An ultra-elastic energy storage and ejection rotor unmanned aerial vehicle

Abstract

This invention provides a hyperelastic catapult-launched rotorcraft unmanned aerial vehicle (UAV), relating to the field of UAV design. It includes a fuselage assembly, an elastic energy storage assembly, and a deformable traction assembly. It employs a high-energy-efficiency hyperelastic energy storage device combining springs, hyperelastic sheets, and hyperelastic ropes. The winding and contraction of the elastic rope in the deformable traction assembly indirectly drives the hyperelastic sheets, ropes, and inner spring in the elastic energy storage assembly to undergo elastic deformation, storing potential energy. The instantaneous release of the stored potential energy is achieved by the breakage of the winding and contracting elastic rope. The powerful reaction force from the ground on the UAV at the moment of potential energy release provides high driving force for catapult launch, achieving a high takeoff speed in a short time and improving the UAV's maneuverability. Upon high-speed landing, the elastic structure stores energy, reducing impact and preventing structural damage to the UAV, ensuring a safe landing.

Description

Technical Field

[0001] This invention relates to the field of rotorcraft drone design, specifically to a superelastic energy storage catapult rotorcraft drone that uses a novel superelastic device to launch the rotorcraft drone into the air. Background Technology

[0002] Rotary-wing drones, as a type of unmanned aerial vehicle that is small in size, light in weight, low in noise, good in stealth, and suitable for use on multiple platforms and in multiple spaces, can achieve vertical take-off and landing without the use of catapults or launchers. They can hover, fly sideways, and fly inverted. Although they fly at low altitudes, they have strong maneuverability and can perform various special missions. Moreover, they have a simple structure, flexible control, low cost, small propellers, good safety performance, convenient disassembly, and easy maintenance. They have been widely used in civilian fields such as photography and irrigation.

[0003] The characteristics and advantages of rotary-wing UAVs make them highly promising for military applications. Their advantages in tactical logistics—low cost, low casualties, low losses, and precise delivery—are a valuable supplement to existing transport and delivery methods, playing a crucial role in establishing comprehensive, three-dimensional tactical logistical support. Furthermore, rotary-wing UAVs have low flight speeds, stable attitudes, and autonomous flight control technology for multiple UAV formations has entered the application stage. Their small radar cross-section allows them to utilize their maneuverability to employ counter-reconnaissance tactics, reducing the probability of radar or visual detection. Even when subjected to air-to-air attacks, rotary-wing UAVs still possess advantages such as a low probability of being hit, minimal losses after being hit, and a limited number destroyed. When equipped with fire support systems, they can conduct efficient and concentrated strikes against enemy forces.

[0004] However, currently, most rotary-wing drones adopt flat-ground takeoff or hand-held takeoff methods. Their rapid takeoff response maneuverability is insufficient in situations requiring emergency takeoff, such as sudden encounters, making it difficult to provide reconnaissance, fire support, and other missions in a timely manner. How to further enhance the rapid takeoff capability of rotary-wing drones while retaining their inherent advantages, in order to gain a first-mover advantage on the battlefield, is an urgent problem to be solved in the current field of rotary-wing drone military applications. Furthermore, most existing rotary-wing drones lack landing cushioning protection devices, making them vulnerable to impact and damage due to mechanical failures, battery depletion, or rapid landing and concealment. How to design landing cushioning protection devices to ensure the safe landing of rotary-wing drones is also a problem that needs to be considered in the design of current rotary-wing drones. Summary of the Invention

[0005] The purpose of this invention is to overcome the shortcomings of the prior art and provide a catapult-launched UAV based on a novel hyperelastic energy storage mechanism to achieve rapid take-off response capability for rotorcraft UAVs, thereby ensuring that rotorcraft UAVs have a first-mover advantage on the battlefield and improving their reconnaissance and combat capabilities. It features small size, simple structure, low cost, convenient operation, and light weight. At the same time, it can use the elastic energy storage mechanism to buffer the impact force when the UAV lands rapidly, protecting the UAV's safe landing.

