A load release device and aircraft thereof

Abstract

The present application relates to a load release device and an aircraft thereof, which includes: a release cabin, a heat-proof cover, a first release assembly and a second release assembly, wherein a load accommodating cavity is provided in the release cabin, and an opening is provided at one end of the release cabin; the heat-proof cover is buckled on one side of the release cabin opening; the first release assembly is installed on the release cabin, and one end is connected to the heat-proof cover, and is used to push the heat-proof cover away from the release cabin; the second release assembly is installed on the release cabin, and one end of the second release assembly is used to fit with the load and drive the load close to the release cabin opening; wherein the heat-proof cover has a release position, and when the first release assembly pushes the heat-proof cover to the release position, a gap is formed between the heat-proof cover and the release cabin for the load to pass through. The present invention pushes the heat-proof cover to the release position by the first release assembly, and pushes the load by the second release assembly, so that the load can be moved out of the release cabin, thereby solving the problem of stable load release of the aircraft under high-speed and high dynamic pressure conditions.

Description

Technical Field

[0001] The present application relates to the field of aircraft, and in particular to a load release device and an aircraft thereof. Background Art

[0002] With the development of aircraft, the types of payloads released and the release conditions are becoming increasingly complex and varied, placing higher demands on existing aircraft payload release devices. Conventional release devices require the aircraft to maintain a certain attitude to accurately release the payload, which greatly increases the design complexity of the release device and the cost of the aircraft.

[0003] As a critical component of an aircraft, the release mechanism not only meets the requirements for loading and releasing payloads but also withstands the mechanical and thermal loads during flight and release. Therefore, the release mechanism's design must take into account factors such as the release power source, structural strength, and ambient temperature. Meeting the requirements for precise payload release under various complex operating conditions while also withstanding mechanical and thermal loads is a pressing challenge facing current aircraft payload release mechanism design. Summary of the Invention

[0004] The present application provides a load release device and an aircraft thereof, which can solve the problem in related technologies that the common release device needs to maintain a certain posture of the aircraft to complete the precise release of the load, which greatly increases the design complexity of the release device and the cost of the aircraft.

[0005] In a first aspect, an embodiment of the present application provides a load release device, comprising: a release cabin, a heat-proof cover, a first release assembly and a second release assembly, wherein a load accommodating cavity is provided in the release cabin, and an opening is provided at one end of the release cabin; the heat-proof cover is buckled on one side of the release cabin opening; the first release assembly is installed on the release cabin, and one end is connected to the heat-proof cover, and is used to push the heat-proof cover away from the release cabin; the second release assembly is installed on the release cabin, and one end of the second release assembly is used to fit with the load, and is used to drive the load close to the release cabin opening; wherein the heat-proof cover has a release position, and when the first release assembly pushes the heat-proof cover to the release position, a gap is formed between the heat-proof cover and the release cabin for the load to pass through.

[0006] In some embodiments, the load release device further includes a dimensional push plate, which is disposed inside the release chamber and has one end surface serving as a load placement surface. One end of the second release assembly is connected to the dimensional push plate.

[0007] In some embodiments, a groove is provided on the heat-proof cover plate, and the dimensional push plate is used to engage with the groove.

[0008] In some embodiments, the second release assembly is disposed on the bottom surface of the release cabin, a thrust hole is provided on the bottom surface of the release cabin, and a thrust hole is provided at the output end of the second release assembly.

[0009] In some embodiments, the second release assembly includes: a gas generator and a release cylinder, the gas generator is arranged on the release cabin; a gas pipeline is connected between the release cylinder and the gas generator, the fixed end of the release cylinder is connected to the release cabin, and the output end is used to fit the load.

[0010] In some embodiments, the release cylinder includes: a cylinder body and a thrust rod, wherein a gas inlet is provided at one end of the cylinder body, and the gas inlet is connected to the gas pipeline; the thrust rod is slidably connected to the inside of the cylinder body, and one end of the thrust rod passes through the other end of the cylinder body.

[0011] In some embodiments, a fixing bracket for fixing the second release assembly is provided on the release cabin.

[0012] In some embodiments, the heat-proof cover is made of a heat-proof composite material;

[0013] A sealing ring and a mounting boss are provided on the side of the heat-proof cover plate that contacts the release cabin.

