013] Furthermore, the angle limiting structure includes two limiting posts disposed on the annular bracket and located at both ends of the expected deflection path of the damping blade, for limiting the deflection range of the damping blade.

[0014] Furthermore, the torsion spring is fitted with a fixing frame fixed to the annular bracket. The fixing frame has multiple arc-shaped holes arranged circumferentially on one end facing away from the annular bracket. The end cap is fixed to the fixing frame by bolts passing through the arc-shaped holes and nuts that fit the bolts. The preload of the torsion spring can be adjusted by adjusting the position of the bolts in the arc-shaped holes.

[0015] Furthermore, the stator component has positive and negative electrodes that are circumferentially cross-distributed; the rotor component has a plurality of conductive plates arranged in a circular pattern; the conductive plates are capable of alternately acquiring charge from the positive and negative electrodes of the stator component, thereby driving the rotor component to rotate.

[0016] Furthermore, the rotor component includes a rotor frame, and a plurality of the conductive sheets are arranged at intervals along the circumferential direction on the outer side of the rotor frame. The stator component includes a stator frame, and a plurality of positive electrodes and a plurality of negative electrodes are uniformly arranged along the circumferential direction on the circumferential surface of the stator frame. The rotor frame is rotatably connected to the stator frame.

[0017] Furthermore, a support frame extending downwards and beyond the rotor assembly is fixed to the lower end of the annular bracket.

[0018] Furthermore, the rotor assembly includes a hub and a plurality of blades circumferentially spaced on the outer circumferential surface of the hub.

[0019] Based on the above technical solution, the solar-powered self-sustaining electrostatic aircraft of the present invention can produce the following significant beneficial effects compared with the prior art: 1. This invention introduces a damping component controlled by an angle adjustment mechanism. This mechanism can directly respond to changes in the stator's rotational speed: when the stator accelerates to a certain threshold due to counter-torque, the aerodynamic drag on the damping blades increases accordingly, overcoming the torque of the elastic reset element and automatically increasing the angle of attack, thereby providing enhanced counter-torque that matches the stator's rotational speed in real time. This feedback adjustment mechanism can automatically suppress and stabilize the stator's rotational speed within a reasonable range, reducing stator instability caused by counter-torque in electrostatic drive and improving the aircraft's adaptive stability and robustness under varying operating conditions (such as power fluctuations caused by changes in illumination). The mechanism of this angle adjustment mechanism is that when the stator rotates slowly, the damping blades maintain their initial tilt angle, providing counter-torque and significant lift. When the stator reaches a certain speed, the damping blade tilt angle increases, at which point the damping blades primarily provide counter-torque force.

[0020] 2. By arranging the rotor assembly below the rotor components, a unique "under-rotor" configuration is formed. This layout has dual advantages: Firstly, it avoids the direct impact of the rotor downwash airflow on the upper damping blades, reducing unnecessary turbulence interference and aerodynamic losses, allowing the damping blades to work efficiently in a cleaner flow field (in the background technology, when the damping blades are below, the high-speed airflow blown downwards by the rotor increases the rotational speed of the damping blades, while the damping blades of this invention, being above, greatly alleviates this problem), improving the accuracy of its torque balance; secondly, under certain operating conditions, the downward airflow induced by the rotation of the damping assembly may even have a certain additional speed-increasing effect on the lower rotor, thus achieving partial synergistic utilization of aerodynamic energy while maintaining passive stability, thereby improving the overall efficiency of the power system.

[0021] 3. In some preferred embodiments, the damping assembly may also integrate an angle limiting structure or an adjustable preload elastic reset component. This not only ensures the safe range of damping blade adjustment but also allows for changes in the system's response threshold through simple mechanical adjustments (such as adjusting the position of the bolt in the arc-shaped hole) to adapt to different aircraft configurations or environmental requirements. Furthermore, this invention requires the aircraft's aerodynamic pressure center to be located below its center of gravity, so that the generated aerodynamic torque can automatically correct the aircraft's horizontal displacement, restoring it to a hovering state—a direct aerodynamic stabilization mechanism. Combined with this stabilization mechanism, a multi-layered, combined active and passive aerodynamic stabilization system is formed, giving the aircraft a stronger ability to automatically recover balance when encountering disturbances, further ensuring the stability of hovering and flight.

