Load releasing device and aircraft thereof

Abstract

The invention relates to a load releasing device and an aircraft thereof, the load releasing device comprises a releasing cabin, a heat-proof cover plate, a first releasing assembly and a second releasing assembly, a load containing cavity is formed in the releasing cabin, and an opening is formed in one end of the releasing cabin; the heat-proof cover plate is buckled on one side of the opening of the release cabin; the first release assembly is mounted on the release cabin, one end of the first release assembly is connected with the heat-proof cover plate, and the first release assembly is used for pushing the heat-proof cover plate away from the release cabin; the second releasing assembly is mounted on the releasing cabin, and one end of the second releasing assembly is attached to the load and used for driving the load to approach the opening of the releasing cabin; wherein the heat-proof cover plate is provided with a release position, and when the first release assembly pushes the heat-proof cover plate to the release position, a gap for a load to penetrate through is formed between the heat-proof cover plate and the release cabin. The heat-proof cover plate is pushed to the release position through the first release assembly, the load is pushed through the second release assembly, the load can be moved out of the release cabin, and stable release of the load of an aircraft under the high-speed and large-dynamic-pressure working condition is achieved.

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 and conditions of aircraft load release are becoming more and more complex and changeable, which puts higher requirements on existing aircraft load release devices. Common release devices need to accurately release the load under the premise that the aircraft maintains a certain attitude, which greatly increases the design complexity of the release device and the cost of the aircraft.

[0003] As an important part of an aircraft, the release device of an aircraft not only meets the requirements of loading and releasing the load, but also has to withstand the mechanical and thermal loads during the flight and release process. Therefore, when designing the release device, factors such as the release power source, structural strength, and ambient temperature must be taken into consideration. While meeting the requirements for accurate release of the load under various complex working conditions, being able to withstand mechanical and thermal loads is an urgent problem that needs to be solved in the current design of aircraft load release devices. 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 accurate 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 plate, a first release component and a second release component, 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 plate is buckled on one side of the release cabin opening; the first release component is installed on the release cabin, and one end is connected to the heat-proof cover plate, and is used to push the heat-proof cover plate away from the release cabin; the second release component is installed on the release cabin, and one end of the second release component 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 plate has a release position, and when the first release component pushes the heat-proof cover plate to the release position, a gap is formed between the heat-proof cover plate 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 of the dimensional push plate as a load placement surface, and 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 formed on the bottom surface of the release cabin, and a thrust hole is formed at an 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, 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-resistant cover plate is made of a heat-resistant composite material;

[0013] A sealing ring and a mounting boss are provided on the side of the heat-proof cover plate that is in contact with 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 comprises 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 a load release device as described above, wherein the release cabin is arranged on the aircraft body.

[0017] The beneficial effects brought by the technical solution 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 a 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 drawings required for use in the description of the embodiments will be briefly introduced below. 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 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 cabin 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 solution of the present application, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, 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 plate 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 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.

[0027] In the present application, the first release component pushes the heat protection cover 1 to the release position so that a gap is formed between the heat protection cover 1 and the release cabin 2 for the load 8 to pass through. At this time, the second release component 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 in an independent modular manner relative to the aircraft, which improves assembly efficiency and allows the release energy of each payload 8 to be precisely controlled.

[0029] Among them, the main part of the release device, the release cabin 2, adopts a box-type structure, which is not only easy to install and operate, but also ensures the stability of the internal components. The release cabin 2 is the main body of the release device, and the end face is designed with a mechanical interface that is installed with the inner wall of the aircraft body. In terms of material selection, in order to take into account durability and corrosion resistance, stainless steel can be used as a preferred material, which can withstand various challenges in extreme environments. In addition, in order to further enhance the reliability of the release cabin 2 under high temperature conditions, a heat-proof cover 1 is set at the opening of the release cabin 2. This design aims to achieve effective thermal protection and prevent external high temperatures from damaging the precision components in the cabin.

