A side pushable interstage separation device and method of use

Abstract

The application relates to a side-pushing air cylinder and inter-stage separation device and a use method, and belongs to the technical field of aircraft cabin section inter-stage separation. The side-pushing air cylinder and inter-stage separation device and the use method comprise an inter-stage cabin, the periphery of the inter-stage cabin is provided with an air cylinder and an air cylinder provided with an air source, and an aircraft main stage is arranged at the front end of the inter-stage cabin and can be separated from the inter-stage cabin through the air cylinder. The first air cylinder and the second air cylinder can separate the inter-stage cabin in the axial direction and push the inter-stage cabin at the same time, so that the inter-stage cabin can move laterally, the axial and lateral separation of the inter-stage cabin and the aircraft main stage can be realized, the inter-stage cabin is prevented from being in the same range as the aircraft main stage after separation, cabin sections are prevented from being easily interfered with each other and causing safety reduction, and the aircraft main stage is prevented from being easily damaged.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft cabin section separation, in particular to a lateral thrustable section separation device and a use method thereof. BACKGROUND

[0002] The unlocking separation technology of an aircraft is a key technology in the field of spaceflight, and the separation unlocking process is directly related to the success or failure of the flight mission of the aircraft.

[0003] At present, the section separation modes of the aircraft mainly include point separation and linear separation. The point separation device includes an explosive bolt, an unlocking bolt, a separation nut and the like, and the linear separation mainly includes a cutting rope, an expansion tube and a shaped charge rope.

[0004] However, the separation impulse provided by both is small, which easily causes the section cabin after separation to be in the same range as the main stage of the aircraft, so that the cabin sections are easily interfered with each other. SUMMARY

[0005] Embodiments of the present application provide a lateral thrustable section separation device and a use method thereof, so as to solve the problem of low separation safety in the conventional separation mode in the related art.

[0006] A first aspect of embodiments of the present application provides a lateral thrustable air cylinder, the air cylinder comprising:

[0007] A first air cylinder, the first air cylinder comprising a first cylinder barrel, a first piston arranged in the first cylinder barrel, a first piston rod connected with the first piston, and a first nozzle arranged outside the first cylinder barrel and capable of laterally spraying gas.

[0008] A gas cylinder, the gas cylinder providing a gas source for the air cylinder.

[0009] In some embodiments, the first nozzle is arranged outside the end of the first cylinder barrel away from the first piston.

[0010] In some embodiments, a gas path is arranged between the air cylinder and the gas cylinder to connect and communicate them.

[0011] A second aspect of embodiments of the present application provides a lateral thrustable section separation device, comprising:

[0012] A section cabin, the section cabin being provided with an air cylinder and a gas cylinder arranged to provide a gas source on the side thereof;

[0013] A main stage of an aircraft, the main stage of the aircraft being arranged at the front end of the section cabin and being capable of being separated from the section cabin by the air cylinder.

[0014] In some embodiments, the air cylinder further comprises:

[0015] The second cylinder which can be axially pushed to separate includes a second cylinder barrel, a second piston arranged in the second cylinder barrel and a second piston rod connected with the second piston.

[0016] In some embodiments, the first cylinder and the second cylinder are both several and even.

[0017] In some embodiments, the several first cylinders are arranged on the side of the inter-stage cabin opposite to the side pushing direction, and the first cylinder nozzles push the inter-stage cabin.

[0018] In some embodiments, the several second cylinders are arranged on the circumferential side of the inter-stage cabin.

[0019] In some embodiments, the inter-stage cabin and the main stage of the aircraft are connected through the explosive bolts.

[0020] The third aspect of the embodiments of the present application provides a use method of the side-pushing inter-stage separation device, which comprises the following steps:

[0021] When the main stage of the aircraft and the boost stage are ready to separate, the control system sends a separation signal to the gas cylinder and the explosive bolt at the same time;

[0022] Then, after the gas cylinder and the explosive bolt receive the separation signal, the explosive bolt is detonated, the main stage of the aircraft and the inter-stage section are disconnected, the gas in the gas cylinder pushes the piston in the cylinder to move through the gas path, the piston pushes the piston rod forward, the piston rod pushes the main stage of the aircraft, and the main stage of the aircraft is pushed forward.

