Aircraft interstage separation method and aircraft

Abstract

The present application provides an aircraft interstage separation method and an aircraft. The aircraft interstage separation method includes: a combustion stage and a separation stage performed in sequence; in the combustion stage: the aircraft is moved at the original acceleration, and under the original acceleration, a conversion member movably arranged in the lower stage of the aircraft is overweight and compresses a locking member, so that the locking member jams the upper stage and the lower stage of the aircraft to lock; in the separation stage: the acceleration of the aircraft is reduced, so that the upper stage and the lower stage move at a current acceleration less than the original acceleration, and the conversion member moves relative to the lower stage in the direction of the upper stage based on the inertia of maintaining the original acceleration, so that the locking member jamming the upper stage and the lower stage is released to unlock. The present application realizes automatic triggering separation, which can not only meet the maneuvering requirements, but also avoid the problems caused by the use of pyrotechnics.

Description

Technical Field

[0001] The present application relates to the field of aerospace technology, and in particular to an aircraft inter-stage separation method and an aircraft. Background Art

[0002] Interstage separation is the process of separating the lower stage from the upper stage after the lower stage of a multi-stage vehicle (such as a rocket, missile, etc.) is shut down. The purpose is to separate and discard the lower stage that has exhausted the propellant.

[0003] Currently, pyrotechnics (such as explosive bolts or cutting ropes) or pen-cap separation methods are often used for stage separation, but there are problems such as strict management and control, unreliable supply cycles, or difficulty in meeting mobility or control requirements. Summary of the invention

[0004] In view of the shortcomings of the existing methods, the present application proposes an aircraft inter-stage separation method and an aircraft, which can realize automatic triggered separation, which can not only meet the maneuvering or control requirements, but also avoid the problems caused by the use of pyrotechnics.

[0005] In a first aspect, an embodiment of the present application provides an aircraft interstage separation method, comprising: a combustion stage and a separation stage performed sequentially;

[0006] During the combustion phase:

[0007] The aircraft is moved at an original acceleration, under which a conversion member movably disposed in a lower stage of the aircraft is overweight and presses a locking member, so that the locking member clamps the upper stage and the lower stage of the aircraft to lock;

[0008] During the separation phase:

[0009] The acceleration of the aircraft is reduced so that the upper stage and the lower stage move at a current acceleration less than the original acceleration. Based on the inertia of maintaining the original acceleration, the conversion member moves toward the direction of the upper stage relative to the lower stage, thereby releasing the locking members that jam the upper stage and the lower stage to unlock them.

[0010] Optionally, the conversion member is elastically connected to the lower stage via an elastic member;

[0011] During the combustion phase, the overweight of the conversion element causes the elastic element to compress, and the elastic element stores energy;

[0012] During the separation phase, the conversion member moves toward the upper stage relative to the lower stage under the action of the inertial force maintaining the original acceleration and the elastic force provided by the elastic member, releasing the pressure on the locking member to unlock the upper and lower stages.

[0013] Optionally, during the combustion phase:

[0014] Get acceleration instructions;

[0015] The engine of the lower stage is controlled to ignite according to the acceleration instruction, and the propellant of the engine of the lower stage is burned to make the aircraft move at the original acceleration.

[0016] Optionally, reducing the acceleration of the aircraft includes:

[0017] When the propellant of the lower stage engine is exhausted and the upper stage engine has not yet started working, the vehicle enters the separation phase;

[0018] In the separation phase, under the effect of aerodynamic drag, the acceleration of the aircraft decreases from the original acceleration to the current acceleration.

[0019] Optionally, reducing the acceleration of the aircraft includes:

[0020] When the aircraft reaches the set speed, the control system sends a separation command and the aircraft enters the separation phase;

[0021] According to the separation instruction, the engine of the lower stage is controlled to be shut down or the propellant combustion of the engine of the lower stage is reduced to reduce the acceleration of the aircraft.

[0022] Optionally, a groove is provided in the upper stage, a first through hole is provided in the side wall of the lower stage, and the locking member is movably disposed in the first through hole;

[0023] The conversion member has a concave and a convex which are sequentially arranged on the outer wall surface along the direction from the lower stage to the upper stage; the concave transitions smoothly to the convex;

[0024] During the combustion stage, the overweight of the conversion piece causes the protrusion to abut against the locking piece, pressing the locking piece into the groove to clamp the upper stage and the lower stage;

[0025] In the separation stage, the conversion member moves relative to the lower stage toward the upper stage, so that the depression is located on the side of the first through hole away from the groove, providing a receiving space for the locking member to be released from the groove, so that the upper stage and the lower stage are unlocked.

[0026] Optionally, in the separation stage, after the connection between the upper stage and the lower stage is released, the method further includes:

[0027] A separation force is applied to at least one of the upper stage and the lower stage to separate the upper stage from the lower stage.

[0028] Optionally, a mounting member, a connecting member and an anti-slip member are provided in the lower stage. The mounting member is connected to the side wall of the lower stage and is provided with a second through hole. One end of the connecting member passes through the second through hole and is connected to the conversion member. The elastic member is provided on the outer periphery of the connecting member and abuts against the conversion member and the mounting member respectively. The conversion member drives the connecting member to move axially along the second through hole. The anti-slip member is provided at the other end of the connecting member to prevent the connecting member from falling out of the second through hole.

[0029] Optionally, along the circumference of the upper stage, a plurality of grooves are sequentially spaced apart in the upper stage; along the circumference of the lower stage, a plurality of first through holes are sequentially spaced apart in the side wall of the lower stage, and at least one steel ball is provided in each first through hole as a locking piece; the number of the grooves is greater than or equal to the number of the first through holes.

[0030] In a second aspect, an embodiment of the present application provides an aircraft, including an upper stage and a lower stage, wherein the upper stage and the lower stage are separated using the above-mentioned aircraft inter-stage separation method.

[0031] The beneficial technical effects brought about by the technical solution provided by the embodiment of the present application include:

[0032] In the embodiment of the present application, during the combustion stage, the aircraft has an original acceleration, and the upper stage, lower stage and conversion member of the aircraft all move under the original acceleration. Since the conversion member is movably arranged in the lower stage, under the original acceleration, the conversion member is overweight (or overloaded) and presses the locking member, so that the locking member is located in the locking position, and the lower stage and the upper stage are locked and connected together. When the aircraft enters the separation stage, the acceleration of the aircraft is switched from the original acceleration to the current acceleration less than the original acceleration, and the upper stage and the lower stage of the aircraft move at the current acceleration. The conversion member movably arranged in the lower stage cooperates with the locking member based on the inertia of maintaining the original acceleration, so that the locking member is located in the unlocking position, and the lower stage and the upper stage are unlocked.