[0014] In some embodiments, the release chamber surface is provided with mounting ears for fixing the first release assembly;

[0015] The first release assembly includes a cover-throwing actuator, one end of which is connected to the mounting ear, and the other end of which is connected to the heat-proof cover plate.

[0016] In a second aspect, an embodiment of the present application provides an aircraft, comprising: an aircraft body and the load release device as described above, wherein the release cabin is arranged on the aircraft body.

[0017] The beneficial effects of the technical solutions provided in the embodiments of the present application include:

[0018] An embodiment of the present application provides a load release device and an aircraft thereof, wherein a first release component pushes a heat-resistant cover plate to a release position so that a gap is formed between the heat-resistant cover plate and the release cabin for the load to pass through. At this time, a second release component pushes the load so that the load can be moved out of the release cabin through the gap, thereby solving the problem of stable load release of the aircraft under high-speed and high dynamic pressure conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0020] Figure 1 A schematic diagram of the overall structure provided for an embodiment of the present application;

[0021] Figure 2 A schematic diagram of a release chamber provided in an embodiment of the present application;

[0022] Figure 3 Schematic diagram of the release cylinder provided in an embodiment of the present application.

[0023] In the figure: 1. Heat-proof cover; 2. Release cabin; 20. Mounting lug; 21. Fixing bracket; 22. Thrust hole; 3. Cover ejection actuator; 4. Release cylinder; 40. Mounting hole; 41. Gas inlet; 42. Thrust rod; 43. Cylinder body; 5. Gas generator; 6. Gas pipeline; 7. Dimensional push plate; 8. Load. DETAILED DESCRIPTION

[0024] In order to enable those skilled in the art to better understand the present invention, the following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0025] See also Figures 1 to 3 The embodiment of the present application provides a load release device and an aircraft thereof, which can solve the problem that the common release device in the related art needs to accurately release the load under the premise that the aircraft maintains a certain posture, which greatly increases the design complexity of the release device and the cost of the aircraft.

[0026] In the first aspect, an embodiment of the present application provides a load release device, which includes: a release cabin 2, a heat-proof cover 1, a first release component and a second release component, wherein a load accommodating cavity is provided in the release cabin 2, and an opening is provided at one end of the release cabin 2; the heat-proof cover 1 is buckled on one side of the opening of the release cabin 2; the first release component is installed on the release cabin 2, and one end is connected to the heat-proof cover 1, and is used to push the heat-proof cover 1 away from the release cabin 2; the second release component is installed on the release cabin 2, and one end of the second release component is used to fit with the load 8, and is used to drive the load 8 close to the opening of the release cabin 2; wherein the heat-proof cover 1 has a release position, and when the first release component pushes the heat-proof cover 1 to the release position, a gap is formed between the heat-proof cover 1 and the release cabin 2 for the load 8 to pass through.

[0027] In the present application, the first release assembly pushes the heat-proof cover 1 to the release position, so that a gap is formed between the heat-proof cover 1 and the release cabin 2 for the load 8 to pass through. At this time, the second release assembly pushes the load 8 so that the load 8 can be moved out of the release cabin 2 through the gap, thereby solving the problem of stable release of the load 8 under high-speed and high dynamic pressure conditions of the aircraft.

[0028] The entire release device is designed as an independent modular unit relative to the aircraft, which improves assembly efficiency and allows the release energy of each payload 8 to be precisely controlled.

[0029] The release chamber 2, the main component of the release mechanism, adopts a box-shaped structure. This structure not only facilitates installation and operation but also ensures the stability of the internal components. As the main body of the release mechanism, the release chamber 2 is designed with a mechanical interface on its end face for mounting on the inner wall of the aircraft body. In terms of material selection, stainless steel is a preferred material for both durability and corrosion resistance, as it can withstand the various challenges of extreme environments. Furthermore, to further enhance the reliability of the release chamber 2 under high-temperature conditions, a heat-resistant cover 1 is installed at the opening of the release chamber 2. This design aims to achieve effective thermal protection, preventing external high temperatures from damaging the delicate components within the chamber.