[0023] When the piston rod moves to the designed stroke, i.e., the main stage of the aircraft and the inter-stage cabin reach the axial separation distance, the gas in the cylinder is sprayed from the nozzle, the inter-stage cabin is side-pushed in the direction opposite to the flight posture of the main stage of the aircraft, and the axial and lateral separation of the inter-stage cabin and the main stage of the aircraft is realized.

[0024] The embodiments of the present application provide a side-pushing inter-stage separation device and a use method. The input gas of the gas cylinder to the first cylinder barrel of the first cylinder makes the internal gas pressure, then the first piston drives the first piston rod to push forward, the first piston rod pushes the main stage of the aircraft, and the main stage of the aircraft is boosted forward, so that the main stage of the aircraft and the inter-stage cabin are axially separated. When the main stage of the aircraft and the inter-stage cabin reach the axial separation distance, the gas in the first cylinder is sprayed from the first nozzle, and the inter-stage cabin is side-pushed in the direction opposite to the flight posture of the main stage of the aircraft.

[0025] The input gas of the gas cylinder to the second cylinder barrel of the second cylinder makes the internal gas pressure, then the second piston drives the second piston rod to push forward, the first piston rod pushes the main stage of the aircraft, and the main stage of the aircraft is boosted forward, so that the main stage of the aircraft and the inter-stage cabin are axially separated.

[0026] The axial and lateral separation of the inter-stage cabin and the main stage of the aircraft can be realized, and the safety is improved.

[0027] The aircraft main stage is separated by the gas cylinder and the explosion bolt, the impact on the aircraft main stage is small, the flight attitude of the aircraft main stage is not disturbed, the flight of the aircraft main stage separated by the gas cylinder and the explosion bolt is more stable. BRIEF DESCRIPTION OF DRAWINGS

[0028] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed in the embodiment description will be briefly introduced. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor.

[0029] Figure 1 The structural schematic diagram provided for the embodiments of the present application is provided.

[0030] Figure 2 The structural schematic diagram provided for the first gas cylinder in the present application is provided.

[0031] Figure 3 The structural schematic diagram provided for the second gas cylinder in the present application is provided.

[0032] Figure 4 The axial separation state schematic diagram provided for the embodiments of the present application is provided.

[0033] Figure 5 The lateral thrust separation state schematic diagram provided for the embodiments of the present application is provided.

[0034] 1, aircraft main stage; 2, explosion bolt; 3, gas cylinder; 31, first gas cylinder; 32, second gas cylinder; 311, first cylinder barrel; 312, first piston rod; 313, first piston; 314, first nozzle; 321, second cylinder barrel; 322, second piston rod; 323, second piston; 4, inter-stage cabin; 5, gas cylinder; 6, gas path. DETAILED DESCRIPTION

[0035] In order to make the purpose, technical solutions and advantages of the embodiments of the present application more clear, the technical solutions in the embodiments of the present application will be described clearly and completely in the following with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor are within the scope of protection of the present application.

[0036] The embodiment of the present application provides a side-pushing interstage separation device and a use method, which can solve the problem of low separation safety in the traditional separation mode.

[0037] Referring to Figures 1-3 As shown in the figure, the first aspect of the embodiment of the present application provides a side-pushing cylinder, which comprises:

[0038] The cylinder 3, the first cylinder 31 and the gas cylinder 5

[0039] When the interstage cabin 4 is separated from the main stage 1 of the aircraft, the gas cylinder 5 provides a gas source for the first cylinder 31 and the second cylinder 32, the first cylinder 31, the first piston 313 arranged in the first cylinder barrel 311, the first piston rod 312 connected with the first piston 313 and the first nozzle 314 arranged outside the first cylinder barrel 311 and capable of side spraying gas.