[0006] The objective of this invention is achieved through the following technical solution:

[0007] A super-elastic energy storage catapult-launched unmanned aerial vehicle (UAV) includes an elastic energy storage component, a deformable traction component, and a body component;

[0008] The body components include an outer shell, a top shell, an inner top plate, an inner chassis, an inner core frame, an inner fixing ring, a wing fixing ring, a wing, a wing slider, a wing connecting rod, a wing spring, an inner support column, a rotor, and a rotor motor. The internal skeleton of the UAV consists of an inner core frame, an inner top plate, inner support columns, inner fixing rings, and an inner chassis. Four inner support columns are evenly distributed circumferentially, with one end connected to the inner top plate and the other to the inner chassis. Four inner fixing rings are evenly distributed and each connects to two inner support columns to limit frame vibration. The bottom of the inner core frame is fixed to the inner chassis via shaft holes, and the other end is inserted into the mounting hole of the inner top plate, forming a stable support for connecting the elastic energy storage component. The bottom of the inner chassis is installed inside the outer shell via mounting holes, and the top of the outer shell is fixed to the wing fixing ring via shaft holes, thus forming a stable extension outward from the inner skeleton. Four wings are evenly distributed circumferentially, with one end connected to the wing fixing ring via shaft holes and the other end connected to the wing connecting rod via mounting shafts. The inner support columns contain components for… The wing-spreading spring and wing-spreading slider are mounted in a groove. The wing-spreading connecting rod is evenly distributed around its circumference, with one end connected to the wing-spreading slider and the other end connected to the wing. When the wing-spreading slider moves within the groove of the inner support column, it drives the wing-spreading connecting rod connected to it to move, thereby causing the wing to rotate around the mounting position of the wing-spreading fixing ring to realize the opening and closing movement of the wing. The wing has a mounting position for the rotor motor, and the rotor is fixed to the output shaft of the rotor motor. When the wing is unfolded, the rotor motor is started, thereby driving the rotor to rotate, giving the drone the ability to stay airborne. The inner top plate has a pin hole, which, through cooperation with the electromagnetic pin, locks the drone's wings, enhancing the drone's resistance to airflow disturbances during flight. The top shell is connected to the outer shell by threads, which is easy to disassemble.

[0009] The elastic energy storage component includes a hyperelastic sheet, an inner core spring, a wing inner core, a hyperelastic sheet inner core, a hyperelastic rope, a hyperelastic sheet mounting block, a chassis, and an electromagnetic pin. The wing inner core and the hyperelastic sheet inner core are respectively inserted into the inner core frame of the body assembly through mounting through holes. The wing inner core is located above the hyperelastic sheet inner core, and the hyperelastic sheet inner core forms a whole by engaging with the bottom mounting hole of the wing inner core via a top protruding shaft, thus having the same axial movement mode. The wing inner core has evenly distributed protruding shafts around its perimeter, which insert into the wing slider mounted in the inner support column groove of the body assembly, enabling the wing inner core to drive the wing slider to move along the axial direction, thereby actuating the opening and closing of the wings. The hyperelastic sheet mounting block... The four hyperelastic plates are evenly distributed circumferentially within the mounting slots of the hyperelastic plate inner core. Their two ends are respectively inserted into the mounting slots located in the hyperelastic plate mounting block and the chassis to achieve fixation. The hyperelastic plates have binding spools for binding hyperelastic ropes. The two ends of the hyperelastic ropes are respectively bound to the binding spools in the inner fixing rings of the hyperelastic plates and the fuselage components. The electromagnetic pin is fixed to the inner core of the wing. During assembly, it is aligned with the pin hole on the inner top plate. At the moment of ejection, it is inserted into the pin hole to restrict the movement capability of the inner core of the wing, thereby indirectly locking the spatial position of the wing.