[0030] In this embodiment, the surface of the heat-proof cover plate 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 weakening the impact of aerodynamic thermal heating and aerodynamic resistance. The specific material of the heat-proof cover plate 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 performance. It can effectively block the transfer of heat and play an excellent heat-proof effect. 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, a sealing ring and a mounting boss are provided on the side of the heat-proof cover plate 1 that fits the release chamber 2. Specifically, a sealing ring with sealing performance and a stable mounting boss are designed on the side of the heat-proof cover plate 1 that fits the release chamber 2. Such a design ensures that when the heat-proof cover plate 1 is buckled on the opening of the release chamber 2, a tightly closed space can be formed, thereby meeting the high sealing requirements for the internal environment of the release chamber 2 before the load 8 is released.

[0032] As a key component, the material selection of the sealing ring is crucial. In order to ensure long-term stability under high temperature, high pressure and complex environmental conditions, the sealing ring is made of a special synthetic rubber material that is resistant to high temperature, aging and corrosion. This material not only has good elastic recovery ability and can maintain excellent sealing effect after multiple openings and closings, but also can effectively resist chemical erosion in the external environment and extend the service life.

[0033] The design of the mounting boss fully considers the convenience and stability of installation. The boss has a regular shape and precise size, and perfectly matches the groove at the opening of the release chamber 2, ensuring that the heat protection cover 1 can be quickly positioned during installation and can achieve the ideal installation position without tedious adjustments.

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

[0035] Furthermore, the load 8 is fixed in the internal space of the box-shaped structure, that is, in the load accommodating cavity, by a specially made alloy strap. This fixing process is crucial, as it ensures that the load 8 remains absolutely stable during the entire process of being transported to the designated location and waiting to be released, and effectively prevents the load 8 from moving or being damaged due to external factors such as bumps and vibrations. The alloy strap is made of high-strength alloy material, has excellent tensile strength and wear resistance, and can withstand various stresses of the load 8 during the fixing process, ensuring that the fixing effect is long-lasting and reliable.

[0036] In order to facilitate the second release assembly to efficiently drive the load 8 close to the opening of the release chamber 2, so as to smoothly complete the subsequent release operation, calculated and optimized prefabricated notches are set on the alloy strap. The position, shape and size of these notches have been strictly tested and verified to ensure that they can achieve the best breaking effect when the second release assembly is working while meeting the strength requirements.

[0037] When the second release component receives the release command from the control system and starts to work according to the predetermined program, it will act on the alloy strap with appropriate force and speed. At this time, the prefabricated notch on the strap will become the key point of fracture. As the stress gradually accumulates, the strap will break neatly and quickly here, thus completely releasing the restraint on the load 8. This design not only ensures the stable fixation of the load 8 before release, but also ensures that the load 8 can complete the release operation quickly and smoothly when released, realizing seamless connection from fixation to release, greatly improving the reliability and operation efficiency of the entire system.

[0038] Based on the above embodiments, in this embodiment, the load release device also includes 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 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, and 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 formed on the bottom surface of the release chamber 2, and the thrust hole 22 is formed at the output end of the second release assembly.

[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 a high-temperature resistant alloy material with good mechanical properties. 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 protection cover plate 1, which 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 protection cover plate 1 after being locked, effectively preventing the potential impact of the external environment on the internal structure of the aircraft.

[0046] In order to achieve stable locking of the dimensional push plate 7 after the load 8 is released, a groove structure is prefabricated on the heat-proof cover plate 1. These grooves have been strictly mechanically calculated to ensure that they can withstand the huge pressure when the dimensional push plate 7 is locked. Through clever layout, accurate docking positions are provided for the dimensional push plate 7. When the dimensional push plate 7 is pushed into place, its edge can be seamlessly snapped into the groove, and a stable and reliable locking mechanism is formed through the mutual interlocking of physical structures. This design not only ensures the firm locking of the dimensional push plate 7 in extreme environments, but also greatly simplifies the installation and disassembly process, and improves the operating efficiency of the entire system.

[0047] Among them, the load 8 pushes the heat-proof cover plate 1 out and away from the aircraft body under the action of the dimensional push plate 7. After the load 8 is successfully pushed out, the dimensional push plate 7 will continue to be pushed outward and stuck into the groove on the heat-proof cover plate 1 under the action of the second release component, filling the opening formed on the release cabin 2 after the heat-proof cover plate 1 is pushed out, so that the load accommodating cavity forms a closed area again. The surface of the dimensional push plate 7 is conformal to the shape of the aircraft body, which ensures the good aerodynamic performance of the aircraft after the load 8 is released, and plays a role in heat insulation.

