A spacecraft center of mass measurement device

Abstract

The application discloses a spacecraft center of mass measuring device, comprising a connecting frame, a plurality of first connecting points are arranged on the lower side of the connecting frame, and the first connecting points are located in a first plane; a connecting assembly is arranged on the upper portion of the connecting frame, the lower end of the connecting assembly is rigidly connected with the upper side of the connecting frame, and the upper end of the connecting assembly is used for being hoisted; a plurality of measuring assemblies are arranged on the lower portion of the connecting frame, the upper end of each measuring assembly is connected with each first connecting point, the lower end of each measuring assembly is connected with each hoisting point of a spacecraft to be measured, and the measuring assemblies are provided with controllable telescopic connecting pieces and tension testers between the two ends of the measuring assemblies. The spacecraft center of mass measuring device is convenient for measuring the position of the center of mass of the spacecraft.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft equipment manufacturing, and in particular to a spacecraft center of mass measuring device. BACKGROUND

[0002] In order to ensure accurate planning of the operating trajectory of a spacecraft such as a rocket to achieve a given launch task, the center of mass position of the spacecraft needs to be measured in advance. Existing spacecraft center of mass position measuring devices are generally of the placement type, i.e. the spacecraft is placed on the center of mass measuring device and the precise position of the center of mass of the spacecraft relative to the spacecraft is determined after the pressure received at the corresponding positions is measured by switching the attitude multiple times. However, due to the high degree of complexity of the shape of the spacecraft, the external shape of some spacecrafts determines that they are not suitable for being placed on the corresponding center of mass measuring device, or the external shape of the spacecraft will be damaged after being placed, which will affect the launch of the spacecraft. If the spacecraft is divided into segments and placed on the center of mass position measuring device, the center of mass of each segment needs to be calculated, and due to the change in the position of the internal equipment during the splicing of the segments, there will be a large gap between the calculated center of mass position and the actual center of mass position. Therefore, designing a center of mass measuring device that is convenient for measuring the center of mass position of various spacecrafts has become a problem to be solved in the field. SUMMARY

[0003] In view of the above-mentioned defects or shortcomings in the prior art, it is desirable to provide a spacecraft center of mass measuring device that is convenient for measuring the center of mass position.

[0004] The specific technical solutions are as follows:

[0005] The present application provides a spacecraft center of mass measuring device, comprising:

[0006] A connecting frame, wherein the lower side of the connecting frame is provided with a plurality of first connecting points, and the plurality of first connecting points are located in a first plane;

[0007] A connecting assembly, wherein the connecting assembly is located at the upper part of the connecting frame, the lower end of the connecting assembly is rigidly connected to the upper side of the connecting frame, and the upper end of the connecting assembly is used to be lifted;

[0008] A plurality of measuring assemblies, wherein the plurality of measuring assemblies are also provided, and the plurality of measuring assemblies are located at the lower part of the connecting frame, the upper end of each measuring assembly is connected to a corresponding connecting point, and the lower end of each measuring assembly is connected to a corresponding lifting point of the spacecraft to be measured, and the measuring assemblies are provided with controllable telescopic connecting pieces and tension testers between the two ends of the measuring assemblies.

[0009] Optionally, the measuring assembly further comprises:

[0010] A rotating connecting piece, wherein one end of the rotating connecting piece is rotatably connected to a corresponding first connecting point about a first axis, and the first axis is perpendicular to the first plane.

[0011] a pitch connecting piece, which is hinged between the other end of the rotating connecting piece and one end of the telescopic connecting piece.

[0012] Optionally, the measuring assembly further comprises a connecting rod, one end of the connecting rod being connected to the other end of the telescopic connecting piece, and the other end of the connecting rod having an outer shape corresponding to the mounting structure at the lifting point on the spacecraft to be measured, for detachable connection therewith.

[0013] Optionally, the telescopic connecting piece is an electric cylinder.