[0010] The deformable traction assembly consists of a wound retractable elastic rope, a motor box, bearings, a connector, a traction motor, and a rear cover of the motor box. The motor box contains the bearing and the mounting position for the traction motor, which is threadedly connected to the inner core of the elastic energy storage assembly, ensuring that it can have the same axial displacement as the inner core of the wing. The rear cover of the motor box, the traction motor, the connector, the bearing, and the motor box are placed concentrically in sequence. One end of the connector is connected to the motor shaft through a shaft hole, and the protruding shaft portion of the other end is inserted into the bearing. The rear cover of the motor box is threadedly connected to the motor box, and its connection to the motor mounting slot within the motor box restricts the motor's displacement within the motor box. Simultaneously, to ensure the installation of the connector, the motor box has a through hole for installing the connector. The motor shaft and bearing, while ensuring the connector's rotational movement capability, restrict its axial displacement within the motor box. The two ends of the wound retractable elastic rope are connected to the connector and the chassis in the elastic energy storage assembly, respectively, through wiring holes.

[0011] Preferably, the wings have rubber edging.

[0012] Preferably, the connecting rod, the wing slider, and the mounting post of the wing hinge connecting rod are made of aluminum alloy.

[0013] Preferably, the inner top and bottom are provided with impact-resistant sponge.

[0014] Preferably, the binding post is placed in the mounting hole on the two hollowed-out surfaces of the ultra-elastic sheet.

[0015] Preferably, the number of binding posts on the superelastic sheet is 3, and the number of superelastic ropes bound to each binding post is 3.

[0016] Preferably, the length of the wound elastic rope is fixed and it is provided with a binding mark line.

[0017] Preferably, the number of hyperelastic sheets is 4.

[0018] Preferably, the number of wound shrink elastic cords is 3.

[0019] The beneficial effects of this invention are:

[0020] This invention discloses a super-elastic energy storage catapult-launched rotary-wing UAV, comprising an elastic energy storage component, a deformable traction component, and a fuselage component. The deformable traction component applies a deformation driving force to the elastic energy storage component, causing it to undergo elastic deformation and store energy. The instantaneous release of this deformation generates a powerful ground impact force, and the reaction force from the ground propels the UAV into the air. The cushioning performance of the elastic energy storage component reduces the ground impact upon landing. This rotary-wing UAV avoids the insufficient maneuverability issues associated with ground-based or hand-held launches, ensuring a first-strike advantage and improving its reconnaissance and combat capabilities. It also protects the UAV during safe landings due to mechanical failures, battery depletion, or the need for rapid concealment. It boasts advantages such as simple structure, low cost, easy operation, light weight, small size, low noise, and good stealth. Specifically:

[0021] The aforementioned airframe components include an outer shell, a top shell, an inner top plate, an inner chassis, an inner core frame, an inner fixing ring, a wing fixing ring, a wing, a wing slider, a wing connecting rod, a wing spring, an inner support column, a rotor, and a rotor motor. The inner core frame, inner top plate, inner support column, inner fixing ring, and inner chassis constitute the internal skeleton of the UAV, used to install the elastic energy storage component. The outer shell, which houses the internal skeleton, together with the wing fixing ring, wing connecting rod, wing slider, and wing spring, forms the external skeleton that stably extends outward from the internal skeleton of the rotary-wing UAV. Simultaneously, the wing slider, through the wing connecting rod, drives the wing to rotate around the mounting axis of the wing fixing ring, thus enabling the wing to open and close, enhancing the maneuverability and stealth capabilities of the rotary-wing UAV. The rotor motor is installed in a mounting slot on the wing, with its motor shaft connected to the rotor. When the wing is deployed, the rotor rotates at high speed, providing lift to the UAV. The inner fixing plate has pin holes for fixing to it, which cooperate with the electromagnetic pins in the aforementioned elastic energy storage component to secure the wing. The body components provide the UAV with its most basic flight capabilities and provide mounting positions for other components.

[0022] The aforementioned deformable traction assembly includes a wound retractable elastic rope, a motor box, bearings, a connector, a traction motor, and a rear cover of the motor box. Both ends of the wound retractable elastic rope are connected to the chassis of the elastic energy storage assembly via wiring holes and the connector. The motor box is threadedly connected to the inner core of the elastic energy storage assembly. When the traction motor operates, causing the wound retractable elastic rope to wound and retract, the motor box, pulled by one end of the wound retractable elastic rope, will cause the flapping inner core, which is fixed to the motor box, to undergo axial displacement, providing deformation force to the elastic energy storage assembly and compressing it to produce elastic deformation.

