A shield for thermal separation of rocket stages and a launch vehicle

Abstract

The application discloses a protection device for rocket interstage thermal separation and a carrier rocket, wherein the protection device comprises a support, a connecting plate, a protection plate and a driving part; the connecting plate arranged on the support is connected with the protection plate; the protection plate is movably connected with the connecting plate; the driving part is arranged between the protection plate and the connecting plate and is used for driving the protection plate to move from a first position to a second position; in actual operation, the cabin section of the carrier rocket is in the first position before the interstage thermal separation process, and the plug is inserted into the socket; after the plug is separated from the socket, the protection plate moves from the first position to the second position under the action of the driving part; at this time, the protection plate covers the socket, the socket is shielded by the protection plate; at this time, the high-speed gas flow of the engine exhaust flame is diffused backward after being sprayed from the nozzle; the protection plate effectively protects the socket from being impacted by the engine exhaust flame, thereby the reliability of the electrical socket is maintained, and the stability of the operation of the carrier rocket is improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of space rockets, in particular to a protective device for inter-stage thermal separation of a rocket and a carrier rocket. BACKGROUND

[0002] The information provided in this section is for the purpose of generally presenting the context of the disclosure. To the extent that the descriptions in this section describe the work of the inventors, and to the extent that the descriptions are not considered to be prior art to the claims, the descriptions are not necessarily considered to be prior art by virtue of being included in this section.

[0003] During flight, the structure and electrical units of the carrier rocket will undergo severe thermal environment tests. In order to cope with the thermal environment, effective thermal protection measures need to be taken for the structure and electrical units. The inter-stage separation is composed of a separation plug and a socket. After the inter-stage structure is separated, the plug is pulled out of the socket under the action of mechanical force, realizing the separation of the electrical cable network of the carrier rocket.

[0004] During the inter-stage thermal separation of the carrier rocket, when the plug is separated, the socket is completely exposed at the bottom of the carrier rocket. At this time, the high-speed gas flow of the upper stage engine exhaust is diffused backward after being ejected from the nozzle, and the separation socket will be impacted by the exhaust of the upper stage engine. The electrical socket impacted by the gas flow may have a short circuit risk, which may cause flight failure. SUMMARY

[0005] In view of the defects in the prior art, the present application provides a protective device for inter-stage thermal separation of a rocket and a carrier rocket to solve the problem that the socket is exposed after the inter-stage structure is separated and is impacted by the engine exhaust.

[0006] The above-mentioned purpose of the present application is mainly realized by the following technical scheme:

[0007] A protective device for inter-stage thermal separation of a rocket, comprising:

[0008] a support for fixing at a socket on the rocket;

[0009] a connecting plate fixed on the support;

[0010] a protective plate movably connected with the connecting plate, and the protective plate has a first position and a second position, when the protective plate is in the first position, the protective plate and the socket have a space for plug-in and plug-out, and when the protective plate is in the second position, the protective plate covers the socket;

[0011] A driving part is arranged between the protection plate and the connecting plate and is used to drive the protection plate to move from the first position to the second position.

[0012] Further, the protection plate is rotatably connected with the connecting plate.

[0013] Further, the driving part comprises a rotating shaft and a double torsion spring, the rotating shaft penetrates the connecting plate and the protection plate at the same time, so that the protection plate can rotate around the rotating shaft, the double torsion spring is sleeved on the rotating shaft, one end of the double torsion spring is clamped on the connecting plate, and the other end of the double torsion spring is pressed on the protection plate.

[0014] Further, the end of the rotating shaft is provided with a plug for limiting the axial movement of the rotating shaft.

[0015] Further, the support is provided with a reserved hole for accommodating the socket.

[0016] Further, the protection plate is provided with a reinforcing rib on each side.

[0017] Further, the support is provided with at least two groups of mounting hole positions.