[0048] On the basis of the above embodiments, in this embodiment, the second release component 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.

[0049] Specifically, the pyrotechnics stored in the gas generator 5 are ignited after 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, and the gas inlet 41 is closely connected to the gas pipeline 6, ensuring that the high-pressure gas can accurately enter the cylinder 43. The internal space of the cylinder 43 provides sufficient sliding tracks for the thrust rod 42, so that it can move freely under the drive of the high-pressure gas. One end of the thrust rod 42 is slidably connected to the inside of the cylinder 43, and the other end passes through the other end of the cylinder 43 and is directly connected to the V-shaped push plate 7, forming a power transmission path.

[0051] When the high-pressure gas enters the gas inlet 41 of the release cylinder 4 through the gas pipeline, its huge energy instantly acts on the thrust rod 42, driving the thrust rod 42 to slide along the inside of the cylinder body 43. This movement of the thrust rod 42 is converted into power to push the load 8 to release through its direct connection with the dimensional push plate 7. Under the pushing action of the thrust rod 42, the dimensional push plate 7 pushes the load 8 out of the release cabin 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 on the release cabin 2 through a fixing structure such as bolts at the mounting hole 40 .

[0054] Furthermore, the surface of the release cabin 2 is provided with mounting ears 20 for fixing the first release assembly. The first release assembly includes a cover-throwing actuator 3, one end of which is connected to the mounting ears 20, and the other end is connected to the heat-proof cover 1. The cover-throwing actuator 3 is a thrust rod 42 driven by a small pyrotechnic, which is arranged and installed on both sides of the release cabin 2, and is used to push the heat-proof cover 1 away from the aircraft.

[0055] In summary, the release device of the present application solves the problems of stable release of load 8 of the aircraft under high speed and high dynamic pressure conditions, anti-heat insulation problem inside the aircraft, and multiple release of 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 component pushes the heat protection cover 1 to the release position so that a gap is formed between the heat protection cover 1 and the release cabin 2 for the load 8 to pass through. At this time, the second release component 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 formed on the bottom surface of the release chamber 2 , and the thrust hole 22 is formed at the output end of the second release assembly.

[0062] In some embodiments, the second release assembly includes: a gas generator 5 and a release cylinder 4, wherein the gas generator 5 is disposed 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 cabin 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 the present application, it should be noted that the terms "upper", "lower", etc. 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 the present application and simplifying the description, rather than indicating or implying 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 the present 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 it can be an indirect connection through an intermediate medium, or it can be a connection between the two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present 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 only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such 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 including 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, the elements defined by the sentence "comprise a ..." do not exclude the presence of other identical elements in the process, method, article or device including the elements.

[0070] The above description is only a specific implementation of the present application, so that those skilled in the art can understand or implement the present application. Various modifications to these embodiments will be apparent to those skilled in the art, and the general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present application. Therefore, the present application will not be limited to the embodiments shown herein, but will conform to the widest range consistent with the principles and novel features applied for herein.

Claims

1. A load release device, characterized in that: It includes: A release cabin (2), wherein a load accommodating cavity is arranged in the release cabin (2), and an opening is arranged at one end of the release cabin (2); A heat-proof cover plate (1), wherein the heat-proof cover plate (1) is buckled onto one side of the opening of the release cabin (2); A first release assembly, the first release assembly being mounted on the release chamber (2) and having one end connected to the heat-resistant cover plate (1) and being 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 fit the load (8) so as to drive the load (8) close to the opening of the release chamber (2); The heat-proof cover plate (1) has a release position, and 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, characterized in that: 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, characterized in that: 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, characterized in that: 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 thrust hole (22) is penetrated at the output end of the second release component.

5. The load release device according to claim 1, characterized in that: The second release assembly comprises: a gas generator (5), wherein the gas generator (5) is arranged on the release cabin (2); A release cylinder (4), 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).

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 inside 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, characterized in that: The release cabin (2) is provided with a fixing bracket (21) for fixing the second release assembly.

8. The load release device according to claim 1, characterized in that: 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, characterized in that: 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 ear (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; According to any one of claims 1 to 9, the release cabin (2) is arranged on the aircraft body.

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