CN218296899U - Middle-sized liquid carrier rocket perpendicularity adjusting device - Google Patents

Middle-sized liquid carrier rocket perpendicularity adjusting device Download PDF

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CN218296899U
CN218296899U CN202221730143.4U CN202221730143U CN218296899U CN 218296899 U CN218296899 U CN 218296899U CN 202221730143 U CN202221730143 U CN 202221730143U CN 218296899 U CN218296899 U CN 218296899U
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rocket
adjusting
main body
cylinder
verticality
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韦银利
张彦杰
张瑜
杨俊�
李云龙
王登
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LandSpace Technology Co Ltd
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LandSpace Technology Co Ltd
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Abstract

The utility model discloses a verticality adjusting device for a medium-sized liquid carrier rocket, which comprises a launching platform and an adjusting mechanism, wherein the adjusting mechanism is used for adjusting the verticality of the rocket in cooperation with rocket feet, is positioned on the launching platform, the lower end of the adjusting mechanism is connected with the upper surface of the launching platform, and the upper end of the adjusting mechanism is connected with the lower end of the rocket feet and is used for supporting the rocket feet; the pressure measuring device is positioned at one end of the supporting disc main body, which is far away from the launching platform, and is used for measuring the pressure between the supporting disc main body and the rocket foot; the regulator is positioned in the support disc main body and used for regulating the distance between the support disc main body and the rocket foot so that the rocket perpendicularity meets the preset requirement. Compared with the prior art, the device has the advantages of convenience in operation and cost saving, and can improve the adjusting precision of the rocket perpendicularity and the rocket carrying capacity.

Description

一种中型液体运载火箭垂直度调整装置A verticality adjustment device for a medium-sized liquid launch vehicle

技术领域technical field

本实用新型涉及火箭发射领域,特别涉及一种中型液体运载火箭垂直度调整装置。The utility model relates to the rocket launch field, in particular to a verticality adjustment device for a medium-sized liquid carrier rocket.

背景技术Background technique

液体火箭垂直度调整是调整火箭初始姿态,保证火箭起飞安全和飞行精度的重要措施。液体运载火箭壳体很薄,无法在水平状态下加注后起竖发射,所以其垂直度调整是在火箭竖立到发射平台以后进行的垂直度调整。例如,垂直度的调整可以分为加注前空载状态垂直度调整和加注后带载状态垂直度调整两种。The vertical adjustment of liquid rocket is an important measure to adjust the initial attitude of the rocket and ensure the safety of rocket take-off and flight accuracy. The shell of the liquid launch vehicle is very thin, and it cannot be launched vertically after filling in a horizontal state, so its verticality adjustment is performed after the rocket is erected on the launch platform. For example, the verticality adjustment can be divided into verticality adjustment in the no-load state before filling and verticality adjustment in the loaded state after filling.

在我国现有的运载火箭发射装置调平工作流程中,普遍采用地面一套水平测量仪器,箭上尾端和仪器舱各一套水平测量仪的方式。这种方式可以可靠地完成发射装置调平要求,也基本可以满足垂直度的高精度要求。但是却存在三个问题:一是箭/弹地设备数量多,实现和操作过程复杂;二是增加了箭上设备,导致火箭运载能力减少;三是火箭成本大幅增加,市场竞争力下降。随着民营航天技术的发展,市场对火箭发射流程的简化和单枚火箭的发射低成本、免维护、快速反应提出了新的要求。In the current leveling workflow of launch vehicle launchers in our country, a set of leveling instruments on the ground, a set of leveling instruments on the tail end of the arrow and a set of leveling instruments in the instrument cabin are generally used. This method can reliably meet the leveling requirements of the launching device, and can basically meet the high-precision requirements of verticality. However, there are three problems: one is that the number of arrows/ground launch equipment is large, and the implementation and operation process is complicated; the second is that the increase of arrow equipment reduces the rocket’s carrying capacity; the third is that the cost of the rocket has increased significantly and the market competitiveness has declined. With the development of private aerospace technology, the market has put forward new requirements for the simplification of the rocket launch process and the low cost, maintenance-free, and rapid response of a single rocket launch.