[0023] The aforementioned elastic energy storage component includes a hyperelastic sheet, an inner core spring, a wing inner core, a hyperelastic sheet inner core, a hyperelastic rope, a hyperelastic sheet mounting block, a chassis, and an electromagnetic pin. Driven by the deformation traction system, the wing inner core applies a deformation force to the hyperelastic sheet through the hyperelastic sheet inner core, causing the hyperelastic sheet to bend. The inner core spring, with one end installed inside the hyperelastic sheet inner core, undergoes compression deformation under the displacement of the hyperelastic sheet inner core. The hyperelastic rope, with both ends attached to the hyperelastic sheet and the fuselage component terminals respectively, undergoes tensile deformation as the hyperelastic sheet deforms. The hyperelastic sheet, inner core spring, and hyperelastic rope in the elastic energy storage component store energy through elastic deformation and release it instantaneously as the winding and contracting elastic rope breaks, generating a powerful ground impact force. The reaction force of the ground on the chassis enables the rotor drone to be launched into the air. At the same time, the hyperelastic sheet instantly returns to its original shape and is fixed to the inner core of the wing. An electromagnetic pin is inserted into a pin hole on the top plate inside the airframe component, restricting the movement of the inner core of the wing and thus locking the spatial position of the wing in the airframe component. Attached Figure Description

[0024] Figure 1 This is an isometric schematic diagram of the present invention.

[0025] Figure 2 This is a cross-sectional schematic diagram of the present invention.

[0026] Figure 3 This is an isometric schematic diagram of the body skeleton of the present invention.

[0027] Figure 4 This is an isometric schematic diagram of the internal structure after the shell and part of the skeleton of the present invention have been removed.

[0028] Figure 5 This is a schematic diagram of the assembly relationship of the elastic energy storage component after deformation following the removal of the superelastic rope in this invention.

[0029] Figure 6 This is a schematic diagram of the assembly relationship of the deformable traction component of the present invention.

[0030] Figure 7 This is a schematic diagram showing the fit between the electromagnetic pin and the pin hole of the present invention. Detailed Implementation

[0031] The technical solution of the present invention will be further described in detail below with reference to the accompanying drawings, but the scope of protection of the present invention is not limited to the following description.

[0032] like Figures 1 to 7 As shown, a hyperelastic catapult rotor drone includes a body assembly, an elastic energy storage assembly, and a deformable traction assembly.

[0033] The body components include a wing 11, a rotor 12, a top shell 13, an outer shell 14, a wing connecting rod 15, a wing slider 16, a wing spring 17, a rotor motor 18, an inner core frame 19, an inner fixing ring 110, a wing fixing ring 111, an inner top plate 112, an inner support column 113, and an inner chassis 114. The inner core frame 19, inner fixing ring 110, inner top plate 112, inner support column 113, and inner chassis 114 constitute the internal skeleton of the rotary-wing UAV. The four inner support columns 113 are evenly distributed circumferentially, with their ends fixed to the inner top plate 112 and inner chassis 114 respectively through mounting holes. The four inner fixing rings 110 are connected to two inner support columns 114 respectively through shaft holes. The inner core frame 19 is fixed to the inner chassis 114 through bottom mounting holes. The wing 11, rotor 12, top shell 13, outer shell 14, wing connecting rod 15, wing slider 16, and wing spring 17 constitute the stable skeletal extension of the rotary-wing UAV from the internal skeleton outwards. The two ends of the wing spring 17 are respectively connected to the bottom of the upper sliding groove of the inner support column 113 and also mounted on the inner support column 114. The wing slider 16 in the slide groove is fixedly connected and provides auxiliary support for the movement of the wing slider 16 in the slide groove. One end of the wing 17 has a mounting hole and is mounted on the cylindrical mounting position of the wing fixing ring 111, and can rotate around the mounting position. Both ends of the wing connecting rod 15 have mounting holes and form hinge connections with the wing slider 16 and the wing connecting rod mounting positions of the wing 17, respectively. The rotor motor 18 is mounted in the motor mounting position of the wing 17, providing rotational torque for the rotor 12 fixed on its shaft. The inner bottom surface of the outer shell 14 is fixedly connected to the bottom surface of the inner chassis 114 through mounting holes, and the upper end surface is fixedly connected to the bottom surface of the wing fixing ring 111 through mounting holes, thus fixing the entire airframe. The top shell 13 is threadedly mounted on the outer shell 14.