[0033] In the embodiment of the present application, the aircraft relies on the inertial force caused by the overload during movement or the maneuvering during movement to adjust the position of the conversion member and the locking member, realize the conversion of the position (locked position and unlocked position) of the locking member, and thus control the state of the lower stage and the upper stage (locked connection state or unlocked detachable state). Without using pyrotechnics, explosives, external instructions, or any electrical interface, the aircraft can be designed to use the characteristics of acceleration change (from the original acceleration to the current acceleration less than the original acceleration) as a trigger mechanism for the passive separation of the lower stage and the upper stage, and automatic triggering separation can be achieved when certain conditions are met.

[0034] The aircraft inter-stage separation method of the embodiment of the present application can improve the connection stiffness between the lower stage and the upper stage without pyrotechnics, and is completely independent of any external control. It can meet maneuvering or control requirements and avoid the problems caused by the use of pyrotechnics.

[0035] Additional aspects and advantages of the present application will be partially given in the following description, which will become apparent from the following description, or will be understood through the practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] The above and / or additional aspects and advantages of the present application will become apparent and easily understood from the following description of the embodiments in conjunction with the accompanying drawings, in which:

[0037] Figure 1 A schematic flow chart of an aircraft inter-stage separation method provided in an embodiment of the present application;

[0038] Figure 2 A sectional view of an aircraft provided in an embodiment of the present application, wherein the locking structure is located in a locked position.

[0039] Reference numerals:

[0040] 100-inter-stage separation system; 10-first separation body; 11-first accommodating chamber; 12-first through hole; 13-mounting piece; 14-second through hole; 15-first wall section; 16-second wall section; 17-third wall section; 20-second separation body; 21-second accommodating chamber; 22-groove; 30-locking piece; 40-switching structure; 41-conversion piece; 42-locking fitting part; 43-unlocking fitting part; 44-adjusting component; 45-elastic piece; 46-limiting anti-slip structure; 47-connecting piece; 48-anti-slip piece. DETAILED DESCRIPTION

[0041] The embodiments of the present application are described below in conjunction with the drawings in the present application. It should be understood that the implementation methods described below in conjunction with the drawings are exemplary descriptions for explaining the technical solutions of the embodiments of the present application and do not constitute a limitation on the technical solutions of the embodiments of the present application.

[0042] Those skilled in the art will appreciate that, unless expressly stated, the "said" and "the" used herein may also include plural forms. It should be further understood that the term "including" used in the specification of the present application refers to the presence of the features, integers, steps, operations, elements and / or components, but does not exclude the implementation of other features, information, data, steps, operations, elements, components and / or combinations thereof supported by the technical field. The term "and / or" used herein refers to at least one of the items defined by the term, for example, "A and / or B" may be implemented as "A", or as "B", or as "A and B".

[0043] In order to make the objectives, technical solutions and advantages of the present application clearer, the implementation methods of the present application will be further described in detail below with reference to the accompanying drawings.

[0044] The aircraft inter-stage separation method and aircraft provided in the present application are intended to provide a separation method that can meet maneuverability or control requirements while avoiding the use of pyrotechnics.

[0045] The following is a detailed description of the technical solution of the present application and how the technical solution of the present application solves the above technical problems with specific embodiments. It should be noted that the following implementations can refer to, draw on or combine with each other, and the same terms, similar features and similar implementation steps in different implementations will not be described repeatedly.

[0046] The present application embodiment provides an interstage separation system 100, the structural schematic diagram of the interstage separation system 100 is as follows Figure 2 As shown, the first separation body 10 , the second separation body 20 , the locking member 30 and the switching structure 40 are included.

[0047] The first separation body 10 has a first accommodating cavity 11 ; the second separation body 20 has a second accommodating cavity 21 for accommodating part of the first separation body 10 , and a groove 22 is provided on the inner wall of the second separation body 20 , which is communicated with the second accommodating cavity 21 .

[0048] The locking piece 30 is movably disposed on the side wall of the first separation body 10. The locking piece 30 has a locking position relative to the side wall of the first separation body 10, where the locking piece 30 enters the groove 22 to lock the first separation body 10 and the second separation body 20, and an unlocking position where the locking piece 30 escapes from the groove 22 to unlock the first separation body 10 and the second separation body 20.

[0049] The switching structure 40 is movably disposed in the first accommodating cavity 11 , and the switching structure 40 is used to cooperate with the locking member 30 to switch the position of the locking member 30 .

[0050] When the first separation body 10 and the second separation body 20 need to be locked and connected together, a portion of the first separation body 10 is placed in the second accommodating cavity 21, and the locking member 30 is made to correspond to the groove 22. The switching structure 40 cooperates with the locking member 30 to make the locking member 30 enter the groove 22, thereby locking and connecting the first separation body 10 and the second separation body 20 (in a locked connection state). Figure 2 When the first separation body 10 and the second separation body 20 that are locked and connected together need to be unlocked and separated, the position of the switching structure 40 in the first accommodating cavity 11 is adjusted, and the switching structure 40 cooperates with the locking member 30 so that the locking member 30 can be disengaged from the groove 22, thereby unlocking the first separation body 10 and the second separation body 20 (in an unlocked and separable state), and there is no longer a locking force between the first separation body 10 and the second separation body 20, and they can move away from each other under the action of an external force (such as a separation force), thereby achieving the purpose of separation.

[0051] In the embodiment of the present application, if the first separation body 10 and the second separation body 20 do not need to be separated (i.e., locked and connected together), the inter-stage separation system 100 is moved under the original acceleration (the movement direction is from the first separation body 10 to the second separation body 20). Since the switching structure 40 is movably arranged in the first accommodating chamber 11, the switching structure 40 (specifically the conversion member 41) is in an overweight (or overloaded) state under the original acceleration. At this time, the switching structure 40 cooperates with the locking member 30 based on the original acceleration, so that the locking member 30 is located in the locked position, and the first separation body 10 and the second separation body 20 are locked and connected together. The first separation body 10 and the second separation body 20 are in a locked connection state, such as Figure 2 shown.