[0022] In summary, this invention, through the synergistic effect of a passive adaptive damping adjustment mechanism and an optimized aerodynamic layout, not only overcomes the self-stabilization technology bottleneck of electrostatically driven micro-aircraft, but also improves its aerodynamic efficiency and environmental adaptability. The structure is simple and reliable, and has industrial application value. Attached Figure Description

[0023] Figure 1 This is a perspective view of the present invention; Figure 2 This is a perspective view of the present invention. Figure 3 This is a three-dimensional view from the perspective of the present invention; Figure 4 This is a three-dimensional structural diagram of the damping component and angle adjustment mechanism in this invention; Figure 5 for Figure 4 A perspective view of the mechanism shown without the end caps; Figure 6 for Figure 5 Enlarged view of section A in the middle; Figure 7 for Figure 4 A perspective view of the mechanism shown without its support frame; Figure 8 for Figure 4 The diagram shows a three-dimensional view of the structure with the support frame, end cap, and bolts and nuts removed.

[0024] Explanation of reference numerals in the attached figures: 1. Stator component; 101. Positive electrode; 102. Negative electrode; 103. Stator frame; 2. Rotor components; 201. Conductive sheet; 202. Rotor frame; 203. Shaft; 3. Rotor assembly; 301. Hub; 302. Blades; 4. Solar power supply components; 5. Damping assembly; 501. Annular bracket; 502. Damping blade; 503. Support frame; 6. Angle adjustment mechanism; 601. Connecting shaft; 602. Connecting bearing; 603. Elastic reset component; 604. End cap; 605. Limiting post; 606. Fixing frame; 607. Arc-shaped hole; 608. Bolt; 609. Nut. Detailed Implementation

[0025] The technical solutions of the embodiments of this application will be clearly described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application are within the scope of protection of this application.

[0026] It should be noted that the terms "first," "second," etc., used in the specification and claims of this application are used to distinguish similar objects and not to describe a specific order or sequence. It should be understood that such use of data can be interchanged where appropriate so that embodiments of this application can be implemented in orders other than those illustrated or described herein, and the objects distinguished by "first," "second," etc., are generally of the same class and are not limited in number; for example, a first object can be one or more. Furthermore, in the specification and claims, "and / or" indicates at least one of the connected objects, and the character " / " generally indicates that the preceding and following objects are in an "or" relationship.

[0027] It should be noted that in the description of this application, the directional terms such as "front, back, up, down, left, right", "horizontal, vertical, horizontal" and "top, bottom" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description. Unless otherwise stated, these directional terms do not indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on the scope of protection of this application. The directional terms "inner" and "outer" refer to the inner and outer contours relative to the outline of each component itself.

[0028] It should be noted that the scope of the methods and apparatus in the embodiments of this application is not limited to performing functions in the order shown or discussed, but may also include performing functions in a substantially simultaneous manner or in the reverse order, depending on the functions involved. For example, the described methods may be performed in a different order than described, and various steps may be added, omitted, or combined. In addition, features described with reference to certain examples may be combined in other examples.

[0029] This invention discloses a miniature electrostatic solar-powered self-sustaining aircraft.

[0030] The main body of the electrostatic motor in this invention is based on existing technology (for example, the structure of the main body of the electrostatic motor can be disclosed in two documents cited in the background art). The main body includes a stator component 1, a rotor component 2 disposed in the stator component 1, a rotor assembly 3, and a solar power supply assembly 4.

[0031] The rotor assembly 3 is connected to the rotor component 2 and is driven by the rotor component 2 to generate lift.

[0032] The stator component 1 has positive electrodes 101 and negative electrodes 102 that are circumferentially cross-distributed; the rotor component 2 has a plurality of conductive plates 201 arranged in a circular pattern; the conductive plates 201 can alternately acquire charge from the positive electrodes 101 and negative electrodes 102 of the stator component 1, thereby driving the rotor component 2 to rotate.

[0033] The rotor component 2 includes a rotor frame 202, and a plurality of conductive sheets 201 are arranged at intervals along the circumferential direction on the outer side of the rotor frame 202. The stator component 1 includes a stator frame 103, and a plurality of positive electrodes 101 and a plurality of negative electrodes 102 are uniformly arranged along the circumferential direction on the circumferential surface of the stator frame 103. The rotor frame 202 is rotatably connected to the stator frame 103.

[0034] The positive electrode 101 and negative electrode 102 on the stator component 1 are respectively connected to the positive and negative electrodes of the solar power supply component 4. This allows the stator component 1 to drive the rotor component 2 to rotate the rotor assembly 3.

