An aircraft-mounted dispensing device

Abstract

The present application relates to the technical field of unmanned aerial vehicle, especially to a kind of aircraft mounting and launching device, the device includes support frame, binding belt and drive assembly, support frame is installed on aircraft.Binding belt is used to bundle and fix the object to be launched at the bottom of support frame, and its both ends are provided with the hanging ring that can be hung in the both sides of support frame.Drive assembly is integrally arranged on support frame, including driving part, transmission structure and hook, and the hanging ring is buckled and hung on the hook to realize mounting lock.When working, driving part drives hook to rotate through transmission structure, so that hook and hanging ring are separated, the binding constraint of binding belt is released, and launching is completed.The device realizes accurate unlocking and launching by relying on mechanical linkage, mounting is reliable, launching action is stable and smooth, effectively improves the problems of poor adaptability, low fixing reliability and easy jamming of traditional mounting device, and can be widely adapted to aircraft mounting and launching scenarios of various types of launching loads, and has strong practicality.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and more particularly to an aircraft mounting and deployment device. Background Technology

[0002] In long-distance, silent material delivery scenarios, medium-to-large gliding unmanned transport aircraft, relying on their unpowered gliding characteristics, possess outstanding advantages such as high carrying efficiency, low noise, good concealment, and low operating costs. This effectively compensates for the shortcomings of powered aircraft, such as easy exposure, high energy consumption, and high maintenance costs, making them suitable for covert delivery operations in complex environments. These aircraft lack autonomous propulsion and cannot fly independently over long distances; they must be carried out via external payloads and high-altitude delivery to achieve long-distance operations. Therefore, a dedicated payload delivery system is a key supporting equipment to ensure the smooth execution of their delivery missions.

[0003] Current payload delivery systems are mostly designed for conventional powered UAVs and small payloads. Their structural dimensions, load-bearing specifications, and locking mechanisms are all designed for conventional flight vehicles and cannot be adapted to the large fuselage, special airfoil structure, and gliding delivery conditions of medium and large unpowered gliding UAVs. Existing systems have low structural integration and loose layout, with external attachments occupying a large space, which can easily cause aerodynamic interference to the carrier aircraft and affect its flight safety. At the same time, their locking and positioning structures have poor adaptability and cannot reliably fix the glider, making it prone to swaying and deviation during flight. Furthermore, their unlocking and delivery stability is insufficient, and problems such as delivery jamming and attitude deviation are prone to occur, which seriously affect delivery accuracy and operational safety.

[0004] Furthermore, existing payload systems are complex in structure, cumbersome in operation, and difficult to disassemble, debug, and maintain, making them unsuitable for high-frequency, rapid-response delivery requirements. In summary, existing technologies suffer from poor adaptability, non-compact structure, low reliability, and inconvenient operation, failing to meet the specific payload delivery requirements of medium-to-large gliding unmanned transport aircraft. Therefore, there is an urgent need to develop a payload system and delivery method that is specifically designed, compact in structure, reliable in operation, and easy to operate, ensuring that unmanned transport aircraft can efficiently and safely complete silent material delivery missions. Summary of the Invention

[0005] The purpose of this invention is to provide an aircraft mounting and deployment device that meets the requirements of reliable operation and convenient operation for mounting and deployment of medium and large gliding unmanned transport aircraft.

[0006] To achieve this objective, the present invention adopts the following technical solution: An aircraft payload delivery device, installed on an aircraft, includes: A support frame, which is mounted on the aircraft; The binding strap is used to tie the object to be placed to the bottom of the support frame, and the two ends of the binding strap are provided with hanging loops that hang on both sides of the support frame. A drive assembly is mounted on the support frame. The drive assembly includes a drive component, a transmission structure, and a hook. The hanging ring is fastened to the hook. The drive component drives the hook to rotate through the transmission structure, causing the hook to disengage from the hanging ring.

[0007] Furthermore, the transmission structure includes: A drive shaft is connected to the drive component; A transmission assembly is connected to the drive shaft, and the hook is disposed at the transmission end of the transmission assembly; A locking assembly for locking or unlocking the transmission assembly.