[0052] If the first separation body 10 and the second separation body 20 need to be separated, the acceleration of the interstage separation system 100 is switched from the original acceleration to a current acceleration that is less than the original acceleration. During the switching process, the switching structure 40 has the inertia to maintain the original acceleration. Since the inter-stage separation system 100 moves in the direction from the first separation body 10 to the second separation body 20, when the acceleration is switched to the current acceleration, the first separation body 10 and the second separation body 20 both move under the current acceleration. At this time, under the action of the inertial force maintaining the original acceleration, the switching structure 40 moves relative to the first accommodating cavity 11 in the direction from the first separation body 10 to the second separation body 20, so that the position of the switching structure 40 and the locking member 30 is changed. The switching structure 40 cooperates with the locking member 30 based on the inertia of maintaining the original acceleration, and the locking member 30 switches to the unlocked position, thereby switching the first separation body 10 and the second separation body 20 to an unlocked and separable state. The locking member 30 is in the unlocked position, and there is no longer a locking force between the first separation body 10 and the second separation body 20, and they can move away from each other under the action of an external force (such as a separation force), so that the first separation body 10 and the second separation body 20 are unlocked, thereby achieving the separation purpose.

[0053] In the embodiment of the present application, the interstage separation system 100 adjusts the position of the switching structure 40 in the first accommodating chamber 11 by means of the inertial force caused by the overload in the movement (such as flying) or the maneuvering in the movement, so as to switch the locking member 30 between the locked position and the unlocked position, thereby controlling the state (locked connection state or unlocked separable state) of the first separation body 10 and the second separation body 20. Without using pyrotechnics, without explosives, without external instructions, and without setting any electrical interface, the interstage separation system 100 can be designed to use the characteristics of acceleration change (from the original acceleration to the current acceleration less than the original acceleration) as the trigger mechanism for the passive separation of the first separation body 10 and the second separation body 20 in the embodiment of the present application, and when certain conditions are met (such as the adjustment of the position of the switching structure 40 due to the acceleration change is sufficient to release the locking member 30 from the groove 22), the automatic triggering separation can be realized.

[0054] The inter-stage separation system 100 of the embodiment of the present application can improve the connection stiffness between the first separation body 10 and the second separation body 20 without pyrotechnics, and is completely independent of any external control. It can meet the mobility or control requirements and avoid the problems caused by the use of pyrotechnics (such as unreliable supply cycles, delays in project progress, etc.).

[0055] It should be noted that, in the embodiment of the present application, at least part includes part or all. Of course, in other optional embodiments of the present application, the second accommodating chamber 21 can also be used to accommodate the entire first separation body 10 according to actual needs. When the first separation body 10 and the second separation body 20 need to be locked and connected together, the entire first separation body 10 is placed in the second accommodating chamber 21 to facilitate the connection of the second separation body 20.

[0056] It should be noted that in the embodiment of the present application, the original acceleration is a positive acceleration (i.e., greater than 0), and the original acceleration can be a variable value or a fixed value. The current acceleration can be a positive acceleration, or 0, or a negative acceleration (i.e., less than 0, performing a deceleration motion), and the current acceleration can be a variable value or a fixed value, as long as the current acceleration is less than the original acceleration.

[0057] It should be noted that, in the embodiments of the present application, a plurality includes two or more than two.

[0058] Alternatively, if Figure 2As shown, in the embodiment of the present application, a plurality of grooves 22 are sequentially spaced along the circumference of the second accommodating cavity 21; a plurality of first through holes 12 are sequentially spaced along the circumference of the side wall of the first separation body 10, and at least one steel ball is disposed in each first through hole 12 as a locking member 30; the number of the grooves 22 is equal to the number of the locking members 30. In this way, when the first separation body 10 and the second separation body 20 are locked and connected together, the plurality of locking members 30 are matched with the plurality of grooves 22 in a one-to-one correspondence, which can improve the locking effect of the first separation body 10 and the second separation body 20, and improve the connection stability and connection rigidity.

[0059] Of course, in some other optional embodiments of the present application, according to actual needs, the number of grooves 22 can be made greater than the number of locking members 30, that is, one locking member 30 corresponds to multiple grooves 22. When the first separation body 10 and the second separation body 20 need to be locked and connected together, a locking member 30 is selectively matched with one of the multiple grooves 22, which can improve the locking effect of the first separation body 10 and the second separation body 20 and improve the connection stability, connection stiffness, flexibility and adaptability.

[0060] Alternatively, if Figure 2 As shown, in the embodiment of the present application, the locking member 30 includes a steel ball, and the side wall of the first separation body 10 is provided with a first through hole 12 corresponding to the steel ball, and the steel ball is movably arranged in the first through hole 12. The steel ball can flexibly rotate in the first through hole 12. Under the action of the switching structure 40, part of the structure of the steel ball enters the groove 22 to lock the first separation body 10 and the second separation body 20, or the steel ball with a part of the structure located in the groove 22 is released from the groove 22, so that the first separation body 10 and the second separation body 20 are unlocked and can be separated. This setting method has a simple structure and is easy to operate.

[0061] Alternatively, if Figure 2 As shown, in the embodiment of the present application, the switching structure 40 includes a conversion member 41, which is movably arranged in the first accommodating cavity 11 along the arrangement direction of the first separation body 10 and the second separation body 20. The conversion member 41 has a locking matching portion 42 and an unlocking matching portion 43 which are sequentially arranged along the direction from the second separation body 20 to the first separation body 10; the locking matching portion 42 is used to match with the locking member 30 (for example, the locking matching portion 42 pushes the locking member 30 into the groove 22), so that the locking member 30 is located in the locked position; the unlocking matching portion 43 is used to match with the locking member 30 (for example, the unlocking matching portion 43 provides an accommodating space for the locking member 30 to escape from the groove 22), so that the locking member 30 is located in the unlocked position.