[0035] As an embodiment 1 of the present invention, such as Figure 1-3 As shown, in order to improve the self-sustaining stability of the single-rotor electrostatic aircraft, a damping assembly 5 is fitted over the stator frame 103 of the stator component 1. The damping assembly 5 includes an annular support 501 fitted over the stator frame 103, and a plurality of damping blades arranged circumferentially on the annular support 501, wherein the angle of attack of each damping blade 502 is opposite to that of the blade 302 of the rotor assembly 3.

[0036] In this embodiment, a rotating shaft 203 is fixed downward at the center of the rotor frame 202, and the rotating shaft 203 is connected to the rotor assembly 3 located below the rotor component 2.

[0037] The rotor assembly 3 includes a central hub 301 and a plurality of blades 302 evenly spaced around the outer circumference of the hub 301. A shaft 203 located below the rotor assembly 2 has its downwardly extending end fixedly connected to the central portion of the hub 301 (e.g., via a key connection, interference fit, or adhesive bonding). Thus, when the rotor assembly 2 rotates under the influence of an electrostatic field, its torque is directly and without delay transmitted to the hub 301 via the shaft 203, thereby driving all the blades 302 to rotate synchronously, cutting through the air to generate the lift required to sustain the aircraft's flight.

[0038] The core of this embodiment lies in the fact that a damping assembly 5 is coaxially fitted outside the stator frame 103. This assembly consists of an annular support 501 and multiple circumferentially distributed damping blades 502, forming an outer ring structure surrounding the stator. At the same time, the rotor assembly 3, which generates lift, is connected to the lower part of the rotor component 2 via a rotating shaft 203, forming a unique vertical layout with the damping assembly on top and the rotor assembly below.

[0039] In this embodiment, when the electrostatic motor operates, the electrostatic force driving the rotor component 2 and rotor assembly 3 to rotate generates an equal and opposite counter-torque on the stator component 1. The damping component 5 is directly mounted on the stator component 1, allowing it to directly respond to and resist this counter-torque. The angle of attack direction of the damping blade 502 is opposite to that of the rotor blade 302, ensuring that when it rotates with the stator, the direction of the generated aerodynamic torque is opposite to the stator's rotational tendency, thus achieving torque balance. In addition to providing balanced torque, the damping component 5 also provides additional lift.

[0040] In this embodiment, the rotor assembly 3 is positioned below the entire power system, ensuring that the strong downwash airflow generated by its rotation is primarily directed downwards, avoiding direct impact on the upper damping blades 502. This ensures that the damping blades 502 operate in a relatively stable flow field, resulting in more stable and predictable aerodynamic characteristics (drag and torque), thus improving the reliability and accuracy of the passive balancing effect. The "top-stable, bottom-rising" layout brings comprehensive aerodynamic benefits. While the upper damping assembly 5 balances torque, its rotation also agitates the air. However, the impact of this airflow on the lower rotor is much smaller compared to the direct impact of the downwash airflow on the stable surface in a "rotor-on-top" layout (where the rotor-on-top structure causes the high-speed downward airflow from the rotor to accelerate the rotation of the damping blades, which is detrimental to reducing the stator component's rotational speed). More importantly, under certain operating conditions, the slight downward airflow induced by the rotation of the damping assembly 5 may pre-accelerate or regulate the flow field of the rotor's incoming airflow, thereby improving rotor efficiency or its operating condition to a certain extent, achieving synergistic aerodynamic functions.

[0041] In this embodiment, the solar power supply component 4 (including at least a solar panel and a micro-boost circuit module, etc.) is mounted on the top of the stator frame 103. The center of gravity of the solar power supply component 4, the aerodynamic pressure center of the aircraft, and the center of gravity of the motor are coaxial and located on the central axis of the motor. The rotor blades 302 and damping blades 502 of the rotor assembly 3 need to be arranged symmetrically, that is, the number of blades is even. The specific number needs to be matched according to the motor speed and adjusted according to the relationship between the angular momentum of the two rotating components. Under the condition that the lift allows, increasing the number of blades 302 is beneficial to the stability of the aircraft. At the same time, the aerodynamic pressure center of the aircraft needs to be close to the center of gravity of the aircraft. The shape of the blades 302 can be double trapezoidal. The shape of the damping blades 502 can be rectangular or trapezoidal. The specific size can be determined according to the propeller size and torque balance relationship. During the design, the damping blades 502 should have a small moment of inertia to ensure that the angular momentum of the propeller is much greater than that of the damping blades. The "top-down" arrangement positions the aerodynamic pressure center below the center of gravity, generating aerodynamic torque that automatically corrects the aircraft's horizontal displacement, restoring it to a hovering state—a direct aerodynamic stabilization mechanism. In other embodiments of this application, the relative positions of the propeller and the power supply system can be adjusted; for example, the propeller can be positioned above the power supply system.