[0034] The elastic energy storage component includes a hyperelastic rope 21, a hyperelastic sheet 22, a chassis 23, a wing-shaped inner core 24, a hyperelastic sheet mounting block 25, a hyperelastic sheet inner core 26, an electromagnetic pin 27, and an inner core spring 28. The hyperelastic sheet inner core 26 is inserted into the aforementioned inner core frame 19 through a through hole, forming a flexible connection that allows translation along the axis of the aforementioned inner core frame 19. The wing-shaped inner core 24 is flexibly connected to the aforementioned inner core frame 19 in the same way as the hyperelastic sheet inner core 26, and the wing-shaped inner core 24 is located above the hyperelastic sheet inner core 26. Its bottom irregular groove and the top irregular convex shaft of the hyperelastic sheet inner core 26 form a shaft hole fit, achieving a fixed connection between the two during movement along the axis of the aforementioned inner core frame 19. Four hyperelastic sheet mounting blocks 25 are evenly distributed circumferentially and assembled separately. Within the mounting slot of the mounting block of the superelastic inner core 26, both ends of the superelastic sheet 22 are respectively inserted into the superelastic sheet mounting block 25 and the superelastic sheet slot of the chassis 23 and fixed together with bolts. Both ends of the superelastic rope 21 are respectively bound to the aforementioned inner fixing ring 110 and the binding post on the superelastic sheet 22. Both ends of the inner core spring 28 are respectively fixed to the superelastic inner core 26 and the aforementioned inner chassis 114, providing auxiliary support for the movement of the superelastic inner core 26 and the wing-shaped inner core 24 and further storing potential energy.

[0035] The deformable traction assembly includes a motor housing cover 31, a traction motor 32, a connector 33, a bearing 34, a motor housing 35, and a winding and shrinking elastic rope 36. The motor housing cover 31, traction motor 32, connector 33, bearing 34, and motor housing 35 are arranged circumferentially. The motor housing 35 has a slot for the traction motor 32, and a countersunk through hole for accommodating the bearing 34 and connector 33 on the end face of the slot. Finally, it is connected to the aforementioned wing inner core 24 by threads. One end of the connector 33 is inserted into the bearing 34, and the other end is inserted into and fixed to the output shaft of the traction motor 32, ensuring that the connector 33 only has rotational movement capability and will not produce axial displacement under the winding and shrinking traction of the winding and shrinking elastic rope 36. The two ends of the winding and shrinking elastic rope 36 are respectively bound to the aforementioned chassis 23 and the wiring hole of the connector 33.

[0036] The operation of this hyperelastic catapult-launched rotor drone is as follows:

[0037] Before the rotorcraft drone is launched, its wings must be retracted for easy storage. Therefore, the drone's operation can be divided into three stages: the first stage is wing retraction, the second stage is launch, and the third stage is flight. This invention aims to design a novel launch-launch rotorcraft drone structure. The flight control system and circuit design are omitted in the following description of its use; only the process of changing the winding and retracting elastic rope, as well as the mechanical movement during wing retraction and launch, are described.

[0038] Replacement process of the winding and shrinking elastic rope: After the drone is recovered, a new winding and shrinking elastic rope needs to be replaced for the next catapult flight. Rotate and remove the top shell 13 that is threadedly connected to the outer shell 14. Rotate and remove the motor box 35 that is threadedly connected to the wing inner core 24. Rotate and remove the motor box rear cover 36 that is threadedly connected to the motor box 35. Then, place the traction motor 32 in the motor mounting slot of the motor box 35 and remove the connector 33 fixed to it. Remove the broken winding and shrinking elastic rope bound to the connector 33 and re-bind the new winding and shrinking elastic rope 36 to the wiring hole. Then, reassemble them into the drone in the reverse order of the removal of each device. Finally, remove the other end of the broken winding and shrinking elastic rope on the chassis 23 and bind the free end of the new winding and shrinking elastic rope 36 through the wiring hole on the chassis 23.