[0030] In this embodiment, the surface of the heat-proof cover 1 is conformal to the outer surface of the aircraft body, bearing the mechanical and thermal loads during flight, playing a role in heat insulation, and reducing the impact of aerodynamic thermal heating and aerodynamic resistance. The specific material of the heat-proof cover 1 is a high-performance heat-proof composite material, such as a fiberglass composite material that has been specially processed. This material is selected for its light weight, high strength and excellent thermal insulation properties. It can effectively block the transfer of heat and achieve excellent heat protection. The use of fiberglass composite materials not only improves the thermal protection capability of the entire release device, but also ensures the stability and durability of the device in complex and changing mission environments.

[0031] Furthermore, the side of the heat shield 1 that mates with the release chamber 2 is equipped with a sealing ring and mounting bosses. Specifically, the side of the heat shield 1 that mates with the release chamber 2 is designed with a sealing ring and a stable mounting boss. This design ensures that when the heat shield 1 is snapped onto the opening of the release chamber 2, a tightly enclosed space is formed, thereby meeting the high sealing requirements for the internal environment of the release chamber 2 before the payload 8 is released.

[0032] As a key component, the seal ring's material selection is crucial. To ensure long-term stability under high temperatures, high pressures, and complex environmental conditions, the seal ring is constructed from a special synthetic rubber material that is resistant to high temperatures, aging, and corrosion. This material not only exhibits excellent elastic recovery, maintaining an excellent seal even after repeated opening and closing, but also effectively resists chemical attack from the external environment, extending its service life.

[0033] The mounting boss is designed for ease of installation and stability. Its regular shape and precise dimensions perfectly match the grooves at the opening of the release chamber 2, ensuring that the heat shield 1 can be quickly positioned during installation, eliminating the need for tedious adjustments to achieve the ideal installation position.

[0034] In actual operation, when the payload 8 needs to be released, the first release assembly pushes the heat shield 1 to open it, and the second release assembly pushes the payload 8 toward the side close to the heat shield 1. At this time, the payload 8, under the action of the second release assembly, can also push the heat shield 1 out and away from the aircraft, increasing the gap for the payload 8 to pass through and achieving a quick and safe release process for the payload 8. After the payload 8 is released, the heat shield 1 is re-fastened to the opening of the release chamber 2, forming a tightly enclosed space again, fully preparing for the next mission. This design not only meets the sealing requirements before the payload 8 is released, but also greatly improves the operational convenience and reliability of the entire release device.

[0035] Furthermore, load 8 is secured within the box-shaped structure's interior, or load-holding cavity, using specially crafted alloy straps. This crucial securing process ensures that load 8 remains absolutely secure throughout the entire process of transport to the designated location and awaiting release, effectively preventing movement or damage to load 8 caused by external factors such as bumps and vibrations. The alloy straps are made of a high-strength alloy material with excellent tensile strength and wear resistance, capable of withstanding the various stresses of load 8 during the securing process, ensuring a durable and reliable securement.

[0036] To facilitate the efficient movement of the second release assembly toward the opening of the release chamber 2, allowing for a smooth subsequent release, the alloy straps are designed with calculated and optimized prefabricated notches. The location, shape, and size of these notches have been rigorously tested and verified to ensure they meet strength requirements while achieving optimal breaking performance during the operation of the second release assembly.

[0037] When the second release assembly receives the release command from the control system and begins operating according to a pre-set procedure, it applies the alloy strap with appropriate force and speed. At this point, the prefabricated notch in the strap becomes the critical breaking point. As stress gradually accumulates, the strap snaps cleanly and quickly at this point, completely releasing the restraint on load 8. This design not only ensures that load 8 is securely fixed before release, but also ensures that the release operation is completed quickly and smoothly during release, achieving a seamless transition from fixation to release, significantly improving the reliability and operational efficiency of the entire system.

[0038] Based on the above embodiment, in this embodiment, the load release device also includes a dimensional push plate 7, which is arranged inside the release cabin 2, and one end face of the dimensional push plate 7 is a load 8 placement surface, and one end of the second release component is connected to the dimensional push plate 7.

[0039] Specifically, in this embodiment, the dimensional push plate 7 is disposed inside the load accommodating cavity. When the load 8 is installed inside the load accommodating cavity, the load 8 placement surface is disposed on the dimensional push plate 7 .