[0042] As an embodiment 2 of the present invention, such as Figure 1 , 4 As shown in Figure 6, based on Embodiment 1, the damping component 5 has been further optimized. In this embodiment, the damping blade 502 is not fixedly connected to the annular support 501, but is connected in a deflectable manner through an angle adjustment mechanism 6. The angle adjustment mechanism 6 is configured to passively adjust the tilt angle of the damping blade 502 in response to the rotational speed of the stator component 1.

[0043] Specifically, the angle adjustment mechanism 6 mainly includes: Connecting shaft 601: A connecting shaft 601 is fixed at the root of each damping blade 502; Connecting bearing 602: The annular bracket 501 is provided with a mounting hole corresponding to the connecting shaft 601, and a connecting bearing 602 is fixed in the hole. The connecting shaft 601 passes through the connecting bearing 602, thereby realizing the rotational connection of the damping blade 502 relative to the annular bracket 501. Elastic reset member 603: connected between the connecting shaft 601 and the annular bracket 501, used to apply a reset torque to the connecting shaft 601; Angle limiting structure: To limit the adjustment range of the damping blade 502, two limiting posts 605 are provided on the annular bracket 501 at both ends of the expected deflection path of the damping blade 502. The root of the damping blade 502 is located between these two limiting posts 605, thereby limiting its maximum and minimum angle of attack.

[0044] The angle adjustment mechanism 6 operates entirely passively, and its adjustment process is as follows: Normal state (low speed or equilibrium): When the rotational speed of the stator component 1 due to the counter-torque is low, the aerodynamic drag torque acting on the damping blade 502 is small and cannot overcome the reset torque of the elastic reset member 603 (because of the limit post 605, the elastic reset member 603 can be set with an initial torque so that when the aerodynamic drag reaches a certain threshold, the reset force of the elastic reset member 603 can be overcome to cause the damping blade 502 to rotate). At this time, the damping blade 502 is held at the initial small angle of attack position under the action of the torsion spring, providing the basic counter-balancing torque. Since the overall rotational speed is low at this time, the angle of attack of the damping blade 502 is configured to generate lift while providing the basic counter-torque, thus assisting the takeoff of the aircraft.

[0045] Adjustment State (High-Speed ​​or Unbalanced State): When the aircraft's power increases or it is disturbed, causing the stator component 1 to rotate faster, the damping blade 502's velocity relative to the air increases, and the aerodynamic drag torque it experiences increases accordingly. At this time, the damping blade 502 should automatically adjust to a state more conducive to counteracting the torque. When this aerodynamic drag torque exceeds the preset reset torque of the elastic reset member 603, it will drive the connecting shaft 601 to rotate against the reset force of the elastic reset member 603, thereby causing the angle of attack of the damping blade 502 to deflect in the direction of increasing. At this time, the angle of the damping blade 502 is more suited to increasing drag rather than providing auxiliary lift.

[0046] Establishing a new equilibrium: The increased angle of attack directly leads to a significant increase in the reverse aerodynamic torque generated by the damping blade 502. This increased balancing torque will effectively suppress the acceleration trend of the stator component 1 until the aerodynamic drag torque, the reset torque of the elastic reset element 603, and the system drag torque reach a new equilibrium. At this point, the rotational speed of the stator component 1 will stabilize at a new, restricted level, while the damping blade 502 remains at a certain increased angle of attack position.

[0047] In this embodiment, at low speeds, the damping blade 502 maintains a small angle of attack, resulting in low aerodynamic drag. While providing the basic balancing torque, this angle of attack is more conducive to providing auxiliary lift, avoiding unnecessary power loss. When instability occurs (speed increases), the mechanism can respond quickly, instantly providing a larger restoring torque by increasing the angle of attack (at this point, the angle of attack primarily provides balancing torque, rather than auxiliary lift), resulting in a faster response and more significant damping effect in suppressing oscillations. This "on-demand" damping force provision is more efficient than a system that always provides a fixed large damping.

[0048] As an embodiment 3 of the present invention, based on embodiment 2, such as Figure 1 and 4As shown in Figure 8, the elastic reset member 603 and its installation and adjustment structure in the angle adjustment mechanism 6 are further described in detail, and a specific scheme for adjustable torsion spring reset and preload is disclosed.