[0039] Wing retraction phase: To facilitate the storage and transportation of the UAV, the deployed wings 11 need to be retracted. The electromagnetic switch of the electromagnetic pin 27, which is fixed to the inner core 24 of the wing, is activated. Under the action of electromagnetic force, the two pin pieces in the electromagnetic pin 27 move closer to each other, causing the electromagnetic pin 27 to disengage from the pin hole 115 on the inner top plate 112 under the traction of the winding and contracting elastic rope 36. After the top of the pin pieces of the electromagnetic pin 27 has completely disengaged from the pin hole 115, the electromagnetic switch is turned off, and the two pin pieces return to their initial positions. Afterward, the system continues to control the traction motor 32 to rotate, and the winding and contracting elastic rope 36, which is respectively bound to the connector 33 and the chassis 23, rotates under the drive of the rotation of the traction motor 32. The winding and contracting elastic rope 36 drives the motor box 35 to move together. The inner core 24 of the wing, which is fixed to the motor box 35, is pulled along the axis towards the base 23 by the winding and contracting elastic rope 36. The protruding shaft on the inner core 24 of the wing, which is connected to the wing slider 16, drives the wing slider 16 to move in the same direction. Finally, the wing connecting rod 15, which is connected to the wing slider 16 and the wing 11 hinge at both ends, pulls the wing 11 to rotate downward around the wing mounting position on the wing fixing ring 111. When the wing 11 fits into the wing groove on the outer shell 14, the control system stops the rotation of the traction motor 32 and locks it, thereby realizing the retraction of the wing 11. During the retraction phase of the wing 11, the inner core 24 of the wing moves closer to the base 23 while pressing the inner core 26 of the superelastic sheet that is released from it to move together, and compresses the superelastic sheet 22 and the inner core spring 28 to a certain extent, so that the elastic energy storage component stores a certain amount of elastic potential energy in advance before the ejection operation is carried out.

[0040] During the ejection phase: After the wing 11 retracts, when the control system receives the ejection command, it controls the traction motor 32 to rotate in the same direction as during the wing retraction phase. Because the wing groove on the outer shell 14 contacts the retracted wing 11 and the wing spring 17 is compressed to its shortest length, the wing slider 16 that drives the wing 11 and the wing inner core 24 connected to the wing slider 16 no longer have the ability to displace along the UAV axis. The ability of the wing 11 to continue retracting inwards is limited. Under the traction of the winding and contracting elastic rope 36, the hyperelastic sheet 22 further bends and deforms, causing the chassis 23, fixed to the other end of the hyperelastic sheet 22, to approach the bottom of the outer shell 14. Simultaneously, the hyperelastic rope 21, bound at both ends to the hyperelastic sheet 22 and the inner fixing ring 110 respectively, is further stretched and stores elastic potential energy under the traction of the bending deformation of the hyperelastic sheet 22. When the winding and contracting elastic rope 36... When the generated shear force reaches and exceeds the limit value, the winding and contracting elastic rope 36 breaks to realize the instantaneous release of energy from the elastic energy storage device, thereby causing the chassis 23 to generate a strong impact on the ground, and using the reaction force from the ground to the chassis 23 to achieve ejection and takeoff. During the takeoff, the inner core 26 of the hyperelastic sheet and the inner core 24 of the wing are driven by the shape recovery of the hyperelastic sheet 22 and the inner core spring 28 to move rapidly towards the top shell 13. At the same time, the inner core 24 of the wing drives the wing slider 16 to move, and under the push of the wing connecting rod 15, which is hinged to the wing slider 16 and the wing 11, the wing 11 is opened. At the same time, the control system controls the rotor motor 18 to rotate at high speed to provide the UAV with loitering capability. In addition, the electromagnetic pin 27, which is fixed to the inner core 24 of the wing, is inserted into the pin hole of the inner top plate 112 to fix the inner core 24 of the wing to the inner top plate 112 to lock the wing 11 and prevent the wing 11 from shaking under the action of airflow. Preferably, to ensure that the wing 11 and the outer shell 14 are not damaged by compression, the wing 11 has a rubber edging; preferably, to ensure that the wing connecting rod 15, the wing slider 16 and the wing 11 are not damaged by pulling, the mounting post of the wing connecting rod 15, the wing slider 16 and the wing 11 that are hinged to the wing connecting rod is made of lightweight and high-strength aluminum alloy; preferably, to avoid impact damage, the bottom of the inner top plate 112 is provided with a sponge to cushion the impact on the inner core 24 of the wing.