因此,亟需提供一种液体火箭垂直度调整装置,该装置具有便于操作和节约成本的优点,可以提高调节精度以及火箭运载能力。Therefore, there is an urgent need to provide a liquid rocket verticality adjustment device, which has the advantages of easy operation and cost saving, and can improve adjustment accuracy and rocket carrying capacity.

发明内容Contents of the invention

本发明的目的是提供一种中型液体运载火箭垂直度调整装置,该装置具有便于操作和节约成本的优点,可以提高调节精度以及火箭运载能力。The object of the present invention is to provide a verticality adjustment device for a medium-sized liquid carrier rocket, which has the advantages of easy operation and cost saving, and can improve the adjustment accuracy and rocket carrying capacity.

为实现上述目的,本发明提供如下技术方案:一种中型液体运载火箭垂直度调整装置,包含发射平台和用于与火箭箭脚配合调整火箭垂直度的调节机构,所述调节机构位于所述发射平台上,且所述调节机构的下端与所述发射平台的上表面连接,上端与所述火箭箭脚的下端连接且用于支撑所述火箭箭脚;In order to achieve the above object, the present invention provides the following technical solutions: a verticality adjustment device for a medium-sized liquid carrier rocket, comprising a launch platform and an adjustment mechanism for adjusting the verticality of the rocket in cooperation with the arrow legs of the rocket, the adjustment mechanism is located at the launch platform, and the lower end of the adjustment mechanism is connected to the upper surface of the launch platform, and the upper end is connected to the lower end of the rocket foot and used to support the rocket foot;

其中,所述调节机构包含支撑盘主体,测压装置和调节器,所述测压装置位于所述支撑盘主体远离所述发射平台的一端且用于测量所述支撑盘主体与所述火箭箭脚之间的压力;所述调节器位于所述支撑盘主体的内部,用于调节支撑盘主体与所述火箭箭脚之间的距离以使火箭垂直度满足预设要求。Wherein, the adjustment mechanism includes a main body of the support plate, a pressure measuring device and a regulator. The pressure measuring device is located at the end of the main body of the support plate away from the launch platform and is used to measure the distance between the main body of the support plate and the rocket. The pressure between the feet; the regulator is located inside the main body of the support plate, and is used to adjust the distance between the main body of the support plate and the arrow foot of the rocket so that the verticality of the rocket meets the preset requirements.

进一步的,所述支撑盘主体包含壳体和头部法兰,所述壳体为两端相通内部设有空间的结构,所述壳体的下端与所述发射平台的上表面焊接固定,所述头部法兰相对于所述壳体可上下移动。Further, the main body of the support plate includes a shell and a head flange. The shell is a structure with two ends connected to each other and a space is provided inside. The lower end of the shell is welded and fixed to the upper surface of the launching platform. The head flange can move up and down relative to the housing.

进一步的,沿所述支撑盘主体的轴向方向,所述头部法兰依次包含直径不同的第一柱体和第二柱体,所述第一柱体的直径大于所述第二柱体的直径,从而所述第一柱体向所述第二柱体的过渡部位形成限位台,且所述第一柱体位于靠近所述火箭箭脚一侧,所述第二柱体位于靠近所述壳体一侧。Further, along the axial direction of the main body of the support disc, the head flange successively includes a first cylinder and a second cylinder with different diameters, the diameter of the first cylinder is larger than that of the second cylinder diameter, so that the transition from the first cylinder to the second cylinder forms a limit platform, and the first cylinder is located on the side close to the arrow foot of the rocket, and the second cylinder is located on the side close to the arrow foot of the rocket. side of the housing.

进一步的,所述第一柱体位于所述壳体的外侧,所述第二柱体位于所述壳体的内部且可沿所述壳体内壁移动,所述限位台的下端面与所述壳体的上端端面紧贴。Further, the first cylinder is located outside the housing, the second cylinder is located inside the housing and can move along the inner wall of the housing, and the lower end surface of the limiting platform is in contact with the housing. The upper end face of the housing is in close contact.

