Carrier rocket parallel connection and separation structure

Abstract

The invention provides a carrier rocket parallel connection and separation structure which comprises an engine shell, a front skirt and a rear skirt are arranged at the two ends of the engine shell respectively, a connecting assembly is fixed between the front skirt and the rear skirt, and the connecting assembly comprises a plurality of connecting bases; an adapter used for installing an aircraft is arranged on one side of the engine shell. A plurality of hoop assemblies are distributed on the engine shell and comprise two arc-shaped pieces, the first ends of the two arc-shaped pieces are fixed to the connecting base, the second ends of the two arc-shaped pieces are fixed to a connecting plate, and the arc-shaped pieces, the connecting plate and the connecting base are arranged on the engine shell in a sleeving mode after being spliced and connected with the adapter; the arc-shaped piece, the connecting plate and the connecting base are spliced and then arranged on the engine shell in a sleeving mode, so that the adapter can be fixed to the engine shell through the hoop assembly, compared with a traditional welding installation interface mode, the problem that the structural strength of the shell connecting position is insufficient due to welding is solved, flaw detection does not need to be conducted, and the cost is reduced. And the structure reliability is improved while high efficiency and convenience are achieved, and convenience is provided for batch production of rockets.

Description

Technical Field

[0001] This application relates to the technical field of launch vehicles, and particularly relates to a parallel connection and separation structure for a launch vehicle. Background Art

[0002] Solid rocket motors have the characteristics of simple structure, high reliability, large thrust, and convenient use, so they have a wide range of applications. The front and rear skirts in their structure are usually used for axially connecting the shell or other components in series. When other components need to be connected in parallel outside the solid rocket motor shell, a form of locally welding the same material installation interfaces is usually adopted. This welded connection structure has the disadvantages of insufficient structural strength at the shell connection, and the welds need to pass flaw detection before they can be delivered for use, resulting in low reliability and being not conducive to batch production of rockets. Therefore, the above problems need to be solved urgently. Summary of the Invention

[0003] In view of the above-mentioned defects or deficiencies in the prior art, it is desired to provide a parallel connection and separation structure for a launch vehicle.

[0004] This application provides a parallel connection and separation structure for a launch vehicle, including: An engine shell, with a front skirt and a rear skirt respectively provided at both ends of the engine shell. A connection assembly is fixed between the front skirt and the rear skirt, and the connection assembly includes a plurality of connection seats distributed along a first direction; An adapter, which is arranged on the side of the engine shell away from the connection assembly, and the adapter is used to install the aircraft; A hoop assembly, with a plurality of hoop assemblies distributed along the first direction on the engine shell. The hoop assembly includes: Arc-shaped members, with two arc-shaped members symmetrically arranged on both sides of the engine shell, and the first ends of the two arc-shaped members are respectively fixedly connected to the connection seats; A connecting plate, which is fixedly connected to the second ends of the two arc-shaped members respectively; The two arc-shaped members, the connecting plate and the connection seats are spliced and sleeved on the engine shell, and are fixedly connected to the adapter.

[0005] According to the technical solutions provided by some embodiments of this application, A first clamping groove is opened on the side of the first end of the arc-shaped member close to the engine shell, and the first clamping groove is used to arrange the connection seat and fixedly connect with the connection seat; A second clamping groove is opened on the side of the second end of the arc-shaped member away from the engine shell, and the second clamping groove is used to arrange the connecting plate and fixedly connect with the connecting plate; The arc-shaped member has a connecting portion near the second end, and the connecting portion is used for fixedly connecting with the adapter.

[0006] According to the technical solutions provided by some embodiments of the present application, The first end is provided with a first threaded hole, the first threaded hole communicates with the first clamping groove, and the first threaded hole is fixedly connected with the connecting seat through a first bolt; The second end is provided with a second threaded hole, the second threaded hole communicates with the second clamping groove, and the second threaded hole is fixedly connected with the connecting plate through a second bolt; The connecting portion is provided with a third threaded hole, and the third threaded hole is fixedly connected with the fitting through a third bolt.