[0008] Furthermore, the transmission assembly includes: The first link, the end of the first link being rotatably mounted on the drive shaft; The second link, the end of which is hinged to the end of the first link away from the drive shaft; The third link is rotatably mounted on the support frame, one end of the third link is hinged to the end of the second link, and the hook is provided at the other end of the third link; Wherein, the end of the first connecting rod near the drive shaft is provided with an arc-shaped stroke groove, and the end of the drive shaft is fixedly provided with a stop block, which is disposed in the arc-shaped stroke groove; When the stop block abuts against one side wall of the arc-shaped travel groove, the stop block jams the transmission assembly and stops the hook. When the stop block abuts against the other side wall of the arc-shaped travel groove, the stop block moves the transmission assembly and drives the hook to open.

[0009] Furthermore, the locking component includes: The first locking rod is fixed on the drive shaft; The second locking rod has its end hinged to the first locking rod; The slider is slidably mounted on the support frame, and the other end of the second locking rod is hinged to the slider. The slider can extend into or out of the bottom of the second connecting rod to lock or release the second connecting rod.

[0010] Furthermore, the drive member is provided with the transmission structure and the hook on both sides, and the drive member synchronously drives the transmission structure and the hook on both sides.

[0011] Furthermore, a linkage shaft is provided between the pair of transmission structures, and the ends of the linkage shaft are respectively located on the hinge axis of the second link and the third link.

[0012] Furthermore, the support frame is also provided with a limiting wall, which is located at the top of the first connecting rod and the second connecting rod.

[0013] Furthermore, the support frame is provided with a limiting groove, and the hook is disposed at the opening of the limiting groove; the hook can be rotated to open or close the opening of the limiting groove.

[0014] Furthermore, the driving component is a drive motor, and there are two drive shafts, which are coaxially arranged on both sides of the driving component.

[0015] Furthermore, the bottom of the support frame is provided with multiple legs, and the bottom of each of the multiple legs is provided with a slot with an opening facing the same direction.

[0016] The beneficial effects of this invention are: The aircraft loading and delivery device disclosed in this invention includes a support frame, straps, and a drive assembly. The support frame is integrally installed and fixed to the aircraft body, serving as the overall loading and delivery base. The straps are used to bind and constrain the object to be delivered, stably and securely fixing it to the bottom of the support frame. Each end of the strap has a hanging loop, which is correspondingly mounted on both sides of the support frame. The drive assembly is integrated and assembled on the support frame, including a drive component, a transmission structure, and a hook. The hanging loops of the straps are correspondingly engaged with the hooks to achieve loading and locking. The drive component outputs precise mechanical power through the transmission structure, driving the hook to rotate, causing the hook to quickly disengage from the hanging loops and unlock, releasing the binding constraint of the straps and completing the aerial delivery of the object. This device features a high degree of structural integration and a compact layout. The overall component arrangement is simple and reasonable, effectively reducing external aerodynamic interference. Through a combination of flexible binding with straps and mechanical locking with hooks, the structural stability and reliability of the loaded state are greatly improved. The release and unlocking actions are precise, responsive, and synchronized. It can stably adapt to various aircraft loading and release conditions for payloads. It is easy to assemble and maintain, and has strong versatility and practicality. It effectively solves the defects of traditional loading and release devices, such as unreliable fixation, easy jamming during release, and poor adaptability. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of an aircraft mounting and delivery device carrying a gliding unmanned transport aircraft in an embodiment of the present invention; Figure 2 This is an overall schematic diagram of the aircraft mounting and launching device in an embodiment of the present invention; Figure 3 This is a partial schematic diagram of the aircraft mounting and deployment device in an embodiment of the present invention; Figure 4 This is a schematic diagram showing the drive components in the aircraft mounting and launching device in an embodiment of the present invention; Figure 5 This is a schematic diagram of the hook being locked in an embodiment of the present invention; Figure 6 This is a schematic diagram of the hook unlocking process in an embodiment of the present invention; Figure 7 This is a schematic diagram showing the completion of hook unlocking in an embodiment of the present invention.

[0018] In the diagram: 1. Support frame; 11. Limiting baffle; 12. Limiting groove; 13. Support leg; 131. Slot; 2. Binding strap; 21. Hanging ring; 3. Drive assembly; 31. Drive component; 32. Transmission structure; 321. Drive shaft; 3211. Stop block; 322. Transmission assembly; 3221. First connecting rod; 3222. Second connecting rod; 3223. Third connecting rod; 3224. Arc-shaped stroke groove; 323. Locking assembly; 3231. First locking rod; 3232. Second locking rod; 3233. Slider; 3234. Limiting bearing; 324. Linkage shaft; 33. Hook. Detailed Implementation

[0019] The present invention will now be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and not intended to limit it. Furthermore, it should be noted that, for ease of description, the accompanying drawings show only the parts relevant to the present invention, and not all of the structures.