[0062] In the embodiment of the present application, the locking mating portion 42 and the unlocking mating portion 43 are sequentially arranged on the conversion member 41 along the direction from the second separation body 20 to the first separation body 10; if the first separation body 10 and the second separation body 20 do not need to be separated, the interstage separation system 100 moves at the original acceleration along the direction from the first separation body 10 to the second separation body 20. At this time, the first separation body 10, the second separation body 20 and the conversion member 41 all move at the original acceleration. Under the action of the original acceleration and gravity, the locking mating portion 42 of the conversion member 41 cooperates with the locking member 30, and the locking member 30 is located in the locked position, and the first separation body 10 and the second separation body 20 are in a locked connection state; if the first separation body 10 and the second separation body 20 do not need to be separated, the interstage separation system 100 moves at the original acceleration along the direction from the first separation body 10 to the second separation body 20. At this time, the first separation body 10, the second separation body 20 and the conversion member 41 all move at the original acceleration. Under the action of the original acceleration and gravity, the locking mating portion 42 of the conversion member 41 cooperates with the locking member 30, and the locking member 30 is located in the locked position. The first separation body 10 and the second separation body 20 are in a locked connection state. When the body 20 needs to be separated, the acceleration of the inter-stage separation system 100 is switched from the original acceleration to the current acceleration. At this time, the first separation body 10 and the second separation body 20 both move at the current acceleration. Since the conversion member 41 is movable in the first accommodating chamber 11, the conversion member 41 has the inertia to maintain the original acceleration. Under the action of the inertial force, the conversion member 41 moves relative to the first separation body 10 in the direction of the second separation body 20 in the first accommodating chamber 11. The position of the conversion member 41 cooperating with the locking member 30 changes, so that the unlocking mating portion 43 cooperates with the locking member 30. The locking member 30 is located in the unlocking position, and the first separation body 10 and the second separation body 20 are in an unlocked and separable state.

[0063] Optionally, in the embodiment of the present application, the conversion member 41 includes a mass block or a counterweight block, and has a certain weight. When the interstage separation system 100 moves at the original acceleration, the conversion member 41 is in an overweight (or overloaded) state under the action of its own gravity and the original acceleration, so that the conversion member 41 cooperates with the locking member 30 based on its own weight and the original acceleration, so that the locking member 30 is located in the locked position, and the first separation body 10 and the second separation body 20 are in a locked connection state.

[0064] Alternatively, if Figure 2 As shown, in the embodiment of the present application, the locking matching portion 42 is a protrusion provided on the outer wall surface of the conversion member 41, and the protrusion is used to press the locking member 30 into the groove 22. When the first separation body 10 and the second separation body 20 need to be locked, the protrusion is abutted against the locking member 30 (specifically, such as a steel ball), and the protrusion presses the locking member 30 into the groove 22 to achieve the locking purpose.

[0065] Alternatively, if Figure 2As shown, in the embodiment of the present application, the unlocking matching portion 43 is a recess provided on the outer wall surface of the conversion member 41, and the recess is used to provide a receiving space for the locking member 30 that is released from the groove 22. When the first separation body 10 and the second separation body 20 need to be unlocked and separated, the recess is made to correspond to the locking member 30 (specifically, a steel ball), providing a receiving space for the locking member 30, so that the locking member 30 is released and released from the groove 22, thereby achieving the purpose of unlocking and facilitating separation.

[0066] It should be noted that, in the embodiment of the present application, the correspondence between the recess and the locking member 30 includes complete alignment or partial alignment between the recess and the locking member 30 , as long as it is ensured that the locking member 30 can be released from the groove 22 .

[0067] Specifically, in the embodiment of the present application, the steel ball can be movably arranged in the first through hole 12. When it is necessary to unlock and separate the first separation body 10 and the second separation body 20, the recess is aligned with the first through hole 12. The recess is located on the side of the first through hole 12 away from the groove 22, providing a holding space for the steel ball. The steel ball can escape from the groove 22 and enter the holding space provided by the recess, thereby achieving the unlocking purpose.

[0068] Optionally, in the embodiment of the present application, the depression transitions to the protrusion smoothly. In this way, the parts where the conversion member 41 cooperates with the locking member 30 (i.e., the depression and the protrusion) can be smoothly and smoothly switched, ensuring that the conversion member 41 switches the position of the locking member 30 smoothly and effectively.

[0069] Alternatively, if Figure 2 As shown, in the embodiment of the present application, the locking matching portion 42 and the unlocking matching portion 43 extend along the circumference of the conversion member 41 respectively to match with multiple locking members 30. In this way, multiple locking members 30 can be located in the locking position or the unlocking position at the same time, thereby improving work efficiency.

[0070] Alternatively, if Figure 2 As shown, in the embodiment of the present application, the locking fitting portion 42 is a protrusion extending along the circumference of the conversion member 41 , and the unlocking fitting portion 43 is a recess extending along the circumference of the conversion member 41 .

[0071] Of course, in some other optional embodiments of the present application, according to actual needs, multiple locking fitting parts 42 and multiple unlocking fitting parts 43 can be arranged in sequence along the circumference of the conversion member 41, and the multiple locking fitting parts 42 and the multiple unlocking fitting parts 43 are respectively arranged in one-to-one correspondence with the multiple locking members 30 to respectively locate the locking members 30 in the locked position or the unlocked position.

[0072] Alternatively, if Figure 2As shown, in the embodiment of the present application, the switching structure 40 further includes at least one adjusting component 44, which is disposed on the first separation body 10 and located in the first accommodating chamber 11. The adjusting component 44 is connected to the conversion member 41, so that the conversion member 41 can move in the first accommodating chamber 11. The adjusting component 44 is used to apply a force to the conversion member 41 to make the unlocking matching portion 43 match with the locking member 30. Under the force applied by the adjusting component 44 to the conversion member 41, the conversion member 41 has a tendency to move in a direction from the locking matching portion 42 matching with the locking member 30 to the unlocking matching portion 43 matching with the locking member 30, so as to facilitate the locking member 30 to be released and disengaged from the groove 22, which helps to achieve the unlocking and separation of the first separation body 10 and the second separation body 20.

[0073] Alternatively, if Figure 2 As shown, in the embodiment of the present application, a mounting member 13 is provided in the first accommodating cavity 11 , and the mounting member 13 is connected to the side wall of the first separation body 10 ; the adjustment component 44 is installed on the mounting member 13 , and the mounting member 13 supports the adjustment component 44 .

[0074] Alternatively, if Figure 2 As shown, in the embodiment of the present application, the adjustment component 44 includes an elastic member 45 and a limit and anti-slip structure 46, the mounting member 13 is provided with a second through hole 14, one end of the limit and anti-slip structure 46 passes through the second through hole 14 and is connected to the conversion member 41, and the elastic member 45 is arranged on the periphery of the limit and anti-slip structure 46 and abuts against the conversion member 41 and the mounting member 13 respectively.