[0018] Further, the support and the protection plate are each provided with a constraint hole, a limiting piece is movably arranged in the constraint hole, and when the protection plate is located at the first position, the limiting piece can extend into the two constraint holes to limit the movement of the protection plate.

[0019] Further, the protection plate is provided with a heat insulation layer.

[0020] Based on the same inventive concept, the application also provides a carrier rocket, comprising a plurality of cabin sections connected in sequence, a socket and a plug for pluggable connection are arranged between adjacent cabin sections, and the protection device as described above, the support is fixed on the cabin section.

[0021] Compared with the prior art, the application has the following advantages:

[0022] The protection device in the application is arranged at the socket between adjacent cabin sections, is fixed through a support, a connecting plate arranged on the support connects a protection plate, the protection plate is movably connected with the connecting plate, and the protection plate has a first position and a second position, when the protection plate is located at the first position, a space for plugging and unplugging of a plug is formed between the protection plate and the socket, when the protection plate is located at the second position, the protection plate covers the socket, a driving part is arranged between the protection plate and the connecting plate, for driving the protection plate to move from the first position to the second position, in the actual operation process, the cabin section of the carrier rocket is before the interstage thermal separation process, the protection plate is at the first position, and the plug is arranged in the socket, after the interstage thermal separation process is completed, the plug is separated from the socket, under the action of the driving part, the protection plate moves from the first position to the second position, at this time, the protection plate covers the socket, the socket is shielded by the protection plate, at this time, the high-speed gas flow of the engine exhaust plume is diffused backward after being sprayed from the nozzle, the protection plate effectively protects the socket from being impacted by the engine exhaust plume, and the reliability of the electrical socket is maintained, and the stability of the operation of the carrier rocket is improved. BRIEF DESCRIPTION OF DRAWINGS

[0023] In order to more clearly illustrate the technical solutions in the embodiments of the application, the drawings needed to be used in the embodiment description will be briefly introduced. Obviously, the drawings in the following description are only some embodiments of the application, and other drawings can be obtained by those skilled in the art without creative labor.

[0024] Figure 1 The first direction structure schematic diagram of the protection device provided by the embodiment of the application is shown in the figure.

[0025] Figure 2 The second direction structure schematic diagram of the protection device provided by the embodiment of the application is shown in the figure.

[0026] Figure 3 The installation schematic diagram of the protection device provided by the embodiment of the application is shown in the figure.

[0027] Figure 4 The structure schematic diagram of the protection plate in the first position provided by the embodiment of the application is shown in the figure.

[0028] Figure 5 The structure schematic diagram of the protection plate in the second position provided by the embodiment of the application is shown in the figure.

[0029] In the figure: 1, support; 2, connecting plate; 3, protection plate; 4, driving part; 41, rotating shaft; 42, double torsion spring; 43, bolt; 51, reserved hole; 52, reinforcing rib; 53, mounting hole; 54, constraint hole; 61, socket; 62, plug. DETAILED DESCRIPTION

[0030] The application will be further described below in conjunction with the accompanying drawings and specific embodiments. It should be noted that the description of these embodiments is used to help understand the application, but does not constitute a limitation of the application. The specific structures and functional details disclosed herein are only used to describe the example embodiments of the application. However, the application can be embodied in many alternative forms, and should not be understood as limited in the embodiments described herein.

[0031] As Figures 1-5 shown, Figure 1 a first direction structure schematic diagram of the protection device provided by the embodiment of the application, Figure 2 a second direction structure schematic diagram of the protection device provided by the embodiment of the application, Figure 3 an installation schematic diagram of the protection device provided by the embodiment of the application, Figure 4 a structure schematic diagram of the protection plate 3 in the first position provided by the embodiment of the application, Figure 5 a structure schematic diagram of the protection plate 3 in the second position provided by the embodiment of the application.