[0007] According to the technical solutions provided by some embodiments of the present application, A plurality of pyrotechnic devices are provided between the adapter and the aircraft; The pyrotechnic device has a first state and a second state. When in the first state, the adapter is fixedly connected with the aircraft. When in the second state, the adapter is disconnected from the aircraft; The adapter is further provided with a separation push mechanism, and the separation push mechanism is used to apply a normal thrust to the aircraft in the second state.

[0008] According to the technical solutions provided by some embodiments of the present application, The adapter is also provided with a plurality of shear pins corresponding to the pyrotechnic devices; The shear pins are fixedly installed on the adapter and are pluggable and unplugable with the aircraft, and are used to reduce the shear force received by the pyrotechnic devices.

[0009] According to the technical solutions provided by some embodiments of the present application, One side of the adapter close to the aircraft is further provided with a shear-resistant structure; The shear-resistant structure is a sunken docking groove, which is used to dock with the protruding part on the aircraft, so as to reduce the shear force received by the pyrotechnic devices.

[0010] According to the technical solutions provided by some embodiments of the present application, the hoop assembly and the connecting seat are filled with felt between the engine housing.

[0011] According to the technical solutions provided by some embodiments of the present application, The adapter is also provided with a splitter; The splitter is pluggable and unplugable with the aircraft, and is used to transmit a separation signal to the aircraft as the starting control time point.

[0012] Compared with the prior art, the beneficial effects of the present application are as follows: The present application provides a parallel connection and separation structure for a launch vehicle, including an engine casing. Front skirts and rear skirts are respectively provided at both ends of the engine casing. A connection assembly is fixed between the front skirt and the rear skirt. The connection assembly includes a plurality of connection seats distributed along a first direction. An adapter is provided on one side of the engine casing away from the connection assembly, and the adapter is used to install a flying vehicle. A plurality of hoop assemblies are distributed along the first direction on the engine casing. Each hoop assembly includes two arc-shaped members symmetrically arranged on both sides of the engine casing. The first ends of the two arc-shaped members are respectively fixedly connected to the connection seats. A connecting plate is fixedly connected to the second ends of the two arc-shaped members. After the two arc-shaped members, the connecting plate and the connection seats are spliced, they are sleeved on the engine casing and fixedly connected to the adapter. By sleeving the engine casing after splicing the two arc-shaped members and the connecting plate with the connection seats of the connection assembly, the adapter can be fixedly connected to the engine casing through the hoop assembly. Compared with the traditional form of locally welding the same material installation interfaces, the hoop assembly can be fixedly connected to the adapter by a mechanical connection method, avoiding the problem of insufficient structural strength at the connection of the casing caused by welding. There is no need for flaw detection, which is efficient and convenient while improving the structural reliability and providing convenience for the mass production of rockets.

[0013] It should be understood that the description of technical features, technical solutions, beneficial effects or similar languages in the present application does not imply that all features and advantages can be achieved in any single embodiment. On the contrary, it can be understood that the description of features or beneficial effects means that specific technical features, technical solutions or beneficial effects are included in at least one embodiment. Therefore, the description of technical features, technical solutions or beneficial effects in this specification does not necessarily refer to the same embodiment. Furthermore, the technical features, technical solutions and beneficial effects described in this embodiment can be combined in any appropriate manner. Those skilled in the art will understand that an embodiment can be implemented without one or more specific technical features, technical solutions or beneficial effects of a specific embodiment. In other embodiments, additional technical features and beneficial effects can also be identified in specific embodiments that do not reflect all embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a schematic structural diagram of the parallel connection and separation structure of the launch vehicle provided by the embodiment of the present application; Figure 2 It is a schematic structural diagram of the adapter of the parallel connection and separation structure of the launch vehicle provided by the embodiment of the present application; Figure 3 It is a schematic structural diagram of the pyrotechnics and shear pins of the parallel connection and separation structure of the launch vehicle provided by the embodiment of the present application; Figure 4 It is a schematic structural diagram of the hoop assembly of the parallel connection and separation structure of the launch vehicle provided by the embodiment of the present application.