[0040] In some possible embodiments, the second release assembly may be located inside the load accommodating cavity, with one end connected to the dimensional push plate 7;

[0041] In some other possible embodiments, the second release assembly is disposed on the bottom surface of the release chamber 2 , a thrust hole 22 is provided on the bottom surface of the release chamber 2 , and the output end of the second release assembly is penetrated by the thrust hole 22 .

[0042] In this embodiment, a thrust hole 22 is provided at the output end of the second release assembly and is connected to the dimensional push plate 7, which can push the dimensional push plate 7 toward the side close to the opening, thereby pushing the load 8 out of the release cabin 2 from the gap between the heat-proof cover plate 1 and the release cabin 2.

[0043] The above embodiments are merely multiple possible implementations of the embodiments of the present application, and the embodiments of the present application are not limited thereto.

[0044] On the basis of the above embodiments, in this embodiment, the dimensional push plate 7, as a key component in the aircraft load 8 release system, adopts a high-strength, lightweight and corrosion-resistant fiberglass composite material as the main structure, and also combines it with a high-temperature resistant and mechanically good alloy material. The seamless combination of the two materials is achieved through bonding technology, which not only ensures the overall strength of the structure, but also gives the dimensional push plate 7 heat resistance and durability.

[0045] During the design process of the dimensional push plate 7, the dimensional push plate 7 is made to conform to the shape of the heat-proof cover plate 1. This not only improves the smoothness of the aircraft surface and reduces air resistance, but also ensures that the dimensional push plate 7 fits tightly with the heat-proof cover plate 1 after locking, effectively preventing the potential impact of the external environment on the internal structure of the aircraft.

[0046] To ensure stable locking of the dimensional push plate 7 after the load 8 is released, a prefabricated groove structure is incorporated into the heat-shielding cover 1. These grooves, rigorously mechanically calculated, ensure they can withstand the immense pressure exerted by the dimensional push plate 7 during locking. Their ingenious layout also provides precise docking locations for the dimensional push plate 7. Once the dimensional push plate 7 is pushed into position, its edges seamlessly engage within the grooves. This physical interlocking structure creates a stable and reliable locking mechanism. This design not only ensures the secure locking of the dimensional push plate 7 in extreme environments, but also greatly simplifies installation and removal, improving the overall system's operational efficiency.

[0047] The payload 8, under the action of the dimensional push plate 7, pushes the heat shield 1 out and away from the aircraft body. After the payload 8 is successfully pushed out, the dimensional push plate 7, under the action of the second release assembly, continues to push outward and locks into the groove in the heat shield 1, filling the opening formed in the release chamber 2 after the heat shield 1 is pushed out, and the payload accommodating chamber is once again formed into a sealed area. The surface of the dimensional push plate 7 conforms to the shape of the aircraft body, ensuring good aerodynamic performance after the payload 8 is released, while also providing heat insulation.

[0048] Based on the above embodiment, in this embodiment, the second release component includes: a gas generator 5 and a release cylinder 4, and the gas generator 5 is arranged on the release cabin 2; a gas pipeline 6 is connected between the release cylinder 4 and the gas generator 5, and the fixed end of the release cylinder 4 is connected to the release cabin 2, and the output end is used to fit with the load 8.

[0049] Specifically, the pyrotechnics stored in the gas generator 5 are ignited upon receiving the command, and the generated high-temperature and high-pressure gas is transmitted to the release cylinder 4 through the gas pipeline. In this process, the energy of the gas is fully utilized and converted into mechanical power to push the load 8 to release.

[0050] like Figure 3As shown, a gas inlet 41 is provided at one end of the cylinder 43. This gas inlet 41 is tightly connected to the gas pipeline 6, ensuring that high-pressure gas can accurately enter the cylinder 43. The internal space of the cylinder 43 provides ample sliding space for the thrust rod 42, allowing it to move freely under the power of the high-pressure gas. One end of the thrust rod 42 is slidably connected to the interior of the cylinder 43, while the other end passes through the other end of the cylinder 43 and directly connects to the dimensional push plate 7, forming a power transmission path.

[0051] When high-pressure gas enters the gas inlet 41 of the release cylinder 4 through the gas pipeline, its enormous energy instantly acts on the thrust rod 42, driving it to slide along the interior of the cylinder 43. This movement of the thrust rod 42, through its direct connection with the dimensional push plate 7, is converted into the force that pushes the load 8 to be released. Under the pushing action of the thrust rod 42, the dimensional push plate 7 pushes the load 8 out of the release chamber 2, completing the entire load 8 release process. This design not only ensures the accuracy and reliability of the load 8 release, but also greatly improves the overall efficiency and safety of the system.