[0032] A protection device for inter-stage thermal separation of a rocket, comprising a support 1, a connecting plate 2, a protection plate 3 and a driving part 4, wherein:

[0033] The support 1 is used to be fixed at the socket 61 on the rocket, and the connection mode between the support 1 and the rocket body can be selected correspondingly according to the flight conditions, so as to keep the stability of the support 1 during the flight of the rocket, and provide a stable positioning basis for the stability of other components of the protection device, improve the overall connection reliability, and be suitable for the complex flight conditions of the rocket.

[0034] The connecting plate 2 is fixed on the support 1.

[0035] As Figure 4 shown, the protection plate 3 is movably connected with the connecting plate 2, and the protection plate 3 has a first position and a second position, when the protection plate 3 is in the first position, the protection plate 3 and the socket 61 have a space for plugging and unplugging of the plug 62, that is, when the protection plate 3 is in the first position, the separation process of the plug 62 on the socket 61 is not affected by the protection plate 3, the plug 62 can be normally separated, and the stability of the launch rocket during the inter-stage thermal separation process is maintained.

[0036] As Figure 5 shown, when the protection plate 3 is in the second position, the protection plate 3 covers the socket 61, at this time, the protection plate 3 at the second position covers the socket 61, and forms protection for the socket 61 and the internal elements of the socket 61.

[0037] The driving part 4 is arranged between the protective plate 3 and the connecting plate 2, and is used for driving the protective plate 3 to move from the first position to the second position.

[0038] The working principle of the embodiment is as follows: the protective device is arranged at the socket 61 between adjacent cabin sections, is fixed through the support 1, the connecting plate 2 arranged on the support 1 is connected with the protective plate 3, the protective plate 3 is movably connected with the connecting plate 2, and the protective plate 3 has a first position and a second position; when the protective plate 3 is located at the first position, the protective plate 3 has a space for the plug 62 to be plugged and unplugged with the socket 61; when the protective plate 3 is located at the second position, the protective plate 3 is arranged on the socket 61; the driving part 4 is arranged between the protective plate 3 and the connecting plate 2, and is used for driving the protective plate 3 to move from the first position to the second position; in the actual operation process, the cabin section of the carrier rocket is located at the first position before the interstage thermal separation process, and the plug 62 is arranged on the socket 61; after the interstage thermal separation process is completed, the plug 62 is separated from the socket 61; under the action of the driving part 4, the protective plate 3 moves from the first position to the second position; at this time, the protective plate 3 is arranged on the socket 61, and the socket 61 is shielded by the protective plate 3; at this time, the high-speed gas flow of the engine exhaust plume is diffused backward after being sprayed from the nozzle, the protective plate 3 effectively protects the socket 61 from being impacted by the engine exhaust plume, thereby the reliability of the electrical socket 61 is maintained, and the stability of the operation of the carrier rocket is improved.

[0039] Further, on the basis of the above embodiment, the protective plate 3 is rotatably connected with the connecting plate 2; compared with the overall movement of the protective plate 3, the protective plate 3 is arranged to rotate from the first position to the second position, the protective plate 3 has a more stable and reliable state, and the shaking or vibration of the overall protective plate 3 is reduced.

[0040] Further, on the basis of the above embodiment, the driving part 4 comprises a rotating shaft 41 and a double torsion spring 42; the rotating shaft 41 penetrates through the connecting plate 2 and the protective plate 3 at the same time, so that the protective plate 3 can rotate around the rotating shaft 41; the double torsion spring 42 is sleeved on the rotating shaft 41, one end of the double torsion spring 42 is clamped on the connecting plate 2, and the other end of the double torsion spring 42 is pressed on the protective plate 3.

[0041] It should be noted that, in the installation process of the double torsion spring 42, the first position of the protective plate 3 is taken as a reference position; after the double torsion spring 42 is clamped on the connecting plate 2, the double torsion spring 42 can be operated to rotate a stroke and then be pressed on the protective plate 3, so that the deformation restoring force of the double torsion spring 42 itself can drive the protective plate 3 to move from the first position to the second position, thereby replacing the driving part 4 which needs to be connected to the electrical system, and the structure is simpler and more reliable.