[0015] The text annotations shown in the figure are as follows: 100 - engine housing; 200 - adapter; 210 - shear pin; 220 - pyrotechnic device; 230 - shear structure; 240 - split insertion; 300 - hoop assembly; 301 - arc-shaped member; 302 - connecting plate; 303 - felt; 400 - connection assembly; 401 - connection seat; 500 - nitrogen spring. Detailed implementation manners

[0016] To enable those skilled in the art to better understand the technical solutions of the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below in conjunction with the accompanying drawings. The description in this part is only exemplary and explanatory, and should not have any restrictive effect on the protection scope of the present application. Specifically, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0017] It should be noted that similar reference numerals and letters denote similar items in the following drawings. Therefore, once an item is defined in one drawing, it does not need to be further defined and explained in subsequent drawings. In addition, the terms "comprising" and "having" and any variations thereof are intended to cover non-exclusive inclusion. For example, a process, method, system, product or device that includes a series of steps or units does not necessarily have to be limited to those clearly listed steps or units, but may include other steps or units not clearly listed or inherent to these processes, methods, products or devices.

[0018] As mentioned in the background art, to solve the problems existing in the prior art, the present embodiment provides a parallel connection and separation structure for a launch vehicle, including: An engine housing 100, with a front skirt and a rear skirt respectively provided at both ends of the engine housing 100, and a connection assembly 400 is fixed between the front skirt and the rear skirt. The connection assembly 400 includes a plurality of connection seats 401 distributed along a first direction; An adapter 200, which is provided on the side of the engine housing 100 away from the connection assembly 400, and the adapter 200 is used to mount the aircraft; A hoop assembly 300, with a plurality of hoop assemblies 300 distributed along the first direction on the engine housing 100, and the hoop assembly 300 includes: Arc-shaped members 301, with two arc-shaped members 301 symmetrically provided on both sides of the engine housing 100, and the first ends of the two arc-shaped members 301 are respectively fixedly connected to the connection seats 401; A connecting plate 302, which is respectively fixedly connected to the second ends of the two arc-shaped members 301; After the two arc-shaped members 301, the connecting plate 302 and the connecting seat 401 are spliced, they are sleeved on the engine housing 100 and fixedly connected to the adapter 200.

[0019] As Figure 1 and Figure 4 shown, the first direction is the axial direction of the engine housing 100. Front skirts and rear skirts are respectively provided at both axial ends of the engine housing 100. Both ends of the connecting assembly 400 are respectively connected to the front skirt and the rear skirt on the engine housing 100. It and the adapter 200 are respectively located on opposite sides of the engine housing 100. And a counterweight is provided inside the connecting assembly 400 for balancing the weights on both sides of the engine housing 100, thereby adjusting the position of the center of mass of the overall structure. The balance of the center of mass position helps to optimize the dynamic performance during the rocket flight, reduce the deviation of the flight attitude, reduce the difficulty of flight control, and further improve the flight accuracy and safety of the rocket; In this embodiment, three hoop assemblies 300 are sleeved on the engine housing 100. The three hoop assemblies 300 are axially distributed along the engine housing 100. The two arc-shaped members 301 of each hoop assembly 300 are symmetrically arranged. The first ends of the two arc-shaped members 301 are respectively fixed to the connecting seat 401, and the second ends of the two are respectively fixed to the connecting plate 302, and then spliced to form an annular structure to be sleeved on the engine housing 100. The fixed method after the hoop assembly 300 is spliced is convenient for installation and disassembly, making the overall connection structure of the hoop assembly 300 more stable and reliable, and at the same time facilitating the replacement or repair of each component when needed; The adapter 200 is connected to the three hoop assemblies 300 simultaneously by a mechanical connection method, and then the adapter 200 is fixed on the engine housing 100.

[0020] After the two arc-shaped members 301, the connecting plate 302 and the connecting seat 401 of the connecting assembly 400 are spliced and sleeved on the engine housing 100, the adapter 200 can be fixedly connected to the engine housing 100 through the hoop assembly 300. Compared with the traditional form of locally welding the same material installation interface, the hoop assembly 300 can be fixed by mechanical connection after splicing, avoiding the problem of insufficient structural strength at the connection of the housing caused by welding, and eliminating the need for flaw detection. It is efficient and convenient while improving the structural reliability, providing convenience for the mass production of rockets.