进一步的,所述第一柱体和所述第二柱体一体成型设计。Further, the first column and the second column are integrally formed.

进一步的,所述第一柱体远离所述第二柱体的一端设有用于固定所述测压装置的凹槽,所述测压装置为压力传感器。Further, the end of the first cylinder away from the second cylinder is provided with a groove for fixing the pressure measuring device, and the pressure measuring device is a pressure sensor.

进一步的,所述调节器包括丝杠结构和驱动装置;所述驱动装置的输出端与所述丝杠结构的输入连接,所述丝杠结构的输出端与所述头部法兰抵接,所述丝杠结构用于在所述驱动装置带动下,带动所述头部法兰上下移动。Further, the regulator includes a screw structure and a driving device; the output end of the driving device is connected to the input of the screw structure, and the output end of the screw structure abuts against the head flange, The lead screw structure is used to drive the head flange to move up and down under the driving of the driving device.

进一步的,所述驱动装置为液压马达,且所述液压马达通过可编程控制器控制。Further, the driving device is a hydraulic motor, and the hydraulic motor is controlled by a programmable controller.

进一步的,所述调节机构沿所述发射平台的上表面周向均匀排布。Further, the adjustment mechanisms are uniformly arranged circumferentially along the upper surface of the launching platform.

进一步的,所述调节机构的数量为A个,其中,A≥4。Further, the number of the adjustment mechanism is A, wherein, A≥4.

与现有技术相比,本发明的有益效果是:本申请的火箭垂直度调整过程,通过测压装置测量支撑盘主体与火箭箭脚之间的压力,根据压力的数值通过调节器调节支撑盘主体与火箭箭脚之间的距离以使支撑盘主体与火箭箭脚之间的压力相等。Compared with the prior art, the beneficial effect of the present invention is: the rocket verticality adjustment process of the present application measures the pressure between the main body of the support plate and the arrow foot of the rocket through the pressure measuring device, and adjusts the support plate through the regulator according to the value of the pressure The distance between the main body and the rocket foot to equalize the pressure between the support plate body and the rocket foot.

此外,本申请的调整装置,可以通过对支撑盘主体进行多次调节,以使得火箭发动机机架基准面与支撑盘主体初始面(多个支撑盘主体远离发射平台端形成的平面)平行。另外,本申请可以在不增加箭上测量装置的基础上,通过对支撑盘主体进行多次调节,对火箭发动机机架基准面与支撑盘主体初始面平行,以快速实现对火箭垂直度的精确调节,为后续调节打下基础。该装置具有便于操作和节约成本的优点,可以提高火箭垂直度的调节精度以及火箭运载能力。In addition, the adjustment device of the present application can adjust the main body of the support plate multiple times so that the base plane of the rocket engine frame is parallel to the initial surface of the main body of the support plate (the plane formed by the ends of the support plate bodies away from the launch platform). In addition, on the basis of not increasing the measurement device on the arrow, the application can adjust the main body of the support plate multiple times, and make the reference plane of the rocket engine frame parallel to the initial surface of the main body of the support plate, so as to quickly realize the accurate verticality of the rocket. Adjustment lays the foundation for subsequent adjustments. The device has the advantages of convenient operation and cost saving, and can improve the adjustment accuracy of the verticality of the rocket and the carrying capacity of the rocket.

附图说明Description of drawings

图1为本发明液体火箭垂直度调整装置的结构示意图;Fig. 1 is the structural representation of liquid rocket verticality adjusting device of the present invention;

图2为本发明支撑盘主体和调节器的结构示意图。Fig. 2 is a structural schematic diagram of the main body of the support plate and the adjuster of the present invention.