[0075] When the locking fitting portion 42 cooperates with the locking member 30, the elastic member 45 is in a compressed state. At this time, the elastic member 45 compresses and stores energy, and applies an elastic force to the conversion member 41 along the direction of the first separation body 10 pointing to the second separation body 20, so that the conversion member 41 has a tendency to switch from the locking fitting portion 42 cooperating with the locking member 30 to the unlocking fitting portion 43 cooperating with the locking member 30. However, at this time, the conversion member 41 is affected by the overload under the action of its own gravity and original acceleration, and overcomes the elastic force of the elastic member 45. The locking fitting portion 42 of the conversion member 41 cooperates with the locking member 30, pressing the locking member 30 into the groove 22, thereby locking the first separation body 10 and the second separation body 20.

[0076] When the acceleration switches from the original acceleration to the small current acceleration, the conversion member 41 switches to the position where the unlocking mating part 43 cooperates with the locking member 30 while maintaining the inertial force of the original acceleration and the elastic force of the elastic member 45, so that the locking member 30 can be released from the groove 22, thereby unlocking the first separation body 10 and the second separation body 20.

[0077] Driven by the conversion member 41, the limit anti-slip structure 46 is movably arranged in the second through hole 14 along the axis of the second through hole 14, and the second through hole 14 has a guiding effect on the movement of the limit anti-slip structure 46. The limit anti-slip structure 46 is used to limit the extreme position of the conversion member 41. The extreme position of the conversion member 41 includes a first position in which the locking matching part 42 cooperates with the locking member 30 and a second position in which the unlocking matching part 43 cooperates with the locking member 30, or a first nearby position located near the first position and within a reasonable range and a second nearby position located near the second position and within a reasonable range. As long as it is ensured that the conversion member 41 can switch between the first position and the second position, it is possible to avoid the conversion member 41 being too offset and difficult to restore to the first position and the second position.

[0078] Of course, in some other optional embodiments of the present application, the adjustment assembly 44 may also include only the elastic member 45 according to actual needs, and the elastic member 45 is respectively connected to the conversion member 41 and the mounting member 13, and the elastic member 45 is in a compressed state when the locking fitting portion 42 is matched with the locking member 30. At this time, the elastic member 45 not only applies an elastic force to the conversion member 41 along the first separation body 10 pointing to the second separation body 20, so that the conversion member 41 has a tendency to switch from the locking fitting portion 42 matching with the locking member 30 to the unlocking fitting portion 43 matching with the locking member 30, but also limits the extreme position of the conversion member 41.

[0079] Alternatively, if Figure 2 As shown, in the embodiment of the present application, the position-limiting anti-slip structure 46 includes a connecting member 47 and an anti-slip member 48 connected to each other. The connecting member 47 passes through the second through hole 14 and is detachably connected to the conversion member 41. The anti-slip member 48 is located on the side of the mounting member 13 away from the conversion member 41. The radial dimension of the anti-slip member 48 along the connecting member 47 is greater than the radial dimension of the second through hole 14 along the connecting member 47. In this way, the anti-slip member 48 cannot pass through the second through hole 14. When the conversion member 41 moves in the direction from the first separation body 10 to the second separation body 20, driving the connecting member 47 and the anti-slip member 48 to move along the axial direction of the second through hole 14, the anti-slip member 48 can abut against the wall surface of the mounting member 13 away from the conversion member 41, thereby limiting the limit position of the conversion member 41 moving in the direction from the first separation body 10 to the second separation body 20, and preventing the connecting member 47 from falling out of the second through hole 14.

[0080] Optionally, in the embodiment of the present application, the conversion member 41 is provided with a threaded hole, and one end of the connecting member 47 passes through the second through hole 14 and is threadedly connected to the threaded hole, thereby being detachably connected to the conversion member 41 .

[0081] Optionally, in the embodiment of the present application, the connecting member 47 and the anti-dropping member 48 are an integrated structure. The position-limiting anti-dropping structure 46 includes but is not limited to bolts.

[0082] Of course, in other optional embodiments of the present application, the connector 47 and the anti-slip member 48 can be made into separate structures according to actual needs. Optionally, the anti-slip member 48 includes but is not limited to a nut. The nut is threadedly connected to the connector 47. In addition to playing a limiting role, the range of movement of the conversion member 41 can be adjusted by adjusting the position of the connection between the nut and the connector 47, thereby improving flexibility and adaptability and having strong versatility.

[0083] Alternatively, if Figure 2 As shown, in the embodiment of the present application, the elastic member 45 includes a spring. When the elastic member 45 cooperates with the position limiting and anti-slipping structure 46 , the spring is sleeved on the outer periphery of the connecting member 47 .

[0084] Alternatively, if Figure 2 As shown, in the embodiment of the present application, there are multiple adjustment components 44, which are sequentially arranged at intervals along the circumference of the first accommodating cavity 11 and are respectively connected to the conversion member 41. The multiple adjustment components 44 work together to make the conversion member 41 movable in the first accommodating cavity 11, and to make the conversion member 41 have a tendency to move in the direction from the locking matching portion 42 matching with the locking member 30 to the unlocking matching portion 43 matching with the locking member 30, so that the force on the conversion member 41 is relatively balanced, thereby improving the effectiveness of the adjustment.

[0085] Alternatively, if Figure 2 As shown, in the embodiment of the present application, a plurality of adjustment components 44 are evenly spaced in sequence along the circumference of the conversion member 41, so that various parts of the conversion member 41 are subjected to balanced forces, a consistent switching effect is obtained, and work efficiency is improved.

[0086] Alternatively, if Figure 2 As shown, in the embodiment of the present application, the side wall of the first separation body 10 includes a first wall segment 15, a second wall segment 16 and a third wall segment 17 connected in sequence. The mounting member 13 is connected to the first wall segment 15 and is located in the inner cavity of the first wall segment 15. The inner cavities of the first wall segment 15, the second wall segment 16 and the third wall segment 17 are connected in sequence to form a first accommodating cavity 11. The third wall segment 17 is provided with a first through hole 12, which is connected to the inner cavity of the third wall segment 17 and the outside of the third wall segment 17 (such as the groove 22 located outside the third wall segment 17) respectively. The recess and the third wall segment 17 enclose an accommodating space for accommodating the locking member 30 that escapes from the groove 22.