[0052] On the basis of the above embodiment, in this embodiment, a fixing bracket 21 for fixing the second release assembly is provided on the release cabin 2 .

[0053] See also Figure 1 and Figure 2 As shown, the gas generator 5 is arranged on the fixing bracket 21, and the release cylinder 4 is fixed to the release cabin 2 through a fixing structure such as bolts at the mounting hole 40.

[0054] Furthermore, the release chamber 2 is provided with mounting lugs 20 for securing the first release assembly. This first release assembly includes a cover ejection actuator 3, one end of which is connected to the mounting lug 20 and the other end to the heat shield 1. The cover ejection actuator 3 is a thrust rod 42 driven by a small explosive device and is mounted on both sides of the release chamber 2 to push the heat shield 1 away from the aircraft.

[0055] In summary, the release device of the present application solves the problems of stable release of the load 8 of the aircraft under high-speed and high dynamic pressure conditions, anti-heat insulation problem inside the aircraft, and multiple release of the aircraft surface shape and load 8 after release. It has the advantages of simple structure, high assembly efficiency, strong load-bearing capacity, and good anti-heat insulation effect.

[0056] In a second aspect, an embodiment of the present application provides an aircraft, which includes: an aircraft body and a load release device provided by any of the above embodiments of the present application, wherein the release cabin 2 is arranged on the aircraft body.

[0057] In the present application, the first release assembly pushes the heat-proof cover 1 to the release position, so that a gap is formed between the heat-proof cover 1 and the release cabin 2 for the load 8 to pass through. At this time, the second release assembly pushes the load 8 so that the load 8 can be moved out of the release cabin 2 through the gap, thereby solving the problem of stable release of the load 8 under high-speed and high dynamic pressure conditions of the aircraft.

[0058] In some embodiments, the load release device includes: a release cabin 2, a heat-proof cover plate 1, a first release component and a second release component, wherein the release cabin 2 is provided with a load accommodating cavity, and one end of the release cabin 2 is provided with an opening; the heat-proof cover plate 1 is buckled on one side of the opening of the release cabin 2; the first release component is installed on the release cabin 2, and one end is connected to the heat-proof cover plate 1, and is used to push the heat-proof cover plate 1 away from the release cabin 2; the second release component is installed on the release cabin 2, and one end of the second release component is used to fit with the load 8, and is used to drive the load 8 close to the opening of the release cabin 2; wherein the heat-proof cover plate 1 has a release position, and when the first release component pushes the heat-proof cover plate 1 to the release position, a gap is formed between the heat-proof cover plate 1 and the release cabin 2 for the load 8 to pass through.

[0059] In some embodiments, the load release device further includes a dimensional push plate 7, which is disposed inside the release chamber 2, and one end surface of the dimensional push plate 7 is a load 8 placement surface, and one end of the second release assembly is connected to the dimensional push plate 7.

[0060] In some embodiments, a groove is provided on the heat-proof cover plate 1, and the dimensional push plate 7 is used to engage with the groove.

[0061] In some embodiments, the second release assembly is disposed on the bottom surface of the release chamber 2 , a thrust hole 22 is provided on the bottom surface of the release chamber 2 , and the output end of the second release assembly is penetrated by the thrust hole 22 .

[0062] In some embodiments, the second release assembly includes: a gas generator 5 and a release cylinder 4, the gas generator 5 is arranged on the release cabin 2; a gas pipeline 6 is connected between the release cylinder 4 and the gas generator 5, the fixed end of the release cylinder 4 is connected to the release cabin 2, and the output end is used to fit with the load 8.

[0063] In some embodiments, the release cylinder 4 includes: a cylinder body 43 and a thrust rod 42, wherein a gas inlet 41 is provided at one end of the cylinder body 43, and the gas inlet 41 is connected to the gas pipeline 6; the thrust rod 42 is slidably connected to the inside of the cylinder body 43, and one end of the thrust rod 42 passes through the other end of the cylinder body 43.