附图标记说明:Explanation of reference signs:

1发射平台 2支撑盘主体1 launch platform 2 support plate main body

3测压装置 4调节器3 Pressure measuring device 4 Regulator

5壳体 6头部法兰5 shell 6 head flange

7火箭箭脚7 Rocket Knuckles

具体实施方式detailed description

为使本发明实施例的目的、技术方案和优点更加清楚明白,下面将以附图及详细叙述清楚说明本发明所揭示内容的精神,任何所属技术领域技术人员在了解本发明内容的实施例后,当可由本发明内容所教示的技术,加以改变及修饰,其并不脱离本发明内容的精神与范围。In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the spirit of the disclosure of the present invention will be clearly described below with the accompanying drawings and detailed descriptions. Any person skilled in the art will understand the embodiments of the present invention. , when it can be changed and modified by the technology taught in the content of the present invention, it does not depart from the spirit and scope of the content of the present invention.

本发明的示意性实施例及其说明用于解释本发明,但并不作为对本发明的限定。另外,在附图及实施方式中所使用相同或类似标号的元件/构件是用来代表相同或类似部分。The exemplary embodiments and descriptions of the present invention are used to explain the present invention, but not to limit the present invention. In addition, elements/members with the same or similar numbers used in the drawings and embodiments are used to represent the same or similar parts.

关于本文中所使用的“第一”、“第二”、…等,并非特别指称次序或顺位的意思,也非用以限定本发明,其仅为了区别以相同技术用语描述的元件或操作。As used herein, "first", "second", ... etc. do not refer to a particular sequence or order, nor are they used to limit the present invention, but are only used to distinguish elements or operations described with the same technical terms .

关于本文中所使用的方向用语,例如:上、下、左、右、前或后等,仅是参考附图的方向。因此,使用的方向用语是用来说明并非用来限制本创作。Regarding the directional terms used herein, such as: up, down, left, right, front or rear, etc., only refer to the directions of the drawings. Accordingly, the directional terms used are for illustration and not for limitation of the present invention.

关于本文中所使用的“包含”、“包括”、“具有”、“含有”等等,均为开放性的用语,即意指包含但不限于。As used herein, "comprising", "comprising", "having", "comprising" and so on are all open terms, meaning including but not limited to.

关于本文中所使用的“及/或”,包括所述事物的任一或全部组合。As used herein, "and/or" includes any or all combinations of the stated things.

关于本文中所使用的用语“大致”、“约”等,用以修饰任何可以微变化的数量或误差,但这些微变化或误差并不会改变其本质。一般而言,此类用语所修饰的微变化或误差的范围在部分实施例中可为20%,在部分实施例中可为10%,在部分实施例中可为5%或是其他数值。本领域技术人员应当了解,前述提及的数值可依实际需求而调整,并不以此为限。The terms "approximately" and "about" used herein are used to modify any quantity or error that may vary slightly, but these slight changes or errors will not change its essence. Generally speaking, the range of slight changes or errors modified by such terms may be 20% in some embodiments, 10% in some embodiments, 5% in some embodiments or other numerical values. Those skilled in the art should understand that the aforementioned values can be adjusted according to actual needs, and are not limited thereto.

某些用以描述本申请的用词将于下或在此说明书的别处讨论,以提供本领域技术人员在有关本申请的描述上额外的引导。Certain terms used to describe the present application are discussed below or elsewhere in this specification to provide those skilled in the art with additional guidance in describing the present application.