[0014] Optionally, the connecting assembly comprises:

[0015] a fixing piece, which is arranged on the upper side of the connecting frame;

[0016] a lifting hook, which is used for hoisting the spacecraft center-of-mass measuring device to a high place;

[0017] a lifting rod, which is arranged between the fixing piece and the lifting hook.

[0018] Optionally, the upper side of the connecting frame is provided with a plurality of second connecting points corresponding to the first connecting points respectively, and the fixing piece also has a plurality of second connecting points, which are connected to the second connecting points respectively.

[0019] Optionally, the lifting rod comprises a first lifting rod, a second lifting rod and an adjusting tube, one end of the first lifting rod being connected to the fixing piece, one end of the second lifting rod being connected to the lifting hook, and the other end of the first lifting rod and the other end of the second lifting rod being threadedly connected to two ends of the adjusting tube respectively.

[0020] The application has the following beneficial effects:

[0021] The spacecraft such as rockets are large in size and complex in structure, and therefore are often assembled by different cabin sections and then hoisted and spliced section by section. Therefore, a large number of lifting points are left on various spacecrafts. In the embodiment, the measuring assemblies can be connected with the lifting points on the spacecraft according to the structure in the application, and the center of mass measuring device is hung at a higher position through the connecting assemblies, the extension length of the telescopic connecting piece is controlled to ensure that the first plane is parallel to the horizontal plane, and then the accurate position of the center of mass of the spacecraft relative to the spacecraft can be obtained by obtaining the measurement data on each tension tester and through the balance formula known in the art. The connecting frame can ensure that a sufficient number of measuring assemblies are arranged below to improve the measurement accuracy. In this way, the spacecraft is always not in contact with the ground during the center of mass measurement, so that the center of mass measurement operation of the spacecraft with different external structures can be applied. In addition, the spacecraft cabin sections do not need to be disassembled and assembled, so that the convenience and accuracy of the center of mass measurement of the spacecraft are improved. BRIEF DESCRIPTION OF DRAWINGS

[0022] Other features, objects, and advantages of the application will become more apparent from the following detailed description of non-limiting embodiments made with reference to the drawings:

[0023] Figure 1 The overall structure schematic diagram of the spacecraft center of mass measuring device provided by the embodiment of the application is shown in the figure.

[0024] Figure 2 The schematic diagram of the measuring assembly in the embodiment is shown in the figure. Figure 1

[0025] Figure reference: 1, connecting frame; 31, telescopic connecting piece; 32, tension tester; 33, rotating connecting piece; 34, pitching connecting piece; 35, connecting rod; 21, fixing piece; 22, lifting hook; 23, lifting rod; 231, first lifting rod; 232, second lifting rod; 233, adjusting tube. DETAILED DESCRIPTION

[0026] The application will be further described in detail below with reference to the drawings and embodiments. It can be understood that the specific embodiments described herein are only used to explain the related application, but not to limit the application. In addition, it should be noted that only the parts related to the application are shown in the drawings for the convenience of description.

[0027] It should be noted that the embodiments in the application and the features in the embodiments can be combined with each other without conflict. The application will be described in detail below with reference to the drawings and embodiments.

[0028] Please refer to Figure 1 The spacecraft center of mass measuring device provided by the embodiment comprises: ​

[0029] A connecting frame 1, which is provided with a plurality of first connecting points on the lower side, and the first connecting points are located in a first plane;

[0030] A connecting assembly, which is located on the upper part of the connecting frame 1, and the lower end is rigidly connected with the upper side of the connecting frame 1, and the upper end is used to be lifted;

[0031] A plurality of measuring assemblies, which are also located on the lower part of the connecting frame 1, and the upper end is connected to each first connecting point, and the lower end is connected to each lifting point of the spacecraft to be measured, and the two ends of the measuring assembly are provided with a controlled telescopic connecting piece 31 and a tension tester 32.