[0041] This hyperelastic catapult-launched rotorcraft UAV utilizes a hyperelastic mechanism combining springs, hyperelastic sheets, and hyperelastic ropes to store elastic potential energy. The instantaneous release of this energy powers the UAV's catapult launch. The working structure of this hyperelastic energy storage mechanism is integrated with the UAV's airframe design, achieving a smooth transition between energy release and wing deployment, and between energy storage and wing retraction. This enhances the rotorcraft UAV's maneuverability and ease of energy storage. The streamlined shell, resembling a projectile, maximizes top space for power supplies and flight control components, effectively raising the center of gravity to reduce the impact of airflow on the UAV's balance during takeoff and minimizing air resistance. The use of a wound-and-contract elastic rope for instantaneous energy release greatly simplifies the device's complexity and avoids the fatigue damage caused by repeated use of the traction device under high traction forces. This invention is small, lightweight, simple in structure, low in cost, and easy to operate, providing a simple and effective method for catapult-launching rotorcraft UAVs.

[0042] In the elastic energy storage component of this hyperelastic catapult rotor UAV, to bind the hyperelastic rope 21 to the hyperelastic sheet 22 and reduce the weight of the UAV, the hyperelastic sheet 22 is hollowed out without affecting its deformation capacity, and binding posts for binding the elastic rope are set in the hollow part. As the hyperelastic sheet 22 bends and deforms, its cross-sectional width increases and its thickness decreases. Preferably, the binding posts are placed in mounting holes on the two hollow surfaces of the hyperelastic sheet to avoid applying tensile force to the binding posts and causing damage when the cross-sectional width of the hyperelastic sheet 22 increases during bending and deformation; to increase... The elastic potential energy storage capacity of the elastic energy storage component is enhanced. Preferably, each hyperelastic sheet 22 has 3 binding posts, and each binding post has 3 hyperelastic ropes. The binding of the hyperelastic rope 21 to the inner fixing ring 110 and the connection of the wing inner core 24 to the wing slider 16 achieve a good integration of the catapult device with the fuselage, avoiding the storage and transportation inconvenience caused by using an external catapult device. At the same time, the buffering performance of the elastic energy storage device integrated with the fuselage reduces the impact of the UAV's rapid descent, protecting the UAV's safe landing.

[0043] The functional characteristic of the winding and shrinking elastic rope drive device is that, under a constant load, the ultimate force of the winding and shrinking elastic rope before winding breakage increases with the increase of the initial length of the winding and shrinking elastic rope and decreases with the increase of the number of winding turns. Under the same load, initial length of the winding and shrinking elastic rope, and material, the difference in the number of winding turns at the time of winding breakage is small, i.e., the difference in the shrinkage displacement caused by winding is small. Therefore, in the deformation traction system of this hyperelastic catapult rotor UAV, preferably, using winding and shrinking elastic rope 36 of the same length results in a small difference in the degree of bending deformation of the hyperelastic sheet 22 at each winding breakage. It can be considered that the winding breakage of the winding and shrinking elastic rope 36 meets the error condition within a small range. Simultaneously, the winding and shrinking elastic rope 36... The binding marking line ensures that the length of the winding shrink elastic rope segment located between the connector 33 and the chassis 23 is consistent. In order to reduce fatigue damage caused by repeated bending of the superelastic sheet 22, the stress of the superelastic sheet 22 when the winding shrink elastic rope 36 breaks is much less than the ultimate stress. Preferably, the number of superelastic sheets 22 is 4. Therefore, the number of winding shrink elastic ropes 36 cannot be too many. If the number of winding shrink elastic ropes is too small, the bending degree of the superelastic sheet 22 will not be sufficient when it breaks, resulting in insufficient energy storage of the elastic energy storage component. Preferably, the number of winding shrink elastic ropes is 3. The deformation traction system uses the winding shrink elastic rope to break to realize the instantaneous release of energy of the elastic energy storage device, avoiding the complexity of the system structure and the fatigue damage of the traction device under large traction force after repeated use.