[0020] In the description of this invention, unless otherwise explicitly specified and limited, the terms "connected," "linked," and "fixed" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0021] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0022] In the description of this embodiment, the terms "upper," "lower," "right," and "left," etc., refer to the orientation or positional relationship shown in the accompanying drawings. They are used only for ease of description and simplification of operation, and 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. Therefore, they should not be construed as limitations on the present invention. In addition, the terms "first" and "second" are used only for distinction in description and have no special meaning.

[0023] Reference Figures 1 to 7 This embodiment discloses an aircraft payload delivery device that is adapted to the external payload and aerial delivery requirements of medium and large gliding unmanned transport aircraft. The overall structure is highly integrated and compact, which can significantly reduce the aerodynamic interference of the external payload while ensuring the structural load-bearing strength. At the same time, it can achieve reliable locking of the payload and precise unlocking of the delivery action. The overall operation is convenient and the operation is highly reliable, and it can be fully adapted to the long-distance silent delivery operation of large unpowered gliding payloads.

[0024] Reference Figure 1 It should be noted that the aircraft referred to in this embodiment refers to various types of airplanes or drones, and the object to be dropped is a large gliding unmanned transport aircraft. Of course, the object to be dropped can also be other objects, such as relief supplies. The main body of this aircraft-mounted drop device is assembled at the external hardpoint of the aircraft fuselage, and as an external load-bearing drop mechanism, it completes the fixed mounting and aerial release operations of the gliding unmanned transport aircraft.

[0025] The aircraft mounting and delivery device includes a support frame 1, straps 2, and a drive assembly 3. The components work together to form an integrated mounting and delivery system. The overall assembly is highly integrated, and the parts are arranged in a neat manner, effectively avoiding the problems of loose and space-consuming traditional mounting structures.

[0026] Reference Figure 2 , Figure 3 and Figure 4 The support frame 1 serves as the core load-bearing structure. It is composed of multiple interconnected plates, which are fixed together by bolts to form a monolithic plate frame structure. The support frame 1 is reliably mounted to the external mounting position on the bottom of the aircraft fuselage using bolts. Its overall load-bearing strength meets the heavy-load requirements of medium to large-sized gliding unmanned transport aircraft, exhibiting excellent structural stability and vibration resistance. The bottom of the support frame 1 has pre-reserved mounting space to conform to the top contour of the gliding unmanned transport aircraft to achieve a close-fitting mounting support, avoiding localized stress concentration and fuselage deformation during mounting.

[0027] The bottom of the support frame 1 is integrally formed with multiple legs 13. In this embodiment, there are four legs 13, which are distributed on both sides and the front and rear ends of the bottom of the support frame 1, forming a multi-point support and load-bearing system. In some embodiments, the legs 13 are fixed to the bottom of the support frame 1 by bolts or welding. In other embodiments, the legs 13 can also be integrally formed with the support frame 1. Each leg 13 has a downward-facing slot 131 at its bottom end. The slot 131 adopts an open-type snap-fit ​​groove design and is U-shaped. It can accurately engage with the pre-set positioning protrusion or fixed point on the top of the gliding unmanned transport aircraft fuselage, realize the pre-positioning limit in the initial loading stage, effectively limit the lateral and longitudinal displacement and angular sway of the gliding unmanned transport aircraft, and ensure that the loaded gliding unmanned transport aircraft can only be launched from below the support frame 1. This greatly improves the structural stability in the flight loading state and avoids the impact of vibration load on the aerodynamic shape and flight attitude of the loaded aircraft during high-altitude flight.