[0021] In a preferred embodiment, A first clamping groove is provided on the side of the first end of the arc-shaped member 301 close to the engine housing 100. The first clamping groove is used for arranging the connecting seat 401 and fixedly connecting with the connecting seat 401; A second clamping groove is provided on the side of the second end of the arc-shaped member 301 far from the engine housing 100. The second clamping groove is used for arranging the connecting plate 302 and fixedly connecting with the connecting plate 302; The arc-shaped part 301 has a connecting part near the second end, and the connecting part is used for fixedly connecting with the adapter 200.

[0022] As Figure 4 As shown, an approximately T-shaped connecting cavity is formed between the first ends of the two arc-shaped parts 301. The connecting cavity is used for arranging the connecting seat 401. The two end parts of the connecting seat 401 on the side close to the engine housing 100 are respectively located in the two first clamping grooves and fixedly connected. After the second ends of the two arc-shaped parts 301 are butted, the two second clamping grooves enclose to form an arc-shaped groove. The inner contour of the arc-shaped groove matches the outer contour of the connecting plate 302. The connecting plate 302 is embedded in the arc-shaped groove and fixedly connected with the two arc-shaped parts 301 respectively. Thus, the two arc-shaped parts 301, the connecting seat 401 and the connecting plate 302 are spliced to form an annular structure. The connecting part is located on one side of the arc-shaped part 301 near the second end, and the connecting part is used for being fixedly connected with the adapter 200 by mechanical connection.

[0023] In a preferred embodiment, The first end is provided with a first threaded hole, and the first threaded hole communicates with the first clamping groove. The first threaded hole is fixedly connected with the connecting seat 401 through a first bolt. The second end is provided with a second threaded hole, and the second threaded hole communicates with the second clamping groove. The second threaded hole is fixedly connected with the connecting plate 302 through a second bolt. The connecting part is provided with a third threaded hole, and the third threaded hole is fixedly connected with the fitting through a third bolt.

[0024] As Figure 4 As shown, a plurality of first threaded holes are opened on the first end and communicate with the first clamping groove. When the two end parts of the connecting seat 401 on the side close to the engine housing 100 are respectively located in the two first clamping grooves, a plurality of first bolts respectively penetrate through the first end and the connecting seat 401 from the corresponding first threaded holes and are threadedly connected with the two, so as to fix the arc-shaped part 301 and the connecting seat 401. The second threaded hole is opened on the second end and communicates with the second clamping groove. When the connecting plate 302 is located in the two second clamping grooves, two second bolts respectively penetrate through the connecting plate 302 and the second end from the corresponding second threaded holes and are threadedly connected with the two, so as to fix the arc-shaped part 301 and the connecting plate 302. A plurality of third threaded holes are opened on the connecting part. A plurality of third bolts respectively penetrate through the adapter 200 and the arc-shaped part 301 from the corresponding third threaded holes and are threadedly connected with the two, so as to fix the arc-shaped part 301 and the adapter 200.

[0025] In a preferred embodiment, A plurality of pyrotechnic devices 220 are arranged between the adapter 200 and the aircraft. The pyrotechnic device 220 has a first state and a second state. When in the first state, the adapter 200 is fixedly connected to the aircraft. When in the second state, the adapter 200 is disconnected from the aircraft. The adapter 200 is also provided with a separation and thrust mechanism, which is used to apply a normal thrust to the aircraft in the second state.