[0040] When the first cylinder 31 needs to be used, the gas cylinder 5 supplies gas to the first cylinder 31, then the first cylinder barrel 311 is filled with gas, then the first piston 313 pushes the first piston rod 312 to be fixed, and the gas also leaks from the gap between the first cylinder 31, the first piston rod 312 and the first piston 313 to the position of the first nozzle 314, so that the lateral thrust is generated.

[0041] Then the first cylinder 32 pushes the interstage cabin 4 towards the axial direction of the main stage 1 of the aircraft, and simultaneously pushes it towards the side, so that the interstage cabin 4 is separated from the main stage 1 of the aircraft, avoiding mutual collision interference.

[0042] Wherein, the cylinder 3 and the gas cylinder 5 are arranged on the interstage cabin 4 respectively, so that after the interstage cabin 4 is separated from the main stage 1 of the aircraft, the interstage cabin 4 can be further separated by the gas cylinder 5 and the cylinder 3, avoiding collision interference.

[0043] In the embodiment, the first nozzle 314 is arranged outside the end of the first cylinder barrel 311 away from the first piston 313.

[0044] In the embodiment, the gas path 6 is connected and communicated between the cylinder 3 and the gas cylinder 5.

[0045] Through the gas path 6, the gas in the gas cylinder 5 is transported to the first cylinder 31 and the second cylinder 32, so that they move and work.

[0046] Referring to Figures 1-5 As shown in the figure, the second aspect of the embodiment of the present application provides a side-pushing interstage separation device, which comprises:

[0047] The interstage cabin 4 and the main stage 1 of the aircraft.

[0048] Wherein, the interstage cabin 4 is provided with the cylinder 3 and the gas cylinder 5 arranged to provide a gas source.

[0049] The aircraft main stage 1 is arranged at the front end of the interstage cabin 4 and can be separated from the interstage cabin 4 by the air cylinder 3.

[0050] The first cylinder barrel 311 of the first air cylinder 31 is inputted with gas by the gas cylinder 5, so that the gas pressure is generated in the first cylinder barrel 311, and then the first piston 313 drives the first piston rod 312 to push forward, the first piston rod 312 pushes the aircraft main stage 1 forward, so that the aircraft main stage 1 is separated from the interstage cabin 4 in the axial direction, and when the aircraft main stage 1 and the interstage cabin 4 reach the set distance in the axial direction, the gas in the first air cylinder 31 is sprayed from the first nozzle 314, and the interstage cabin 4 is side-thrust in the direction opposite to the aircraft attitude of the aircraft main stage 1.

[0051] The separation of the interstage cabin 4 and the aircraft main stage 1 in the axial direction and the lateral direction can be realized.

[0052] In the embodiment, the air cylinder 3 further comprises:

[0053] The second air cylinder 32 comprises a second cylinder barrel 321, a second piston 323 arranged in the second cylinder barrel 321, and a second piston rod 322 movably arranged in the second cylinder barrel 321 and connected with the second piston 323.

[0054] The second cylinder barrel 321 of the second air cylinder 32 is inputted with gas by the gas cylinder 5, so that the gas pressure is generated in the second cylinder barrel 321, and then the second piston 323 drives the second piston rod 322 to push forward, the first piston rod 312 pushes the aircraft main stage 1 forward, so that the aircraft main stage 1 is separated from the interstage cabin 4 in the axial direction.

[0055] In the embodiment, the first air cylinder 31 and the second air cylinder 32 are several and even.

[0056] The first air cylinder 31 and the second air cylinder 32 are even, and the even first air cylinder 31 and the second air cylinder 32 make the thrust of the aircraft main stage 1 and the side-thrust of the interstage cabin 4 be uniformly stressed, so that the odd number causes the stress to be not uniform, and the orientation is deviated.

[0057] In the embodiment, the several first air cylinders 31 are arranged at the side opposite to the side-thrust direction of the interstage cabin 4, and the first nozzle 314 of the first air cylinder 31 side-thrusts the interstage cabin 4.

[0058] The several second air cylinders 32 are arranged at the circumferential side of the interstage cabin 4.