[0028] The binding strap 2 is made of flexible, high-strength elastic band, serving as an auxiliary binding and restraint component in conjunction with the support frame 1 to achieve overall load fixation. The binding strap 2 is made of high-strength nylon or carbon fiber woven material, possessing high tensile strength, fatigue resistance, high and low temperature resistance, and minimal deformation, meeting the long-term load restraint requirements under complex high-altitude conditions. The binding strap 2 wraps around the bottom and sides of the gliding unmanned transport aircraft, tightly binding the entire aircraft to the bottom support plane of the support structure. Annular hanging rings 21 are fixedly mounted at both ends of the binding strap 2, symmetrically arranged on both sides, with uniform overall dimensions and balanced force distribution, ensuring stable mounting at pre-set mounting points on both sides of the support structure. This achieves tension and fixation of the binding strap 2. The flexible binding restraint of the binding strap 2 and the rigid support limit of the support structure work together to form a rigid-flexible dual-fixation structure, preventing slippage, displacement, and loosening under heavy load conditions.

[0029] The support frame 1 has an inner cavity, and the drive assembly 3 is installed in the inner cavity. The drive assembly 3 includes a drive element 31, a transmission structure 32, and a hook 33. The hanging ring 21 of the binding strap 2 is hung on the hook 33, and the hanging ring 21 is released by the rotation of the hook 33. There are two transmission structures 32 and two hooks 33, forming a set, respectively located on both sides of the drive element 31. That is, one drive element 31 simultaneously drives both sides of the transmission structure 32 and the hook 33. The layout is centrally symmetrical, effectively ensuring overall force balance and avoiding the force offset problem caused by unilateral drive. In this embodiment, the drive element 31 is a drive motor. The drive motor adopts a dual-sided coaxial output structure, which has strong power output synchronization and can realize synchronous linkage operation of the dual-sided structure, ensuring the consistency and synchronicity of the delivery action. The support frame 1 is also equipped with a power supply to provide power to the drive motor. The drive motor is locked and fixed to the middle end face of the support structure by the motor fixing bracket. The assembly is firm and has strong vibration resistance, which can adapt to complex working conditions such as high-altitude flight vibration and airflow impact, and avoid drive failure caused by motor loosening or displacement.

[0030] The transmission structure 32 and hook 33 arranged symmetrically on both sides are completely identical. The structural parameters, assembly positions and linkage logic of both sides are completely identical. The drive motor drives the two sets of transmission structures 32 to operate synchronously through the drive shafts 321 on both sides, so as to realize the synchronous unlocking and release of the hooks 33 on both sides. This ensures that the hanging rings 21 at both ends of the binding strap 2 are released synchronously, avoiding faults such as load tilting, attitude deflection and stuck placement caused by unlocking on one side first.

[0031] Each side of the transmission structure 32 includes a drive shaft 321, a transmission assembly 322, and a locking assembly 323. The transmission assembly 322 is a four-bar linkage mechanism, and the locking assembly 323 is a crank-slider 3233 mechanism. The linkage mechanism provides stable transmission, precise stroke, and smooth operation, and can accurately convert the rotational power of the motor into the rotational opening and closing action of the hook 33, thereby achieving stable locking and unlocking functions.

[0032] The transmission assembly 322 includes a first link 3221, a second link 3222, and a third link 3223, which are connected sequentially. The end of the first link 3221 is mounted on the outer end of the drive shaft 321. The first link 3221 is rotatably engaged with the drive shaft 321. That is, when the drive shaft 321 rotates, the first link 3221 does not rotate with it. Instead, it is engaged by other structures on the drive shaft 321, causing the first link 3221 to rotate with the drive shaft 321. The end of the first link 3221 away from the drive shaft 321 is hinged to the end of the second link 3222. The other end of the second link 3222 is hinged to the end of the third link 3223. The middle section of the third link 3223 is rotatably mounted on a fixed point on the side wall of the support structure, forming a swing structure that can rotate around the fixed point. The free end of the third link 3223 is fixedly mounted with a hook 33. Relying on the step-by-step linkage of multiple links, the drive shaft 321 can drive the hook 33 to complete a large-angle opening and closing action with a small rotation. The transmission efficiency is high and the action response is fast.

[0033] Furthermore, the hook 33 can be integrally formed with the third link 3223 to form an integrated structure, thereby reducing the number of parts and simplifying the structure.

[0034] It should be noted that the drive shaft 321 can drive the first connecting rod 3221 to rotate, but not by fixing the first connecting rod 3221 to the shaft hole connection of the drive shaft 321. Instead, the drive shaft 321 drives the first connecting rod 3221 to rotate by abutting against the first connecting rod 3221. In this embodiment, the first connecting rod 3221 and the shaft hole connection of the drive shaft 321 can rotate relative to each other. Specifically, an arc-shaped travel groove 3224 is formed at the end of the first connecting rod 3221 near the drive shaft 321. The arc-shaped travel groove 3224 is a long arc-shaped groove structure. A stop block 3211 is fixedly mounted at the outer end of the drive shaft 321. The stop block 3211 is fitted with the arc-shaped travel groove 3224 with clearance fit. The shape of the stop block 3211 is adapted to the groove shape of the arc-shaped travel groove 3224 and can slide and fit along the internal trajectory of the arc-shaped travel groove 3224.