[0049] Specifically, the elastic reset element 603 is a torsion spring. This torsion spring is sleeved around the shaft segment of the connecting shaft 601 that passes through the connecting bearing 602. One end of the torsion spring is fixed to the connecting shaft 601, allowing it to rotate with the connecting shaft 601.

[0050] The other end of the torsion spring is designed to extend axially, passing over the connecting shaft 601 and facing away from the end of the damping blade 502. This extension end is ultimately fixedly connected to a separate end cap 604.

[0051] To ensure the adjustability of the torsion spring preload and facilitate assembly, a fixing bracket 606 is provided. This fixing bracket 606 is fixed to the annular support 501, and its main body is sleeve-shaped, coaxially spaced around the torsion spring, providing some protection and guidance. On the end flange of the fixing bracket 606 facing away from the annular support 501, multiple arc-shaped holes 607 are spaced apart along the circumference, the centers of which coincide with the axis of the connecting shaft 601.

[0052] The end cap 604 is mounted on the end of the mounting bracket 606 by at least one set (usually one set, but may also be two symmetrical sets) of fasteners. Specifically, bolts 608 pass sequentially through the through holes on the end cap 604 and the arc-shaped holes 607 on the mounting bracket 606, and finally lock into place with nuts 609, thereby pressing and fixing the end cap 604 onto the mounting bracket 606. The bolts and nuts are made of insulating materials, such as polytetrafluoroethylene (PTFE) or polyetheretherketone (PEEK) engineering plastics, to achieve electrical insulation, prevent current from being conducted through the fasteners, and improve the safety and reliability of the equipment.

[0053] In this embodiment, when the damping blade 502 is deflected by aerodynamic force, it drives the connecting shaft 601 to rotate, thereby torturing the torsion spring. The torsion spring generates a torque that opposes this rotation, which is the reset torque that restores the damping blade 502 to its initial angle.

[0054] In this embodiment, loosening the nut 609 allows the end cap 604 to rotate or move along the trajectory of the arc-shaped hole 607. Since one end of the elastic reset member 603 is fixed to the connecting shaft 601 and the other end is fixed to the end cap 604, rotating the end cap 604 is equivalent to changing the initial torsion angle (preload angle) of the torsion spring. Re-tightening the bolt and nut by rotating the end cap 604 in the direction that increases the preload force of the torsion spring increases increases the initial value of the reset torque. Conversely, it reduces the preload force. After adjustment, the new position of the bolt 608 in the arc-shaped hole 607 is fixed.

[0055] This embodiment allows for stepless and continuous adjustment of the torsion spring preload by loosening the nut and rotating the end cap using simple tools (such as a screwdriver or wrench). This precisely sets the stator speed threshold at which the damping blades begin to respond (deflecting to overcome the reset torque). This enables flexible adaptation to aircraft with different takeoff weights, rotor aerodynamic characteristics, or mission requirements, or allows for fine-tuning during the commissioning phase to achieve optimal dynamic stability performance. This enhances the design's versatility and engineering applicability.

[0056] As an embodiment 4 of the present invention, based on any one of embodiments 1-3, a downwardly extending support frame 503 is fixedly connected to the lower end of the annular bracket 501 of the damping component 5.

[0057] The upper end of the support frame 503 is fixed to the lower edge of the annular bracket 501 or the connected stator frame 103 by means of bolt connection or integral molding.

[0058] The support frame 503 extends vertically downwards, and its lowest point is designed to exceed (i.e., be lower than) the lowest swept surface formed when the blades 302 of the rotor assembly 3 rotate.

[0059] During vertical landing, the lowest point of the support frame 503 will contact the ground or landing surface before the rotor assembly 3, acting as a "landing gear" or "buffer foot" to directly prevent the high-speed rotating precision rotor blades 302 from colliding or scraping against the ground. When the aircraft is parked on the ground, the support frame 503 supports the fuselage, keeping the rotor assembly 3 completely suspended in the air, preventing the blades from deforming or being damaged due to pressure or contact with foreign objects. During flight, the support frame 503, as a rigid component connecting the damping assembly and the lower part, can enhance the longitudinal and lateral stiffness of the entire aircraft's lower structure. At the same time, its streamlined rod-like structure has a certain effect on the airflow passing under the fuselage.