[0059] The first air cylinder 31 is arranged at the position opposite to the side-thrust direction of the interstage cabin 4 according to the actual situation, and the second air cylinder 32 is uniformly arranged at the circumferential side of the interstage cabin 4.

[0060] In the embodiment, the interstage cabin 4 and the aircraft main stage 1 are connected by the explosive bolt 2.

[0061] When the aircraft main stage 1 and the interstage cabin 4 need to be separated, the explosive bolt 2 receives a signal to detonate, the connection between the aircraft main stage 1 and the interstage cabin 4 is disconnected, and the aircraft main stage 1 is separated from the interstage cabin 4.

[0062] Referring to Figures 1-5 The third aspect of the embodiments of the present application provides a method for using the lateral thrust interstage separation device, which comprises the following steps:

[0063] Step 1: When the aircraft main stage 1 and the booster stage are ready to be separated, the control system sends a separation signal to the gas cylinder 5 and the explosive bolt 2 at the same time.

[0064] Step 2: Then, after the gas cylinder 5 and the explosive bolt 2 receive the separation signal, the explosive bolt 2 detonates, and the aircraft main stage 1 and the interstage section are disconnected.

[0065] Step 3: The gas cylinder 5 inputs gas to the first cylinder barrel 311 of the first cylinder 31, so that the internal gas pressure is generated, then the first piston 313 drives the first piston rod 312 to push forward, the first piston rod 312 pushes the aircraft main stage 1 forward, so that the aircraft main stage 1 and the interstage cabin 4 are axially separated, and at the same time, when the aircraft main stage 1 and the interstage cabin 4 reach the set distance of axial separation, the gas in the first cylinder 31 is sprayed from the first nozzle 314, and the interstage cabin 4 is pushed to the direction opposite to the flight attitude of the aircraft main stage 1.

[0066] Step 4: At the same time, the gas cylinder 5 inputs gas to the second cylinder barrel 321 of the second cylinder 32, so that the internal gas pressure is generated, then the second piston 323 drives the second piston rod 322 to push forward, the second piston rod 322 pushes the aircraft main stage 1 forward, so that the aircraft main stage 1 and the interstage cabin 4 are axially separated.

[0067] Step 5: The first cylinder 31 and the second cylinder 32 are synchronously operated, so that the axial and lateral separation of the interstage cabin 4 and the aircraft main stage 1 is realized.

[0068] The working principle and process of the present application are as follows:

[0069] When the aircraft main stage 1 and the booster stage are ready to be separated, the control system sends a separation signal to the gas cylinder 5 and the explosive bolt 2 at the same time;

[0070] Then, after the gas cylinder 5 and the explosive bolt 2 receive the separation signal, the explosive bolt 2 detonates, and the aircraft main stage 1 and the interstage section are disconnected,

[0071] The input gas of the first cylinder 31 through the gas cylinder 5 to the first cylinder barrel 311, so that the internal gas pressure, and then the first piston 313 driven by the first piston rod 312 forward, the first piston rod 312 against the aircraft main stage 1 to help it forward, that is, the aircraft main stage 1 and stage cabin 4 axial separation, while the aircraft main stage 1 and stage cabin 4 to reach the axial separation set distance, the gas in the first cylinder 31 from the first nozzle 314, the stage cabin 4 to the opposite direction of the aircraft main stage 1 aircraft attitude side.

[0072] The input gas of the second cylinder 32 through the gas cylinder 5 to the second cylinder barrel 321, so that the internal gas pressure, and then the second piston 323 driven by the second piston rod 322 forward, the second piston rod 322 against the aircraft main stage 1 to help it forward, that is, the aircraft main stage 1 and stage cabin 4 axial separation.

[0073] That is, the stage cabin 4 and the aircraft main stage 1 of the axial and lateral separation, to avoid the separation of stage cabin 4 and the aircraft main stage in the same range, so that the cabin segment is easy to interfere with each other.