[0035] Reference Figure 5 , Figure 6 and Figure 7The two side walls of the arc-shaped travel groove 3224 correspond to the locking position and the unlocking position, respectively. In the standby state, the stop block 3211 fits against one side wall of the arc-shaped travel groove 3224. The first connecting rod 3221 is locked and fixed by the locking and limiting function of the stop block 3211, thereby locking the entire connecting rod transmission assembly 322, limiting the swing displacement of the connecting rod, and finally locking and fixing the hook 33. This ensures that the hook 33 will not be accidentally opened due to vibration or airflow impact in the loaded state. When the release and unlocking action needs to be performed, the drive shaft 321 rotates, causing the stop block 3211 to slide along the arc-shaped travel groove 3224 until the stop block 3211 abuts against the other side wall of the arc-shaped travel groove 3224. The continuously rotating drive shaft 321, through the side wall of the stop block 3211, actuates the first connecting rod 3221 to swing, thereby driving the entire linkage transmission assembly 322 to operate in conjunction, driving the hook 33 to rotate and deflect, completing the opening and unlocking action of the hook 33. The overall travel limit is precise, which can effectively control the opening and closing angle of the hook 33 and avoid release failure caused by excessive action or insufficient travel.

[0036] Due to the large weight of the glider-type unmanned transport aircraft being carried, to prevent the drive motor's locking mechanism from failing due to the reaction force, the drive shaft 321 would rotate under the weight of the glider-type unmanned transport aircraft, causing the hook 33 to rotate and potentially leading to an accidental crash of the glider-type unmanned transport aircraft. The transmission structure 32 is equipped with an independent locking component 323, used for secondary locking and limiting of the linkage transmission system in the loaded state, further improving loading reliability and preventing linkage loosening or malfunction during flight.

[0037] The locking assembly 323 includes a first locking rod 3231, a second locking rod 3232, and a slider 3233. The first locking rod 3231 is fixedly mounted on the shaft of the drive shaft 321 and can rotate synchronously with the drive shaft 321. The outer end of the first locking rod 3231 is hinged to the end of the second locking rod 3232. The other end of the second locking rod 3232 is hinged to the top of the slider 3233. The slider 3233 is horizontally slidably mounted on the sliding guide rail on the side wall of the support frame 1. The slider 3233 can slide horizontally back and forth along the guide rail to realize the telescopic locking and reset release actions.

[0038] In the normal loading and locking state, the slider 3233 slides forward and extends, and the locking structure at the end of the slider 3233 extends into the bottom position of the second link 3222, forming a vertical locking limit on the second link 3222, restricting the vertical swing and horizontal displacement of the second link 3222. Together with the locking structure of the end arc-shaped stroke groove 3224, a double mechanical locking structure is formed, which completely locks the entire transmission link, prevents the hook 33 from being opened accidentally, and greatly improves the safety of heavy-load loading.

[0039] When the release and unlocking action is performed, the drive shaft 321 rotates, causing the first locking rod 3231 to rotate synchronously. The first locking rod 3231 pulls the second locking rod 3232 to deflect and swing, thereby pulling the slider 3233 to retract backward along the guide rail. The locking structure at the end of the slider 3233 disengages from the bottom of the second connecting rod 3222, releasing the locking limit on the second connecting rod 3222, thus completing the locking and unlocking. At this time, the linkage transmission assembly 322 is in a linkage working state, which can cooperate with the rotation of the drive shaft 321 to complete the opening action of the hook 33. The locking and unlocking linkage has strong synchronicity, requiring no additional independent control mechanism, and the structure is simple and the response is rapid.

[0040] Furthermore, in order to reduce the friction between the second connecting rod 3222 and the slider 3233, a limit bearing 3234 is integrally provided on the slider 3233. The bottom end of the second connecting rod 3222 abuts against the limit bearing 3234, converting sliding friction into rotational friction, which makes it easier for the slider 3233 to be pulled away from the bottom end of the second connecting rod 3222.