Claims

1. A solar-powered self-sustaining electrostatic aircraft, comprising: The stator component (1) and the rotor component (2) coaxially inserted within the stator component (1); A solar power supply component (4) is used to supply power to the stator component (1); The rotor assembly (3) is connected to the rotor component (2) and is driven by the rotor component (2) to generate lift; The aircraft is characterized in that the rotor assembly (3) is arranged below the rotor component (2); the aircraft further includes: A damping assembly (5) is mounted on the stator component (1) and rotates synchronously with the stator component (1) to counteract the rotation of the stator component (1) caused by the counter-torque; the damping assembly (5) includes: a) A ring-shaped bracket (501) is fitted onto the outside of the stator component (1); b) Multiple damping blades (502) are arranged circumferentially on the annular support (501), and the angle of attack of each damping blade (502) is opposite to that of the blade (302) of the rotor assembly (3). The damping blade (502) is connected to the annular support (501) via an angle adjustment mechanism (6), which is configured to passively adjust the tilt angle of the damping blade (502) in response to the rotational speed of the stator component (1).

2. The solar-powered self-sustaining electrostatic aircraft according to claim 1, characterized in that, The angle adjustment mechanism (6) includes: Multiple connecting shafts (601) are fixedly connected to each of the damping blades (502); Multiple connecting bearings (602) are fixed on the annular bracket (501) for rotatably supporting the connecting shaft (601). An elastic reset member (603) is connected between the connecting shaft (601) and the annular bracket (501) and is used to apply a reset torque to the connecting shaft (601); When the rotational speed of the annular support (501) exceeds a threshold, the aerodynamic resistance acting on the damping blade (502) overcomes the reset torque of the elastic reset member (603) and causes the damping blade (502) to rotate in the direction of increasing angle of attack, so as to provide a greater reverse torque and suppress the further increase of the rotational speed of the stator component (1).

3. The solar-powered self-sustaining electrostatic aircraft according to claim 2, characterized in that, The elastic reset member (603) is a torsion spring. The torsion spring is sleeved on the part of the connecting shaft (601) that passes through the connecting bearing (602). One end of the torsion spring is fixed on the connecting shaft (601), and the other end of the torsion spring axially passes over the end of the connecting shaft (601) facing away from the damping blade (502) and is fixed with an end cap (604). The end cap (604) is detachably fixed on the annular bracket (501).

4. The solar-powered self-sustaining electrostatic aircraft according to claim 2, characterized in that, It also includes an angle limiting structure for limiting the rotation range of the damping blade (502).

5. The solar-powered self-sustaining electrostatic aircraft according to claim 4, characterized in that, The angle limiting structure includes two limiting posts (605) disposed on the annular bracket (501) and located at both ends of the expected deflection path of the damping blade (502), for limiting the deflection range of the damping blade (502).

6. The solar-powered self-sustaining electrostatic aircraft according to claim 3, characterized in that, The torsion spring is fitted with a fixing frame (606) fixed on the annular bracket (501) at an external spacer. The fixing frame (606) has a plurality of arc-shaped holes (607) arranged in a circular pattern on one end facing away from the annular bracket (501). The end cap (604) is fixed on the fixing frame (606) by bolts (608) passing through the arc-shaped holes (607) and nuts (609) that engage with the bolts (608). The preload of the torsion spring can be adjusted by adjusting the position of the bolts (608) in the arc-shaped holes (607).

7. The solar-powered self-sustaining electrostatic aircraft according to claim 1, characterized in that, The stator component (1) has positive electrodes (101) and negative electrodes (102) arranged in a circumferential cross pattern; the rotor component (2) has a plurality of conductive plates (201) arranged in a circular pattern; the conductive plates (201) can alternately acquire charge from the positive electrodes (101) and negative electrodes (102) of the stator component (1), thereby driving the rotor component (2) to rotate.

8. The solar-powered self-sustaining electrostatic aircraft according to claim 7, characterized in that, The rotor component (2) includes a rotor frame (202), and a plurality of conductive sheets (201) are arranged at intervals along the circumferential direction on the outer side of the rotor frame (202). The stator component (1) includes a stator frame (103), and a plurality of positive electrodes (101) and a plurality of negative electrodes (102) are uniformly arranged on the circumferential surface of the stator frame (103) along the circumferential direction. The rotor frame (202) is rotatably connected to the stator frame (103).

9. The solar-powered self-sustaining electrostatic aircraft according to claim 8, characterized in that, The lower end of the annular bracket (501) is fixed with a support frame (503) that extends downward and extends beyond the rotor assembly (3).

10. The solar-powered self-sustaining electrostatic aircraft according to claim 1, characterized in that, The rotor assembly (3) includes a hub (301) and a plurality of blades (302) arranged circumferentially at intervals on the outer circumferential surface of the hub (301).

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