[0044] The above description is merely a preferred embodiment of the present invention. It should be understood that the present invention is not limited to the forms disclosed herein and should not be construed as excluding other embodiments. It can be used in various other combinations, modifications, and environments, and can be altered within the scope of the concept described herein through the above teachings or related technologies or knowledge. Modifications and variations made by those skilled in the art that do not depart from the spirit and scope of the present invention should be within the protection scope of the appended claims.

Claims

1. A hyperelastic catapult-launched rotary-wing unmanned aerial vehicle, characterized in that, This includes body components, elastic energy storage components, and deformable traction components; The fuselage assembly includes a wing, a rotor, a top shell, an outer shell, a wing connecting rod, a wing slider, a wing spring, a rotor motor, an inner core frame, an inner fixing ring, a wing fixing ring, an inner top plate, an inner support column, and an inner base plate. The upper end of the inner support column is provided with a groove for filling the wing slider and the wing spring. The wing slider and the wing spring are installed in the groove of the inner support column. The two ends of the wing connecting rod are respectively hinged to the wing slider and the wing through shaft holes. The inner top plate is provided with a pin hole. The top shell and the outer shell are connected by threads. The elastic energy storage component includes several hyperelastic ropes, several hyperelastic sheets, a chassis, a wing-shaped inner core, a hyperelastic sheet mounting block, a hyperelastic sheet inner core, an electromagnetic pin, and an inner core spring. The two ends of the hyperelastic sheet are respectively inserted into the mounting slots of the hyperelastic sheet inner core and the chassis and fixed with bolts passing through the through holes at the mounting positions. The two ends of the hyperelastic rope are respectively bound to the binding posts on the hyperelastic sheet and the inner fixing ring. The wing-shaped inner core is provided with an electromagnetic pin that aligns with the pin holes on the aforementioned inner top plate during assembly. The two ends of the inner core spring are respectively connected to the upper end face of the aforementioned inner chassis and the inner upper end face of the hyperelastic sheet inner core. The deformable traction assembly includes a motor box rear cover, a traction motor, a connector, a bearing, a motor box, and several wound retractable elastic ropes. The motor box has a slot for placing the traction motor and a countersunk through hole for filling the bearing and the connector on the end face of the slot. The bottom of the motor box is connected to the aforementioned wing inner core by threads. Each time the ejection operation is completed, the wound retractable elastic ropes need to break due to winding.

2. The hyperelastic catapult-launched rotary-wing UAV according to claim 1, characterized in that, The superelastic sheet has a hollowed-out surface with mounting holes for binding posts used to bind the superelastic rope.

3. The hyperelastic catapult-launched rotary-wing UAV according to claim 1, characterized in that, The number of binding posts on each superelastic sheet is 3.

4. The hyperelastic catapult-launched rotary-wing UAV according to claim 1, characterized in that, The number of super-elastic ropes tied to each binding post is 3.

5. The hyperelastic catapult-launched rotary-wing UAV according to claim 1, characterized in that, The number of hyperelastic sheets is 4.

6. The hyperelastic catapult-launched rotary-wing UAV according to claim 1, characterized in that, The replaceable wound retractable elastic cord is provided with binding marking lines.

7. The hyperelastic catapult-launched rotary-wing UAV according to claim 1, characterized in that, The number of the wound shrinking elastic ropes is 3.

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