[0041] It should be noted that during the unlocking and deployment process, thanks to the structure of the arc-shaped travel groove 3224, the unlocking action of the slider 3233 is performed first. As the stop block 3211 moves from one side wall of the arc-shaped travel groove 3224 to the other side wall, the unlocking action of the slider 3233 is completed. Only after the unlocking action is completed can the rotation and deployment action of the hook 33 be performed.

[0042] Furthermore, in order to limit the movement of the second link 3222, a limiting baffle 11 is integrally formed on the upper end of the support structure corresponding to the swing motion range of the first link 3221 and the second link 3222. The limiting baffle 11 is located in the top area of ​​the link's motion trajectory, forming a top limiting protection structure. This structure can effectively limit the maximum lifting height during the swing of the link, avoid problems such as link overtravel, structural interference, and collision and wear of parts, and protect the internal links, hinge points, and locking structures, thereby improving the structural stability and service life.

[0043] This embodiment utilizes the mechanical limiting design of the second link 3222 to cut off the force transmission channel from the hook 33 to the drive shaft 321 and the drive motor. The large reverse force is no longer transmitted to the rear transmission components, but is directly borne by the upper limiting baffle 11 and the bottom slider 3233 of the second link 3222, which greatly reduces the risk of damage to the drive shaft 321 and the drive motor from impact loads, and effectively improves the durability of the drive assembly 3, the overall structural rigidity, and the operational stability.

[0044] Furthermore, in this embodiment, when the hook 33 is locked, the two first links 3221 are arranged horizontally, and the third link 3223 remains vertical, with the entire four-bar linkage precisely at its mechanical dead point. Relying on the dead point self-locking characteristic, the overturning torque generated by the load on the hook 33 can be offset, maintaining the stable locking of the hook 33 without requiring the drive motor to continuously output locking torque, reducing continuous load losses on the motor, and significantly improving locking reliability.

[0045] A transverse linkage shaft 324 is set between the two sets of symmetrically arranged transmission structures 32. The linkage shaft 324 is transversely arranged at the hinge axis of the second link 3222 and the third link 3223 on both sides. The linkage shaft 324 is coaxial with the hinge points on both sides, which can synchronize the swinging movements of the links on the left and right sides, further eliminate the movement error of the double-sided transmission structure 32, ensure that the opening and closing angle and opening and closing speed of the hooks 33 on both sides are completely consistent, avoid the problem of single-sided jamming of the binding strap 2 and the load tilting during delivery caused by asynchronous movements on both sides, and greatly improve the delivery stability and delivery accuracy.

[0046] A limiting groove 12 is provided at the mounting position of the hook 33 on the side of the support structure. The limiting groove 12 is a concave groove structure. The hook 33 is arranged at the opening of the limiting groove 12 with the opening facing downwards. The rotation trajectory of the hook 33 matches the contour of the opening of the limiting groove 12. In the mounted and locked state, the hook 33 completely closes the opening of the limiting groove 12, and the hanging ring 21 is stably fastened inside the hook 33, preventing it from coming off. During the deployment and unlocking process, the hook 33 rotates and deflects with the connecting rod, gradually opening the opening of the limiting groove 12. After the opening is fully open, the hanging ring 21 is unrestrained and can be smoothly released from the hook 33, completing the release of both ends of the binding strap 2, and finally achieving unrestrained and stable deployment of the gliding unmanned transport aircraft. The limiting groove 12's groove limiting design can accurately restrict the working position of the hook 33, avoiding unlocking failure caused by hook 33 offset or deformation, further improving the overall structural reliability.

[0047] The aircraft payload delivery device in this embodiment has a compact and well-organized overall assembly structure. All drive, transmission, and locking components are integrated and arranged inside and on the sides of the support structure, with no unnecessary protruding structures. This significantly reduces external aerodynamic drag and interference, making it suitable for high-altitude, high-speed flight conditions of the aircraft. The entire payload delivery process is driven by a unified motor and electronic control system, eliminating the need for manual on-site operation. The unlocking action is synchronous, smooth, and reliable, effectively meeting the silent delivery requirements of medium to large unpowered gliding unmanned transport aircraft. It solves the technical problems of poor adaptability, loose structure, low reliability, cumbersome operation, and easy failure during delivery associated with traditional payload structures. It has outstanding advantages such as compact structure, reliable load-bearing capacity, good synchronization, strong adaptability, and convenient operation and maintenance, meeting the requirements for high-frequency, high-precision, and high-reliability long-distance silent delivery of materials.