本发明的实施例提供了一种中型液体运载火箭垂直度调整装置。如图1和图2所示,该装置包含发射平台1和用于与火箭箭脚7配合调整火箭垂直度的调节机构。调节机构位于所述发射平台1上,且调节机构的下端与发射平台1的上表面连接,上端与火箭箭脚7的下端连接且用于支撑火箭箭脚7。调节机构包含支撑盘主体2,测压装置3和调节器4。测压装置3位于支撑盘主体2远离发射平台1的一端且用于测量支撑盘主体2与火箭箭脚7之间的压力。调节器4位于支撑盘主体2的内部,用于调节支撑盘主体2与火箭箭脚7之间的距离以使火箭垂直度满足预设要求。An embodiment of the invention provides a verticality adjustment device for a medium-sized liquid launch vehicle. As shown in Figures 1 and 2, the device includes a launch platform 1 and an adjustment mechanism for adjusting the verticality of the rocket in cooperation with the arrow foot 7 of the rocket. The adjustment mechanism is located on the launch platform 1 , and the lower end of the adjustment mechanism is connected to the upper surface of the launch platform 1 , and the upper end is connected to the lower end of the arrow foot 7 of the rocket and is used to support the arrow foot 7 of the rocket. The adjustment mechanism includes a main body 2 of the support disc, a pressure measuring device 3 and a regulator 4 . The pressure measuring device 3 is located at the end of the support plate main body 2 away from the launch platform 1 and is used to measure the pressure between the support plate main body 2 and the arrow foot 7 of the rocket. The adjuster 4 is located inside the main body 2 of the support plate, and is used for adjusting the distance between the main body 2 of the support plate and the arrow foot 7 of the rocket so that the verticality of the rocket meets the preset requirements.

本申请的中型液体运载火箭垂直度调整装置,通过测压装置测量支撑盘主体2与火箭箭脚7之间的压力,根据压力的数值通过调节器4调节支撑盘主体2与火箭箭脚7之间的距离以使支撑盘主体2与火箭箭脚7之间的压力相等,且通过对支撑盘主体2进行多次调节,可以使火箭发动机机架基准面与支撑盘主体2初始面(多个支撑盘主体远离发射平台端形成的平面)平行。本申请可以在不增加箭上测量装置的基础上,通过对支撑盘主体2进行多次调节,以快速实现对火箭垂直度的精确调节,为后续调节打下基础。该装置具有便于操作和节约成本的优点,并能够提高调节精度以及火箭运载能力。The verticality adjustment device of the medium-sized liquid carrier rocket of the present application measures the pressure between the main body 2 of the support plate and the arrow foot 7 of the rocket through the pressure measuring device, and adjusts the distance between the main body 2 of the support plate and the arrow foot 7 of the rocket through the regulator 4 according to the value of the pressure. The distance between so that the pressure between the support plate main body 2 and the arrow foot 7 of the rocket is equal, and by repeatedly adjusting the support plate main body 2, the rocket engine frame reference plane and the support plate main body 2 initial surfaces (multiple The main body of the support plate is parallel to the plane formed by the end of the launching platform). In this application, on the basis of not increasing the measurement device on the arrow, the main body 2 of the support plate can be adjusted multiple times to quickly realize the precise adjustment of the verticality of the rocket and lay the foundation for subsequent adjustments. The device has the advantages of convenient operation and cost saving, and can improve adjustment accuracy and rocket carrying capacity.

需要说明的是,为了方便调节支撑盘主体2,例如,支撑盘主体2包含壳体5和头部法兰6,其中壳体5为两端相通内部设有空间的结构。为了使得壳体5被固定牢固,例如,壳体5的下端与发射平台1上表面焊接固定。另外,为了便于头部法兰6沿壳体5内壁移动,例如,壳体5的上端用于与头部法兰6的一端配合对头部法兰6的向下移动进行限位,头部法兰6的另一端可沿壳体5内壁上下移动。It should be noted that, for the convenience of adjusting the main body 2 of the support plate, for example, the main body 2 of the support plate includes a shell 5 and a head flange 6 , wherein the shell 5 is a structure in which both ends communicate with each other and a space is provided inside. In order to make the casing 5 be fixed firmly, for example, the lower end of the casing 5 is welded and fixed to the upper surface of the launching platform 1 . In addition, in order to facilitate the movement of the head flange 6 along the inner wall of the housing 5, for example, the upper end of the housing 5 is used to cooperate with one end of the head flange 6 to limit the downward movement of the head flange 6. The other end of the flange 6 can move up and down along the inner wall of the housing 5 .