[0064] In some embodiments, a fixing bracket 21 for fixing the second release assembly is provided on the release cabin 2.

[0065] In some embodiments, the heat-proof cover plate 1 is made of a heat-proof composite material;

[0066] The side of the heat-proof cover plate 1 that contacts the release chamber 2 is provided with a sealing ring and a mounting boss.

[0067] In some embodiments, the surface of the release cabin 2 is provided with a mounting ear 20 for fixing the first release component; the first release component includes a cover-throwing actuator 3, one end of the cover-throwing actuator 3 is connected to the mounting ear 20, and the other end is connected to the heat-proof cover plate 1.

[0068] In the description of this application, it should be noted that the terms "upper" and "lower" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on this application. Unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be internal communication between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in this application can be understood according to the specific circumstances.

[0069] It should be noted that, in this application, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device comprising a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, an element defined by the sentence "comprising a ..." does not exclude the presence of other identical elements in the process, method, article or device comprising the element.

[0070] The foregoing is merely a list of specific embodiments of the present application, intended to enable those skilled in the art to understand or implement the present application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present application. Therefore, the present application is not limited to the embodiments shown herein, but is intended to conform to the broadest scope consistent with the principles and novel features of the present application.

Claims

1. A load release device, characterized in that: It includes: A release cabin (2), wherein a load accommodating cavity is provided in the release cabin (2), and an opening is provided at one end of the release cabin (2); A heat-proof cover plate (1), the heat-proof cover plate (1) being buckled onto one side of the opening of the release cabin (2); A first release assembly, which is mounted on the release chamber (2) and has one end connected to the heat-resistant cover plate (1) and is used to push the heat-resistant cover plate (1) away from the release chamber (2); a second release assembly, the second release assembly being mounted on the release chamber (2), one end of the second release assembly being adapted to engage with the load (8) and to drive the load (8) toward the opening of the release chamber (2); The heat-proof cover plate (1) has a release position. When the first release assembly pushes the heat-proof cover plate (1) to the release position, a gap is formed between the heat-proof cover plate (1) and the release chamber (2) for the load (8) to pass through.

2. The load release device according to claim 1, wherein: The load release device further comprises a dimensional push plate (7), which is arranged inside the release chamber (2), and one end surface of the dimensional push plate (7) is a load placement surface, and one end of the second release assembly is connected to the dimensional push plate (7).

3. The load release device according to claim 2, wherein: The heat-proof cover plate (1) is provided with a groove, and the dimensional push plate (7) is used for engaging with the groove.

4. The load release device according to claim 1, wherein: The second release component is arranged on the bottom surface of the release chamber (2), a thrust hole (22) is provided on the bottom surface of the release chamber (2), and the output end of the second release component is penetrated by the thrust hole (22).

5. The load release device according to claim 1, wherein: The second release assembly comprises: a gas generator (5), the gas generator (5) being arranged on the release cabin (2); A release cylinder (4) is provided, wherein a gas pipeline (6) is connected between the release cylinder (4) and the gas generator (5); a fixed end of the release cylinder (4) is connected to the release cabin (2); and an output end is used for contacting with a load (8).

6. The load release device according to claim 5, characterized in that: The release cylinder (4) comprises: A cylinder body (43), wherein one end of the cylinder body (43) is provided with a gas inlet (41), and the gas inlet (41) is connected to a gas pipeline (6); A thrust rod (42) is slidably connected to the interior of the cylinder body (43), and one end of the thrust rod (42) passes through the other end of the cylinder body (43).

7. The load release device according to claim 1, wherein: The release chamber (2) is provided with a fixing bracket (21) for fixing the second release assembly.

8. The load release device according to claim 1, wherein: The heat-proof cover plate (1) is made of a heat-proof composite material; A sealing ring and a mounting boss are provided on the side of the heat-proof cover plate (1) that contacts the release chamber (2).

9. The load release device according to claim 1, wherein: The surface of the release cabin (2) is provided with a mounting lug (20) for fixing the first release assembly; The first release assembly comprises a cover-throwing actuator (3), one end of which is connected to the mounting lug (20) and the other end of which is connected to the heat-proof cover plate (1).

10. An aircraft, characterized in that: It includes: Aircraft body; The load release device according to any one of claims 1 to 9, wherein the release cabin (2) is arranged on the aircraft body.

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