[0087] The interstage separation system 100 provided in the embodiment of the present application adopts a non-pyrotechnic separation method for separation, which can not only meet the maneuverability or control requirements, but also avoid the problems caused by the use of pyrotechnics. It can be applied to technical fields such as aerospace, and further can be applied to the separation process of aircraft such as missiles.

[0088] The following uses the interstage separation system provided in the embodiment of the present application as an example to apply to a missile to explain the separation principle and working process:

[0089] When the vehicle stages separate, usually the first stage (the lower stage) engine propellant has been exhausted, while the second stage (the upper stage) engine has not yet started working.

[0090] At this time, the aircraft has reached a certain speed, usually supersonic. When the first-stage engine is shut down, the acceleration will usually change rapidly from a positive acceleration of 10g (as the original acceleration) to 1g or even a negative acceleration (as the current acceleration) in a short period of time, such as 0.5 seconds.

[0091] The present application utilizes the characteristic of such acceleration change as a triggering mechanism for the passive separation of the inter-stage separation system 100 .

[0092] When the acceleration is maintained at a relatively high level (such as 10g) (i.e., when accelerating at the original acceleration), the conversion member 41 is affected by the overload, overcomes the spring force of the elastic member 45, and moves downward (i.e., along the direction of the second separation body 20 pointing to the first separation body 10), presses the locking member 30 into the groove 22, and realizes the locking of the first separation body 10 and the second separation body 20, thereby connecting the upper stage and the lower stage together.

[0093] When the acceleration changes from a higher level (such as 10g) to 1g or negative (i.e., when switching from the original acceleration to the current acceleration), the conversion member 41 has the inertia to maintain the original higher level acceleration (i.e., the original acceleration). Under the combined action of the inertial force and the spring force of the elastic member 45, the conversion member 41 moves upward (i.e., along the direction of the first separation body 10 pointing to the second separation body 20), and the locking member 30 is released and disengaged from the groove 22, thereby unlocking the first separation body 10 and the second separation body 20. There is no longer a locking force between the first separation body 10 and the second separation body 20, and the first separation body 10 moves away from the second separation body 20 under the action of the separation force, thereby completing the separation.

[0094] Based on the same inventive concept, the present application embodiment provides an aircraft inter-stage separation method. The flow chart of the aircraft inter-stage separation method is as follows: Figure 1 As shown, the aircraft inter-stage separation method includes a combustion stage S101 and a separation stage S102 performed sequentially.

[0095] In the combustion stage S101: the aircraft is moved at the original acceleration. Under the original acceleration, the conversion member 41 movably arranged in the lower stage of the aircraft is overweight and presses the locking member 30, so that the locking member 30 clamps the upper stage and the lower stage of the aircraft to lock.

[0096] In the embodiment of the present application, during the combustion stage, the aircraft has an original acceleration, and the upper stage, lower stage and conversion member 41 of the aircraft all move under the original acceleration. Since the conversion member 41 is movably arranged in the lower stage, under the original acceleration, the conversion member 41 is overweight (or overloaded) and compresses the locking member 30, so that the locking member 30 is located in the locked position, thereby locking the lower stage and the upper stage together.

[0097] Optionally, in the embodiment of the present application, during the combustion stage:

[0098] Obtain an acceleration instruction. Optionally, the control system sends an acceleration instruction.

[0099] Next, the engine of the lower stage is controlled to ignite according to the acceleration instruction, and the propellant of the lower stage engine burns, causing the aircraft to move at the original acceleration, so that the locking member 30 clamps the upper stage and the lower stage of the aircraft, thereby achieving the purpose of locking the upper stage and the lower stage.

[0100] Optionally, in an embodiment of the present application, when the propellant of the lower stage engine is exhausted and the upper stage engine has not yet started working, the aircraft enters the separation phase.

[0101] Of course, in some other optional implementations of the present application, when the aircraft reaches a set speed, a separation instruction can be sent through the control system to make the aircraft enter the separation stage.

[0102] In the separation phase S102: the acceleration of the aircraft is reduced so that the upper stage and the lower stage move at a current acceleration less than the original acceleration. The conversion member 41 moves toward the direction of the upper stage relative to the lower stage based on the inertia of maintaining the original acceleration, so that the locking member 30 that jams the upper stage and the lower stage is released to unlock.

[0103] In the embodiment of the present application, when the aircraft enters the separation stage from the combustion stage, the acceleration of the aircraft is switched from the original acceleration to the current acceleration which is less than the original acceleration. The upper stage and the lower stage of the aircraft move at the current acceleration. The conversion member 41 movably arranged in the lower stage cooperates with the locking member 30 based on the inertia of maintaining the original acceleration, so that the locking member 30 is located in the unlocking position, thereby unlocking the lower stage and the upper stage.

[0104] Optionally, in an embodiment of the present application, under the action of aerodynamic drag, the acceleration of the aircraft is reduced from the original acceleration to the current acceleration.

[0105] Of course, in some other optional embodiments of the present application, the engine of the lower stage can be controlled to shut down or the propellant combustion amount of the engine of the lower stage can be reduced according to the separation instruction to reduce the acceleration of the aircraft.

[0106] Optionally, in an embodiment of the present application, in the separation stage, after releasing the connection between the upper stage and the lower stage, the method further includes: applying a separation force to at least one of the upper stage and the lower stage to separate the upper stage from the lower stage.

[0107] In the embodiment of the present application, after the lower stage and the upper stage are unlocked, the lower stage and the upper stage are in an unlocked and separable state, and under the action of the separation force, the purpose of separating the lower stage and the upper stage can be achieved.

[0108] Optionally, in the embodiment of the present application, Figure 2 As shown, the conversion member 41 is elastically connected to the lower stage through the elastic member 45. In the combustion stage, the conversion member 41 is overweight, which compresses the elastic member 45 and stores energy. In the separation stage, the conversion member 41 moves toward the direction of the upper stage relative to the lower stage under the action of the inertial force of the original acceleration and the elastic force provided by the elastic member 45, and releases the pressure on the locking member 30, so that the upper stage and the lower stage are unlocked.