[0032] The spacecraft such as rockets are large in size and complex in structure, so different cabin sections are often assembled and then hoisted and spliced section by section. Therefore, there are many lifting points on various spacecrafts. In the embodiment, the measuring assembly can be connected with the lifting points on the spacecraft according to the structure in the application, and the center of mass measuring device can be hung at a higher position through the connecting assembly, the telescopic length of the telescopic connecting piece 31 is controlled to ensure that the first plane is parallel to the horizontal plane, and then the measurement data on each tension tester 32 is obtained, so that the accurate position of the center of mass of the spacecraft relative to the spacecraft is obtained. In this process, any position on the spacecraft can be selected as the coordinate origin, and the center of mass coordinate value is finally obtained according to the mass, center of mass and mass deviation measurement principle known in the art. The connecting frame 1 can ensure that a sufficient number of measuring assemblies are arranged below to improve the measurement accuracy. In this regard, the measurement accuracy of the center of mass of the spacecraft can be improved by increasing the density of the measuring assemblies, and corresponding setting density values can be set for different spacecrafts. In this way, the spacecraft is always not in contact with the ground during the center of mass measurement process, so that the center of mass measurement operation of the spacecraft with different shapes and structures can be applied. The convenience of the center of mass measurement of the spacecraft is improved.

[0033] In the preferred embodiment for improving the convenience of the center of mass position measurement process, the measuring assembly further comprises:

[0034] A rotating connecting piece 33, one end of which is rotatably connected to the corresponding first connecting point around a first axis, and the first axis is perpendicular to the first plane;

[0035] A pitch connecting piece 34, which is hinged between the other end of the rotating connecting piece and one end of the telescopic connecting piece 31.

[0036] As Figure 2As shown in the figure, since the rotation connecting piece 33 and the pitching connecting piece 34 are arranged on one end of the measurement assembly close to the connecting frame 1, the other end of the measurement assembly far from the connecting frame 1 can be adjusted according to the shape of the spacecraft and the distribution of the hanging points, thus improving the convenience of the center of mass measuring device in practical application.

[0037] Here, the rotation connecting piece 33 and the pitching connecting piece 34 can be replaced by a spherical pair structure or other movable connecting structure that can adjust the position and orientation of the other end of the measurement assembly, which is not specifically limited here.

[0038] In a preferred embodiment for further improving the convenience of the center of mass position measuring process, the measurement assembly further comprises a connecting rod 35, one end of the connecting rod 35 is connected to the other end of the telescopic connecting piece 31, and the other end of the connecting rod 35 has a shape corresponding to the mounting structure at the hanging point of the spacecraft to be measured, for detachable connection therewith.

[0039] In this embodiment, the connecting rod 35 is arranged on the end of the measurement assembly connected to the spacecraft to be measured, and the other end of the connecting rod 35 has a shape corresponding to the mounting structure at the hanging point of the spacecraft to be measured, for detachable connection therewith, so as to facilitate the fixation of the spacecraft to be measured on the center of mass measuring device and the removal after the measurement is completed, further improving the convenience of the center of mass position measuring process.

[0040] In a preferred embodiment of the telescopic connecting piece 31, the telescopic connecting piece 31 is an electric cylinder.

[0041] Since the telescopic length of the electric cylinder can be accurately controlled, it is used as a preferred embodiment of the telescopic connecting piece 31 in this embodiment.

[0042] In a preferred embodiment of the connecting assembly, the connecting assembly comprises:

[0043] A fixing piece 21 is arranged on the upper side of the connecting frame 1.

[0044] A hook 22 is used to hang the spacecraft center of mass measuring device at a high place.

[0045] A hanging rod 23 is arranged between the fixing piece 21 and the hook 22.

[0046] The hook 22 is used to hoist the spacecraft center of mass measuring device to a high position, so that after the center of mass measuring device is hoisted to the spacecraft to be measured, the angle between the first plane and the horizontal plane can be adjusted by adjusting the length of the telescopic connecting piece 31, wherein the connection between the fixing piece 21 and the boom 23 and the connection between the boom 23 and the hook 22 can be fixed or detachable.

[0047] In the preferred embodiment for improving the accuracy of the center of mass measurement, the upper side of the connecting frame 1 is provided with a plurality of second connecting points corresponding to the first connecting points respectively, and the fixing piece 21 also has a plurality of second connecting points and is connected to the second connecting points respectively.