[0026] Such as Figure 2 and Figure 3 As shown, the pyrotechnic device 220 uses a non-electric detonating type M16 explosive bolt. In this embodiment, 6 pyrotechnic devices 220 are provided. The 6 pyrotechnic devices 220 are symmetrically arranged along the center line of the adapter 200 on the end face of the adapter 200 away from the engine housing 100. Their initiating ends are arranged inside the adapter 200. Initially, the pyrotechnic device 220 is connected to the aircraft to fix the aircraft to the adapter 200, that is, the above-mentioned first state. When separation is required, the initiating end is ignited, and the pyrotechnic device 220 detonates and disconnects, and the aircraft is disconnected from the adapter 200, that is, the above-mentioned second state. The separation and thrust mechanism uses a nitrogen spring 500, and the inflation requirement is 23.8 ± 0.1 MPa. It has outstanding advantages such as a long thrust application time, simple assembly, and simple and reliable working form. The outer diameter of the nitrogen spring 500 is φ75 mm, the total length is 195 mm, the structural stroke is 75 mm, and the effective stroke is 73 mm. Two nitrogen springs 500 are symmetrically arranged before and after the X-direction centroid of the aircraft. The position of the nitrogen spring 500 on the adapter 200 is adjustable to meet the change of ±20 mm along the X-direction centroid of the aircraft, which can ensure that the thrust resultant force direction of the nitrogen spring 500 during separation passes through the centroid of the aircraft.

[0027] In a preferred embodiment, The adapter 200 is also provided with a plurality of shear pins 210 corresponding to the pyrotechnic device 220; The shear pins 210 are fixedly installed on the adapter 200 and are inserted and unplugged with the aircraft to reduce the shear force received by the pyrotechnic device 220.

[0028] Such as Figure 2 and Figure 3 As shown, in this embodiment, the number of shear pins 210 is also set to 6. The 6 shear pins 210 are symmetrically arranged along the center line of the adapter 200 on the end face of the adapter 200 away from the engine housing 100 and are respectively arranged on one side of the pyrotechnic device 220. The front taper of the shear pin 210 is 1:10. A pin seat that cooperates with the shear pin 210 is provided on the aircraft. The shear pin 210 is inserted into the pin seat on the aircraft along the direction perpendicular to the axial direction of the engine housing 100, avoiding the pyrotechnic device 220 from bearing the shear force between the adapter 200 and the aircraft during flight. In a preferred embodiment, On the side of the adapter 200 close to the aircraft, there is also a shear structure 230; The shear structure 230 is a sunken docking groove for docking with the protruding part on the aircraft, thereby reducing the shear force on the initiator 220.

[0029] As Figure 2 shown, the shear structure 230 is provided on the end face of the adapter 200 on the side close to the aircraft. The shear structure 230 and the six shear pins 210 are multi-constraint positioning. To avoid the machining error and assembly error that may prevent all installations from being in place, the shear pins 210 are designed as a structure that can move up and down, and the deviation of the X and Z directions of the pin holes can be adapted by adjusting the length of the shear pins 210 screwed into the pin seats.

[0030] In a preferred embodiment, a felt 303 is filled between the hoop assembly 300 and the connecting seat 401 and the engine housing 100.

[0031] As Figure 4 shown, the theoretical gap between the inner surface of the annular structure formed by splicing the two arc-shaped parts 301, the connecting plate 302 and the connecting seat 401 and the outer surface of the engine housing 100 is 1.5 mm, and the felt 303 is used for filling; to improve the overall stiffness and friction, a pre-tightening force of 0.5 Mpa needs to be applied when installing the felt 303; to eliminate the precision error of the hoop assembly 300 and the dimensional error of the outer surface of the engine housing 100, different specifications and thicknesses of felt 303 need to be used to test the gap between the annular structure and the engine housing 100 during the assembly process. The relationship between the above gap and the selection of the felt 303 is shown in the following table; Table 1 Serial number Specification (mm) Compressed to (mm) Instantaneous elastic modulus (MPa) Applicable clearance value clearance (mm) 1 2.5 1.3 0.6 1.3-1.5 2 3 1.9 0.68 1.5-2.0 3 3.5 2.4 0.76 2.0-2.5 4 4 3.0 0.84 2.5-3.0 In a preferred embodiment, there is also a splitter 240 on the adapter 200; the splitter 240 is pluggably connected to the aircraft and is used to transmit a separation signal to the aircraft as the starting control time point of the aircraft.