[0109] Optionally, in the embodiment of the present application, Figure 2 As shown, in the combustion stage, the conversion member 41 is overweight so that the protrusion abuts against the locking member 30, pressing the locking member 30 into the groove 22 to clamp the upper stage and the lower stage. In the separation stage, the conversion member 41 moves relative to the lower stage toward the direction of the upper stage, so that the depression is located on the side of the first through hole 12 away from the groove 22, so as to provide a receiving space for the locking member 30 to be released from the groove 22, so that the upper stage and the lower stage are unlocked.

[0110] The aircraft interstage separation method provided in the embodiment of the present application can be used to separate the interstage separation system in the embodiment of the present application. The aircraft interstage separation method in the embodiment of the present application also has the above-mentioned beneficial effects of the interstage separation system in the embodiment of the present application, which will not be repeated here.

[0111] The following uses the aircraft interstage separation method provided in the embodiment of the present application to separate the missile interstage separation system as an example to illustrate the separation method:

[0112] First, assemble the lower stage, the interstage separation system 100 and the upper stage together. It should be noted that the first separation body 10 of the interstage separation system 100 is connected to the lower stage; the second separation body 20 of the interstage separation system 100 is connected to the upper stage. Optionally, the first separation body 10 and the lower stage are an integrated structure. The second separation body 20 and the upper stage are an integrated structure. Of course, in other optional embodiments of the present application, the first separation body 10 can also be arranged and connected with the lower stage body according to actual needs. The second separation body 20 is arranged and connected with the upper stage body.

[0113] Next, the engine of the lower stage (not shown) is started, and the interstage separation system of the aircraft enters the combustion stage, so that the lower stage, the interstage separation system 100 and the upper stage move together at the original acceleration (for example, 10g). The original acceleration may vary with factors such as the engine propellant consumption and time.

[0114] At this time, under the action of its own gravity and original acceleration, the conversion member 41 is affected by overload and overcomes the spring force of the elastic member 45 to move downward (that is, the upper stage points to the direction of the lower stage), pressing the locking member 30 into the groove 22. The locking member 30 is in the locked position, realizing the locking of the first separation body 10 and the second separation body 20, and the upper stage and the lower stage are locked and connected together.

[0115] Then, the lower stage engine ran out of propellant and shut down, the upper stage engine had not yet started working, and the vehicle's interstage separation system entered the separation phase.

[0116] Under the effect of aerodynamic drag, the acceleration of the lower stage, the interstage separation system 100 and the upper stage is rapidly reduced to the current acceleration (such as 1g or even negative) in a short time. The current acceleration may change with the change of environmental factors (such as air pressure, temperature, etc.) and time.

[0117] At this time, the conversion member 41 entering the separation stage has the inertia to maintain the original acceleration. Under the combined action of the inertial force and the spring force of the elastic member 45, the conversion member 41 moves upward (that is, the lower stage points to the upper stage direction), no longer pressing the locking member 30 and providing an accommodating space for the locking member 30 to escape from the groove 22, so that the locking member 30 can be released from the groove 22 to be located in the unlocking position, thereby realizing the unlocking of the first separation body 10 and the second separation body 20. There is no longer a locking force between the lower stage and the upper stage, and the lower stage moves away from the upper stage under the action of the separation force, completing the separation of the lower stage from the upper stage.

[0118] Based on the same inventive concept, an embodiment of the present application provides an aircraft, which includes: the above-mentioned interstage separation system 100, a lower stage and an upper stage, wherein the lower stage is connected to the first separation body 10; and the upper stage is connected to the second separation body 20. The first separation body 10 and the second separation body 20 are separated by the above-mentioned aircraft interstage separation method, so that the lower stage and the upper stage are separated by the above-mentioned aircraft interstage separation method.

[0119] If the lower stage and the upper stage do not need to be separated, the aircraft is moved at the original acceleration, and the interstage separation system 100, the lower stage and the upper stage all move at the original acceleration. The conversion member 41 of the interstage separation system 100 cooperates with the locking member 30 based on the original acceleration, so that the locking member 30 is located in the locking position, and the lower stage and the upper stage are locked and connected together, so that the lower stage and the upper stage are in a locked connection state.

[0120] If the lower stage and the upper stage need to be separated, the acceleration of the aircraft is switched from the original acceleration to the current acceleration, and the interstage separation system 100, the lower stage and the upper stage all move at the current acceleration. The conversion member 41 changes its position based on the inertia of maintaining the original acceleration and cooperating with the locking member 30, so that the locking member 30 is located in the unlocked position, unlocking the lower stage and the upper stage, and placing the lower stage and the upper stage in an unlocked and separable state, thereby achieving separation of the lower stage and the upper stage.

[0121] It should be noted that, since the aircraft in the embodiment of the present application includes the inter-stage separation system in the embodiment of the present application, the aircraft in the embodiment of the present application also has the above-mentioned beneficial effects of the inter-stage separation system in the embodiment of the present application, which will not be repeated here.

[0122] It should be noted that since the upper stage and the lower stage of the aircraft in the embodiment of the present application can be separated by the aircraft inter-stage separation method provided in the embodiment of the present application, the aircraft in the embodiment of the present application also has the above-mentioned beneficial effects of the aircraft inter-stage separation method provided in the embodiment of the present application, which will not be repeated here.

[0123] Optionally, the aircraft of the embodiments of the present application includes but is not limited to aircraft, spacecraft, rockets, etc.

[0124] By applying the embodiments of the present application, at least the following beneficial effects can be achieved:

[0125] In the embodiment of the present application, during the combustion stage, the aircraft has an original acceleration, and the upper stage, lower stage and conversion member of the aircraft all move under the original acceleration. Since the conversion member is movably arranged in the lower stage, under the original acceleration, the conversion member is overweight (or overloaded) and presses the locking member, so that the locking member is located in the locking position, and the lower stage and the upper stage are locked and connected together. When the aircraft enters the separation stage, the acceleration of the aircraft is switched from the original acceleration to the current acceleration less than the original acceleration, and the upper stage and the lower stage of the aircraft move at the current acceleration. The conversion member movably arranged in the lower stage cooperates with the locking member based on the inertia of maintaining the original acceleration, so that the locking member is located in the unlocking position, and the lower stage and the upper stage are unlocked.