[0048] In this embodiment, since the upper side of the connecting frame 1 is also provided with the second connecting points corresponding to the first connecting points, after the spacecraft to be measured is hoisted to the center of mass measuring device, the lower side of the hook 22 can provide sufficient pulling force for the corresponding measuring assembly through the boom 23, so that the measurement data on the tension tester 32 is more accurate after the first plane is leveled, and thus the measurement position of the center of mass of the spacecraft is more accurate.

[0049] In the preferred embodiment for improving the convenience of use of the center of mass measuring device, the boom 23 includes a first boom 231, a second boom 232, and an adjusting pipe 233, one end of the first boom 231 is connected to the fixing piece 21, one end of the second boom 232 is connected to the hook 22, and the other end of the first boom 231 and the other end of the second boom 232 are respectively screwed to the two ends of the adjusting pipe 233.

[0050] In this embodiment, by the cooperation of the first boom 231 and the adjusting pipe 233 and the second boom 232 and the adjusting pipe 233, the overall length of the boom 23 can be adjusted, and the assembly of the connecting assembly is also facilitated, so that the same batch of booms 23 can be applied to connecting frames 1 of different sizes to measure different spacecrafts. Therefore, the convenience of use of the center of mass measuring device is improved.

[0051] The above description is only the preferred embodiment of the present application and the explanation of the applied technical principles. Those skilled in the art should understand that the scope of the invention involved in the present application is not limited to the technical solutions formed by the specific combination of the above technical features, and should also cover other technical solutions formed by any combination of the above technical features or their equivalent features without departing from the inventive concept. For example, the above features can be replaced with the technical features disclosed in the present application (but not limited to) having similar functions to form technical solutions.

Claims

1. A spacecraft center of mass measurement device, characterized in that, include: A connecting frame (1) is provided on the lower side of the connecting frame (1) with a plurality of first connecting points, all of which are located in a first plane; A connecting component is located on the upper part of the connecting frame (1), with its lower end rigidly connected to the upper side of the connecting frame (1) and its upper end used for being lifted. The measuring components are also a plurality of each, and are all located at the lower part of the connecting frame (1). Their upper ends are respectively connected to each of the first connecting points, and their lower ends are respectively connected to each of the lifting points of the spacecraft under test. The measuring components have a controlled telescopic connector (31) and a tensile tester (32) between their two ends. The measurement component includes: A rotating connector (33) is provided, one end of which is rotatably connected to the corresponding first connection point about a first axis, the first axis being perpendicular to the first plane. Pitch connector (34), which is hinged between the other end of the rotating connector and one end of the telescopic connector (31); A connecting rod (35) is provided, one end of which is connected to the other end of the telescopic connector (31). The shape of the other end of the connecting rod (35) corresponds to the installation structure at the lifting point on the spacecraft under test, and is used for detachable connection with it.

2. The spacecraft center of mass measurement device according to claim 1, characterized in that, The retractable connector (31) is an electric cylinder.

3. The spacecraft center of mass measurement device according to claim 1, characterized in that, The connection component includes: A fastener (21) is provided on the upper side of the connecting frame (1); Hook (22), the hook (22) is used to suspend the spacecraft center of mass measurement device at a high position; The lifting rod (23) is located between the fixing member (21) and the hook (22).

4. The spacecraft center of mass measurement device according to claim 3, characterized in that, The upper side of the connecting frame (1) is provided with a plurality of second connecting points corresponding to each of the first connecting points, and the fixing member (21) is also provided with a plurality of them, and is respectively connected to each of the second connecting points.

5. The spacecraft center of mass measurement device according to claim 3, characterized in that, The boom (23) includes a first boom (231), a second boom (232) and an adjusting tube (233). One end of the first boom (231) is connected to the fixing member (21), one end of the second boom (232) is connected to the hook (22), and the other ends of the first boom (231) and the second boom (232) are respectively threaded to the two ends of the adjusting tube (233).

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