值得一提的是,为了方便固定头部法兰6,例如,沿支撑盘主体2的轴向方向,头部法兰6依次包含直径不同的第一柱体和第二柱体。其中第一柱体的直径大于第二柱体,从而第一柱体向第二柱体的过渡部位形成限位台。第一柱体位于靠近火箭箭脚7一侧,用于抵接火箭箭脚,第二柱体位于靠近壳体5的内侧,用于沿壳体内侧运动。具体地,第一柱体位于壳体5的外侧,第二柱体位于壳体5的内部且可沿壳体5内壁移动,限位台的下端面用于与壳体5的上端端面抵接,以限制头部法兰6向下的运动极限位置。It is worth mentioning that, in order to fix the head flange 6 conveniently, for example, along the axial direction of the main body 2 of the support plate, the head flange 6 sequentially includes a first cylinder and a second cylinder with different diameters. Wherein the diameter of the first cylinder is larger than that of the second cylinder, so that the transition from the first cylinder to the second cylinder forms a limiting platform. The first cylinder is located on the side close to the arrow foot 7 of the rocket, and is used to abut the arrow foot of the rocket, and the second cylinder is located on the inner side close to the shell 5, and is used to move along the inner side of the shell. Specifically, the first cylinder is located outside the housing 5, the second cylinder is located inside the housing 5 and can move along the inner wall of the housing 5, and the lower end surface of the limiting platform is used to abut against the upper end surface of the housing 5 , to limit the limit position of the downward movement of the head flange 6 .

此外,为了使得第一柱体和第二柱体连接紧密,固定牢固,例如,第一柱体和第二柱体采取一体成型设计。In addition, in order to make the first cylinder and the second cylinder tightly connected and fixed firmly, for example, the first cylinder and the second cylinder adopt an integral molding design.

需要指出的是,为了方便固定测压装置3,避免测压装置3在第一柱体表面发生位移移动,第一柱体远离第二柱体的一端设有用于固定测压装置的凹槽(凹槽与测压装置匹配设置)。为了方便测压装置3测量压力,例如,测压装置3为压力传感器。It should be pointed out that, in order to facilitate the fixing of the pressure measuring device 3 and avoid the displacement of the pressure measuring device 3 on the surface of the first cylinder, the end of the first cylinder away from the second cylinder is provided with a groove for fixing the pressure measuring device ( The groove is set to match the pressure measuring device). For the convenience of the pressure measuring device 3 to measure pressure, for example, the pressure measuring device 3 is a pressure sensor.

特别需要注意的是,为了便于调节器的调节(上下移动),例如,调节器4包括丝杠结构和驱动装置。其中,驱动装置的输出端与丝杠结构的输入连接,具体的,驱动装置带动丝杠结构移动时,使得丝杠结构的输出端与头部法兰6(第二柱体远离第一柱体一端的端面)接触,进而带动头部法兰6上下移动。It should be particularly noted that, in order to facilitate the adjustment (up and down movement) of the regulator, for example, the regulator 4 includes a lead screw structure and a driving device. Wherein, the output end of the driving device is connected with the input of the lead screw structure. Specifically, when the driving device drives the lead screw structure to move, the output end of the lead screw structure is connected to the head flange 6 (the second cylinder is far away from the first cylinder) One end face) contact, and then drive the head flange 6 to move up and down.

在本实施方式中,为了保证动力充足,例如,驱动装置为液压马达。为了便于控制所述液压马达的输出,例如,液压马达通过可编程控制器控制。In this embodiment, in order to ensure sufficient power, for example, the driving device is a hydraulic motor. In order to control the output of the hydraulic motor, for example, the hydraulic motor is controlled by a programmable controller.

另外,为了方便调节机构对火箭箭脚7的支撑,例如,调节机构沿发射平台的上表面周向均匀排布。经过大量的实验仿真,当调节机构的数量为A个,且满足A≥4时,调节机构对火箭箭脚7的支撑更加牢固,可以更好地避免火箭发生倾斜,有利于对火箭垂直度进行精确调节。In addition, in order to facilitate the adjustment mechanism to support the arrow foot 7 of the rocket, for example, the adjustment mechanisms are evenly arranged circumferentially along the upper surface of the launch platform. After a large number of experimental simulations, when the number of adjustment mechanisms is A and satisfies A≥4, the support of the adjustment mechanism to the arrow foot 7 of the rocket will be more firm, which can better prevent the rocket from tilting, and is conducive to improving the verticality of the rocket. Fine adjustment.