[0048] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the implementation of the present invention. Those skilled in the art will be able to make various obvious changes, readjustments, and substitutions without departing from the scope of protection of the present invention. It is neither necessary nor possible to exhaustively describe all embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the scope of protection of the claims of the present invention.

Claims

1. An aircraft payload delivery device, installed on an aircraft, characterized in that, include: Support frame (1), said support frame (1) is mounted on the aircraft; The binding strap (2) is used to bind the object to be placed to the bottom of the support frame (1). The binding strap (2) has hanging rings (21) at both ends of the binding strap (2) that hang on both sides of the support frame (1). A drive assembly (3) is provided on the support frame (1). The drive assembly (3) includes a drive member (31), a transmission structure (32), and a hook (33). The hanging ring (21) is fastened to the hook (33). The drive member (31) drives the hook (33) to rotate through the transmission structure (32), so that the hook (33) disengages from the hanging ring (21).

2. The aircraft payload delivery device according to claim 1, characterized in that, The transmission structure (32) includes: A drive shaft (321) is connected to the drive member (31); A transmission assembly (322) is connected to the drive shaft (321), and the hook (33) is disposed at the transmission end of the transmission assembly (322); A locking assembly (323) is used to lock or unlock the transmission assembly (322).

3. The aircraft payload delivery device according to claim 2, characterized in that, The transmission assembly (322) includes: The first link (3221) has its end rotatably mounted on the drive shaft (321); The second link (3222) has its end hinged to the end of the first link (3221) away from the drive shaft (321); The third link (3223) is rotatably mounted on the support frame (1). One end of the third link (3223) is hinged to the end of the second link (3222). The hook (33) is located at the other end of the third link (3223). Wherein, the first connecting rod (3221) is provided with an arc-shaped stroke groove (3224) at the end near the drive shaft (321), and a stop block (3211) is fixedly provided at the end of the drive shaft (321), and the stop block (3211) is disposed in the arc-shaped stroke groove (3224); When the stop (3211) abuts against one side wall of the arc-shaped travel groove (3224), the stop (3211) locks the transmission assembly (322) and stops the hook (33). When the stop (3211) abuts against the other side wall of the arc-shaped travel groove (3224), the stop (3211) moves the transmission assembly (322) and drives the hook (33) to open.

4. The aircraft payload delivery device according to claim 3, characterized in that, The locking assembly (323) includes: The first locking rod (3231) is fixed on the drive shaft (321); The second locking rod (3232) has its end hinged to the first locking rod (3231); The slider (3233) is slidably mounted on the support frame (1). The other end of the second locking rod (3232) is hinged to the slider (3233). The slider (3233) can extend into or out of the bottom of the second connecting rod (3222) to lock or release the second connecting rod (3222).

5. The aircraft payload delivery device according to claim 4, characterized in that, The drive member (31) is provided with the transmission structure (32) and the hook (33) on both sides, and the drive member (31) synchronously drives the transmission structure (32) and the hook (33) on both sides.

6. The aircraft payload delivery device according to claim 5, characterized in that, A linkage shaft (324) is also provided between the pair of transmission structures (32), and the ends of the linkage shaft (324) are respectively located on the hinge axis of the second link (3222) and the third link (3223).

7. The aircraft payload delivery device according to claim 6, characterized in that, The support frame (1) is also provided with a limiting wall (11), which is located at the top of the first connecting rod (3221) and the second connecting rod (3222).

8. The aircraft payload delivery device according to any one of claims 1-7, characterized in that, The support frame (1) is provided with a limiting groove (12), and the hook (33) is provided at the opening of the limiting groove (12); the hook (33) can open or close the opening of the limiting groove (12) by rotating.

9. The aircraft payload delivery device according to any one of claims 2-7, characterized in that, The driving component (31) is a drive motor, and there are two drive shafts (321), which are coaxially arranged on both sides of the driving component (31).

10. The aircraft payload delivery device according to any one of claims 1-7, characterized in that, The bottom of the support frame (1) is provided with multiple legs (13), and the bottom of each of the multiple legs (13) is provided with a slot (131) with the opening facing the direction.

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