[0074] In the description of the present application, it should be noted that the terms "upper", "lower" and the like indicate the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, therefore it cannot be understood as a limitation on the present application. Unless otherwise specified and limited, the terms "mounting", "connection", "connection" should be understood broadly, for example, it can be fixed connection, or detachable connection, or integral connection; it can be mechanical connection, or electrical connection; it can be directly connected, or indirectly connected through intermediate medium, it can be the communication between two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0075] It should be noted that in the present application, such as "first" and "second" and other relational terms 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 the entities or operations. Moreover, the terms "include", "contain" or any other variant thereof are intended to cover non-exclusive inclusion, so that the process, method, article or equipment including a series of elements not only includes those elements, but also includes other elements not explicitly listed, or includes elements inherent in such process, method, article or equipment. Without more limitation, the element defined by the sentence "including a…" does not exclude the presence of other identical elements in the process, method, article or equipment including the element.

[0076] The foregoing detailed description of the application has been presented for purposes of illustration and description. Various modifications and changes can be made to these embodiments without departing from the spirit and scope of the application. It is intended that the scope of the application should not be limited by the particular representative embodiments described above. Rather, the general scope of the application is to be determined by the appended claims and their equivalents.

Claims

1. A side-push interstage separation device, characterized in that, The side-push interstage separator uses a side-push cylinder. The side-push cylinder includes: The first cylinder (31) includes a first cylinder barrel (311), a first piston (313) disposed in the first cylinder barrel (311), a first piston rod (312) connected to the first piston (313), and a first nozzle (314) disposed on the outside of the first cylinder barrel (311) for side-blowing gas. Gas cylinder (5), which provides a gas source for cylinder (3); The device includes: Interstage compartment (4), with cylinder (3) and gas cylinder (5) provided around the interstage compartment (4) to supply gas source; The main stage (1) of the aircraft is located at the front end of the interstage compartment (4). The interstage compartment (4) can be separated from the main stage (1) by the side thrust of the cylinder (3). The cylinder (3) also includes: A second cylinder (32) that can be axially pushed apart includes a second cylinder barrel (321), a second piston (323) disposed in the second cylinder barrel (321), and a second piston rod (322) connected to the second piston (323). The inter-stage compartment (4) is connected to the main stage (1) of the aircraft by explosive bolts (2); When the main stage (1) and booster stage of the spacecraft are about to separate, the gas cylinder (5) and the explosive bolt (2) are used to receive the separation signal. The explosive bolt (2) is detonated, the main stage (1) and the interstage section of the spacecraft are disconnected, and the gas in the gas cylinder (5) pushes the first piston (313) in the first cylinder (31) through the gas passage (6). The first piston (313) pushes the first piston rod (312) forward, and the first piston rod (312) holds the main stage (1) of the spacecraft and pushes the booster main stage (1) forward. When the first piston rod (312) moves to the designed stroke, that is, when the main stage (1) and the interstage compartment (4) of the aircraft reach the axial separation distance, the gas in the first cylinder (31) is ejected from the first nozzle (314), pushing the interstage compartment (4) to the side in the opposite direction to the flight attitude of the main stage (1). At the same time, the gas in the gas cylinder (5) pushes the second piston (323) in the second cylinder (32) to move. The second piston (323) drives the second piston rod (322) to push forward. The second piston rod (322) pushes against the main stage (1) of the aircraft to help it move forward, realizing the axial and lateral separation of the interstage compartment (4) and the main stage (1) of the aircraft.

2. The side-push interstage separation device as described in claim 1, characterized in that: There are a total of several cylinders (31) and cylinders (32), and the number is even.

3. The side-push interstage separation device as described in claim 2, characterized in that: Several first cylinders (31) are all located on the opposite side of the side thrust direction of the interstage compartment (4), and the interstage compartment (4) is pushed sideways through the first nozzle (314) of the first cylinder (31).

4. The side-push interstage separation device as described in claim 3, characterized in that: Several second cylinders (32) are arranged around the interstage compartment (4).

5. The side-push interstage separation device as described in claim 1, characterized in that: The first nozzle (314) is located on the outer side of the first cylinder (311) away from the first piston (313).

6. The side-push interstage separation device as described in claim 1, characterized in that: An air passage (6) is provided between the cylinder (3) and the gas cylinder (5) to connect them.

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