[0126] In the embodiment of the present application, the aircraft relies on the inertial force caused by the overload during movement or the maneuvering during movement to adjust the position of the conversion member and the locking member, realize the conversion of the position (locked position and unlocked position) of the locking member, and thus control the state of the lower stage and the upper stage (locked connection state or unlocked detachable state). Without using pyrotechnics, explosives, external instructions, or any electrical interface, the aircraft can be designed to use the characteristics of acceleration change (from the original acceleration to the current acceleration less than the original acceleration) as a trigger mechanism for the passive separation of the lower stage and the upper stage, and automatic triggering separation can be achieved when certain conditions are met.

[0127] The aircraft inter-stage separation method of the embodiment of the present application can improve the connection stiffness between the lower stage and the upper stage without pyrotechnics, and is completely independent of any external control. It can meet maneuvering or control requirements and avoid the problems caused by the use of pyrotechnics.

[0128] Those skilled in the art will appreciate that the various operations, methods, steps, measures, and schemes in the processes discussed in this application may be alternated, changed, combined, or deleted. Furthermore, other steps, measures, and schemes in the various operations, methods, and processes discussed in this application may also be alternated, changed, rearranged, decomposed, combined, or deleted. Furthermore, steps, measures, and schemes in the related art that are similar to those disclosed in this application may also be alternated, changed, rearranged, decomposed, combined, or deleted.

[0129] In the description of the present application, the directions or positional relationships indicated by words such as "center", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" are based on the exemplary directions or positional relationships shown in the accompanying drawings. They are for the convenience of describing or simplifying the description of the embodiments of the present application, and do not indicate or imply that the referred device or component must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be understood as limitations on the present application.

[0130] The terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of this application, unless otherwise specified, "plurality" means two or more.

[0131] In the description of this application, it should be noted that, 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 direct connection, or an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0132] In the description of this specification, specific features, structures, materials or characteristics may be combined in an appropriate manner in any one or more embodiments or examples.

[0133] The above is only a partial implementation method of the present application. It should be pointed out that for ordinary technicians in this technical field, without departing from the technical concept of the scheme of the present application, other similar implementation methods based on the technical ideas of the present application are also within the protection scope of the embodiments of the present application.

Claims

1. A method for separating aircraft stages, characterized in that: It includes a combustion stage and a separation stage which are carried out in sequence; During the combustion phase: The aircraft is moved at an original acceleration, under which a conversion member movably disposed in a lower stage of the aircraft is overweight and presses a locking member, so that the locking member clamps the upper stage and the lower stage of the aircraft to lock; During the separation phase: The acceleration of the aircraft is reduced so that the upper stage and the lower stage move at a current acceleration less than the original acceleration. Based on the inertia of maintaining the original acceleration, the conversion member moves relative to the lower stage toward the direction of the upper stage, so that the locking members that jam the upper stage and the lower stage are released to release the lock.

2. The aircraft stage separation method according to claim 1, characterized in that: The conversion member is elastically connected to the lower stage via an elastic member; During the combustion stage, the overweight of the conversion member causes the elastic member to be compressed, and the elastic member stores energy; In the separation stage, the conversion member moves toward the direction of the upper stage relative to the lower stage under the action of the inertial force maintaining the original acceleration and the elastic force provided by the elastic member, releasing the pressure on the locking member to unlock the upper stage and the lower stage.

3. The aircraft stage separation method according to claim 1, characterized in that: During the combustion phase: Get acceleration instructions; The engine of the lower stage is controlled to ignite according to the acceleration instruction, and the propellant of the engine of the lower stage is burned to make the aircraft move at the original acceleration.

4. The aircraft stage separation method according to claim 1, characterized in that: The reducing the acceleration of the aircraft comprises: When the propellant of the lower stage engine is exhausted and the engine of the upper stage has not yet started to work, the aircraft enters the separation stage; Wherein, in the separation phase, under the effect of aerodynamic drag, the acceleration of the aircraft decreases from the original acceleration to the current acceleration.

5. The aircraft stage separation method according to claim 1, characterized in that: The reducing the acceleration of the aircraft comprises: When the aircraft reaches a set speed, the control system sends a separation command, and the aircraft enters the separation phase; According to the separation instruction, the engine of the lower stage is controlled to shut down or the propellant combustion amount of the engine of the lower stage is reduced to reduce the acceleration of the aircraft.

6. The aircraft inter-stage separation method according to any one of claims 1 to 5, characterized in that: The upper stage is provided with a groove, the side wall of the lower stage is provided with a first through hole, and the locking member is movably arranged in the first through hole; The conversion member has a depression and a protrusion which are sequentially arranged on the outer wall surface along the direction from the lower stage to the upper stage; the depression smoothly transitions to the protrusion; During the combustion stage, the overweight of the conversion member causes the protrusion to abut against the locking member, pressing the locking member into the groove to clamp the upper stage and the lower stage; During the separation stage, the conversion member moves relative to the lower stage toward the direction of the upper stage, so that the depression is located on the side of the first through hole away from the groove, thereby providing a receiving space for the locking member to be released from the groove, thereby unlocking the upper stage and the lower stage.

7. The aircraft stage separation method according to any one of claims 1 to 5, characterized in that: In the separation stage, after the connection between the upper stage and the lower stage is released, the method further comprises: A separation force is applied to at least one of the upper stage and the lower stage to separate the upper stage and the lower stage.

8. The aircraft stage separation method according to claim 2, characterized in that: The lower stage is provided with a mounting member, a connecting member and an anti-slip member. The mounting member is connected to the side wall of the lower stage and is provided with a second through hole. One end of the connecting member passes through the second through hole and is connected to the conversion member. The elastic member is arranged on the outer periphery of the connecting member and abuts against the conversion member and the mounting member respectively. The conversion member drives the connecting member to move axially along the second through hole. The anti-slip member is arranged at the other end of the connecting member to prevent the connecting member from falling out of the second through hole.

9. The aircraft stage separation method according to claim 6, characterized in that: Along the circumference of the upper stage, a plurality of the grooves are sequentially spaced apart in the upper stage; along the circumference of the lower stage, a plurality of the first through holes are sequentially spaced apart in the side wall of the lower stage, and at least one steel ball is disposed in each of the first through holes to serve as the locking piece; the number of the grooves is greater than or equal to the number of the first through holes.

10. An aircraft, characterized in that: The invention comprises an upper stage and a lower stage, wherein the upper stage and the lower stage are separated by using the aircraft inter-stage separation method according to any one of claims 1 to 9.

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