[0032] In this article, specific examples are used to elaborate on the principles and implementation methods of the present application. The description of the above embodiments is only used to help understand the method of the present application and its core idea. The above is only the preferred implementation mode of the present application. It should be noted that due to the limited nature of the written expression, there are objectively infinite specific structures. For those of ordinary skill in the art in this technical field, without departing from the principle of the present invention, several improvements, refinements or changes can be made, or the above technical features can be combined in an appropriate manner; these improvements, refinements, changes or combinations, or the direct application of the concept and technical solution of the invention to other occasions without improvement, should all be regarded as the protection scope of the present application.

Claims

1. A parallel connection and separation structure for a launch vehicle, characterized in that including an engine housing (100) with a front skirt and a rear skirt respectively provided at both ends thereof, and a connection assembly (400) fixed between the front skirt and the rear skirt, the connection assembly (400) including a plurality of connection seats (401) distributed in a first direction; an adapter (200) provided on a side of the engine housing (100) away from the connection assembly, the adapter (200) being used for mounting an aircraft; a hoop assembly (300), a plurality of the hoop assemblies (300) being distributed on the engine housing (100) in the first direction, the hoop assembly (300) including: arc-shaped members (301), two of the arc-shaped members (301) being symmetrically provided on both sides of the engine housing (100), and first ends of the two arc-shaped members (301) being respectively fixedly connected to the connection seats (401); a connecting plate (302) fixedly connected to second ends of the two arc-shaped members (301) respectively; after the two arc-shaped members (301), the connecting plate (302) and the connection seats (401) are spliced, they are sleeved on the engine housing (100) and fixedly connected to the adapter (200).

2. The parallel connection and separation structure of a launch vehicle according to claim 1, wherein a first clamping groove is formed on a side of the first end of the arc-shaped member (301) close to the engine housing (100), and the first clamping groove is used for arranging the connection seat (401) and fixedly connecting with the connection seat (401); a second clamping groove is formed on a side of the second end of the arc-shaped member (301) away from the engine housing (100), and the second clamping groove is used for arranging the connecting plate (302) and fixedly connecting with the connecting plate (302); a connecting portion is provided on the arc-shaped member (301) close to the second end, and the connecting portion is used for fixedly connecting with the adapter (200).

3. The parallel connection and separation structure of a launch vehicle according to claim 2, wherein a first threaded hole is provided at the first end, the first threaded hole communicates with the first clamping groove, and the first threaded hole is fixedly connected to the connection seat (401) through a first bolt; a second threaded hole is provided at the second end, the second threaded hole communicates with the second clamping groove, and the second threaded hole is fixedly connected to the connecting plate (302) through a second bolt; a third threaded hole is provided at the connecting portion, and the third threaded hole is fixedly connected to the adapter (200) through a third bolt.

4. The parallel connection and separation structure of a launch vehicle according to claim 1, wherein a plurality of pyrotechnic devices (220) are provided between the adapter (200) and the aircraft; the pyrotechnic device (220) has a first state and a second state. When in the first state, the adapter (200) is fixedly connected to the aircraft, and when in the second state, the adapter (200) is disconnected from the aircraft; The adapter (200) is further provided with a separating and pushing mechanism, which is used to apply a normal thrust to the aircraft in the second state.

5. The parallel connection and separation structure of a launch vehicle according to claim 4, wherein The adapter (200) is further provided with a plurality of shear pins (210) corresponding to the pyrotechnic device (220); The shear pins (210) are fixedly installed on the adapter (200) and are pluggable and unplugable with the aircraft, and are used to reduce the shear force received by the pyrotechnic device (220).

6. The parallel connection and separation structure of a launch vehicle according to claim 1, wherein The side of the adapter (200) close to the aircraft is further provided with a shear structure (230); The shear structure (230) is a sunken docking groove, which is used to dock with the protruding part on the aircraft, so as to reduce the shear force received by the pyrotechnic device (220).

7. The parallel connection and separation structure of a launch vehicle according to claim 1, wherein A felt (303) is filled between the hoop assembly (300) and the connection seat (401) and the engine casing (100).

8. The parallel connection and separation structure of a launch vehicle according to claim 1, wherein The adapter (200) is further provided with a plug-in (240); The plug-in (240) is pluggable and unplugable with the aircraft, and is used to transmit a separation signal to the aircraft as the starting control time point of the aircraft.

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