[0042] And after the manual operation of the protective plate 3 is returned from the second position to the first position, the double torsion spring 42 is deformed again and has a deformation restoring force, so as to drive the protective plate 3 to rotate from the first position to the second position again, which is reusable and convenient and fast to operate.

[0043] As shown in Figures 1-3 Further, on the basis of the above embodiment, the end of the rotating shaft 41 is provided with a plug 43 for limiting the axial movement of the rotating shaft 41, and the protective plate 3 is repeatedly switched between the first position and the second position. The plug 43 limits the axial displacement of the rotating shaft 41, avoids the separation of the rotating shaft 41, the connecting plate 2 and the protective plate 3, and improves the reliability in the repeated operation process.

[0044] Further, on the basis of the above embodiment, the support 1 is provided with a reserved hole 51 for accommodating the socket 61, so as to more accurately install and fix, reduce installation errors, and ensure that the protective plate 3 is more accurately covered on the socket 61 during movement.

[0045] Further, on the basis of the above embodiment, the protective plate 3 is provided with a reinforcing rib 52 on each side, which improves the structural stability of the protective plate 3, avoids the bending of the protective plate 3 under different temperature conditions or in the process of repeated movement operation, and improves the protection effect on the socket 61.

[0046] Further, on the basis of the above embodiment, the support 1 is provided with at least two groups of mounting holes 53, which maintains the stability of the installation of the support 1.

[0047] Further, on the basis of the above embodiment, the support 1 and the protective plate 3 are each provided with a constraint hole 54, the constraint hole 54 is movably provided with a limiting piece (not shown in the figure), and when the protective plate 3 is located at the first position, the limiting piece can extend into the two constraint holes 54 to limit the movement of the protective plate 3. In the assembly process, the limiting piece is inserted into the constraint holes 54 of the support 1 and the protective plate 3, which limits the movement of the protective plate 3 from the first position to the second position. At this time, the socket 61 is completely exposed, which is more convenient for the plug 62 to be plugged in and out of the socket 61, improves the operation efficiency, and after the plug 62 and the socket 61 on the launch vehicle are equipped, the limiting piece is pulled out, so as to keep the protective plate 3 to play a stable protection role during the flight of the launch vehicle. The limiting piece can be directly made of a long rod structure.

[0048] Further, on the basis of the above embodiment, the protective plate 3 is provided with a heat insulation layer, which improves the protection effect of the protective plate 3 and reduces the heat transfer at the protective plate 3. Specifically, the heat insulation layer can be made of high-temperature heat insulation cloth.

[0049] Based on the same inventive concept, the application also provides a carrier rocket comprising a plurality of cabin sections connected in sequence, a plug-in socket 61 and a plug 62 provided between adjacent cabin sections for plug-in connection, and the protective device as described above, wherein the support 1 is fixed to the cabin section, and in the carrier rocket, the structure, connection relationship, mounting position, etc. of the protective device can refer to the related disclosures of the prior art, and will not be described here.

[0050] It should be understood that the terms first, second, etc. are only used to distinguish the description, and cannot be understood as indicating or implying relative importance. Although the terms first, second, etc. can be used herein to describe various units, these units should not be limited by these terms. These terms are only used to distinguish one unit from another unit. For example, the first unit can be called the second unit, and similarly the second unit can be called the first unit, without departing from the scope of the example embodiments of the application.

[0051] It should be understood that the term "and / or" herein only describes the association relationship of the associated objects, which means that there can be three relationships, for example, A and / or B, which means that there are three cases of A alone, B alone, and A and B together. The term "and" herein describes another association relationship of the associated objects, which means that there can be two relationships, for example, A and B, which means that there are two cases of A alone and A and B together. In addition, the character " / " herein generally indicates that the associated objects before and after are an "or" relationship.