以上所述仅为本发明示意性的具体实施方式,在不脱离本发明的构思和原则的前提下,任何本领域的技术人员所做出的等同变化与修改,均应属于本发明保护的范围。The above are only illustrative specific implementations of the present invention. Under the premise of not departing from the concept and principle of the present invention, any equivalent changes and modifications made by those skilled in the art shall fall within the protection scope of the present invention. .

Claims (10)

1. The device for adjusting the verticality of the medium-sized liquid carrier rocket is characterized by comprising a launching platform and an adjusting mechanism for adjusting the verticality of the rocket in a manner of being matched with rocket feet, wherein the adjusting mechanism is positioned on the launching platform, the lower end of the adjusting mechanism is connected with the upper surface of the launching platform, and the upper end of the adjusting mechanism is connected with the lower ends of the rocket feet and is used for supporting the rocket feet;
the pressure measuring device is positioned at one end of the supporting disc main body, which is far away from the launching platform, and is used for measuring the pressure between the supporting disc main body and the rocket foot; the regulator is positioned in the support disc main body and used for regulating the distance between the support disc main body and the rocket foot so that the rocket perpendicularity meets the preset requirement.
2. The perpendicularity adjusting device of the medium-sized liquid carrier rocket according to claim 1, wherein the supporting plate main body comprises a housing and a head flange, and the housing is a structure with two communicated ends and a space inside; the lower end of the shell is fixedly welded with the upper surface of the launching platform, and the head flange can move up and down relative to the shell.
3. The apparatus for adjusting the verticality of a medium-sized liquid carrier rocket according to claim 2, wherein the head flange comprises a first column and a second column with different diameters in sequence along the axial direction of the support disc main body; the diameter of the first cylinder is larger than that of the second cylinder, so that a limiting table is formed at the transition part of the first cylinder to the second cylinder, the first cylinder is positioned at one side close to the rocket foot, and the second cylinder is positioned at one side close to the shell.
4. The mid-sized liquid carrier rocket perpendicularity adjusting apparatus according to claim 3, wherein the first column is located outside the housing in the axial direction, and the second column is located inside the housing and is movable up and down along the inner wall of the housing.
5. The apparatus of claim 3, wherein the first and second cylinders are integrally formed.
6. The device for adjusting the verticality of a medium-sized liquid carrier rocket according to claim 3, wherein the end of the first column body, which is far away from the second column body, is provided with a groove for fixing the pressure measuring device, and the pressure measuring device is a pressure sensor.
7. The mid-sized liquid carrier rocket perpendicularity adjusting apparatus according to claim 2, wherein the adjuster includes a lead screw structure and a driving device; the output end of the driving device is connected with the input end of the lead screw structure, the output end of the lead screw structure is abutted to the head flange, and the lead screw structure is used for driving the head flange to move up and down under the driving of the driving device.
8. The apparatus of claim 7, wherein the driving device is a hydraulic motor, and the hydraulic motor is controlled by a programmable controller.
9. The apparatus of claim 1, wherein the adjusting mechanisms are arranged uniformly along the circumference of the upper surface of the launching platform.
10. The verticality adjusting device for the medium-sized liquid carrier rocket according to claim 9, wherein the number of the adjusting mechanisms is A, and A is greater than or equal to 4.
CN202221730143.4U 2022-07-05 2022-07-05 Middle-sized liquid carrier rocket perpendicularity adjusting device Active CN218296899U (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN116255867A (en) * 2023-03-27 2023-06-13 航天科工火箭技术有限公司 Supporting frame

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN116255867A (en) * 2023-03-27 2023-06-13 航天科工火箭技术有限公司 Supporting frame

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