[0052] It should be understood that in the description of the application, the orientation or position relationship indicated by the terms "upper", "vertical", "inner", "outer" and the like is the orientation or position relationship when the disclosed product is usually placed, or the orientation or position relationship commonly understood by those skilled in the art, and is only for the convenience of describing the application and simplifying the description, and does not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the application.

[0053] It should be understood that in the description of the application, unless otherwise explicitly specified and limited, the terms "arrangement", "mounting", "connection" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be directly connected, or indirectly connected through an intermediate medium; it can be the communication between the two elements. For those skilled in the art, the specific meaning of the above terms in the application can be understood according to the specific circumstances.

[0054] The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments of the application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms "comprises", "comprising", "includes" and / or "including" when used herein, specify the presence of stated features, integers, steps, operations, elements, and / or components but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and / or groups thereof.

[0055] In the following description, specific details are set forth to provide a thorough understanding of example embodiments. However, persons having ordinary skill in the art will understand that the example embodiments can be practiced without the specific details. In other instances, well-known processes, structures and techniques have not been shown to avoid obscuring the subject matter of this disclosure.

[0056] The specific embodiments described hereinabove are presented for purposes of numerical and structural examples and not for purposes of limitation. Various modifications to these embodiments can and will be implemented by persons skilled in the art that the general principles set forth herein can be implemented in alternative embodiments as will be apparent to those skilled in the art. Each and every variation that implements the principles of the application exemplified herein includes within its scope the embodiments described hereinabove. Thus, any and all modifications to these embodiments that do not depart from the spirit and scope of the claimed application are to be considered within the scope of the application.

[0057] It is to be understood that the information disclosed in this Background section is for the purpose of providing context for the disclosure and that the information can include ideas not prior art to one of ordinary skill in the art.

Claims

1. A protective device for interstage thermal separation in rockets, characterized in that, It includes: A support for securing a socket on the rocket; A connecting plate, which is fixed to the support; A protective plate is movably connected to the connecting plate, and the protective plate has a first position and a second position. When the protective plate is in the first position, there is space between the protective plate and the socket for plug insertion and removal. When the protective plate is in the second position, the protective plate covers the socket. A driving unit is disposed between the protective plate and the connecting plate, and is used to drive the protective plate to move from the first position to the second position; Each of the support and the protective plate is provided with a constraint hole. A limiting member is movably installed in the constraint hole. When the protective plate is in the first position, the limiting member can extend into the two constraint holes to restrict the movement of the protective plate.

2. The protective device for interstage thermal separation of rockets as described in claim 1, characterized in that: The protective plate is rotatably connected to the connecting plate.

3. The protective device for interstage thermal separation of rockets as described in claim 2, characterized in that: The drive unit includes a rotating shaft and a double torsion spring. The rotating shaft passes through both the connecting plate and the protective plate, so that the protective plate can rotate around the rotating shaft. The double torsion spring is sleeved on the rotating shaft, with one end of the double torsion spring clamped on the connecting plate and the other end pressed against the protective plate.

4. The protective device for interstage thermal separation of rockets as described in claim 3, characterized in that: The end of the shaft is provided with a pin for limiting the axial movement of the shaft.

5. The protective device for interstage thermal separation of rockets as described in claim 1, characterized in that: The support is provided with a reserved hole for accommodating the socket.

6. The protective device for interstage thermal separation of rockets as described in claim 1, characterized in that: Each side of the protective plate is provided with a reinforcing rib.

7. The protective device for interstage thermal separation of rockets as described in claim 1, characterized in that: The support is provided with at least two sets of mounting holes.

8. The protective device for interstage thermal separation of rockets as described in claim 1, characterized in that: The protective panel is equipped with a heat insulation layer.

9. A launch vehicle, characterized in that: It includes multiple compartments connected end to end, with pluggable sockets and plugs between adjacent compartments, and a protective device as described in any one of claims 1-8, wherein the support is fixed to the compartment.

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