A rocket compartment separation test device

Abstract

This application discloses a rocket compartment separation test device, comprising: at least two test vehicles, each of which is configured to carry and connect to two compartments to be separated; each test vehicle is equipped with a first measurement module for measuring the acceleration of the two compartments in the horizontal plane during separation; and a test platform having a horizontal supporting surface, with the axes of the two compartments to be separated parallel to the supporting surface, the supporting surface being configured to support the test vehicles. This rocket compartment separation test device provides more accurate data.

Description

Technical Field

[0001] The present application generally relates to the field of aerospace equipment technology, and in particular to a rocket compartment separation test device. Background Art

[0002] In order to ensure the accuracy of the operation of separation-type spacecraft such as rockets, it is necessary to calculate in advance the impact force that the compartments to be separated on the spacecraft will be subjected to during separation. In order to simulate the state of gradual separation between the compartments on the spacecraft during flight, it is generally necessary to place the compartments to be separated on a separation test device and test the forces exerted on the two compartments during the separation process. Existing separation test devices are generally guide rail type test devices, that is, the two compartments to be separated are placed on two test vehicles that are slidably connected to the guide rails, and the separation of the two compartments is achieved using the same separation mechanism such as explosive bolts as in the actual separation. The acceleration of the two compartments is tested during the separation process to determine the forces exerted on the two compartments. However, since the force exerted on the two compartments by the separation mechanism such as explosive bolts when triggered is not necessarily only in the direction of the track extension, the force conditions of the two compartments when separated measured by the above-mentioned separation test device are not accurate. It is difficult to achieve precise control of the flight trajectory of the spacecraft using this data as a reference. Summary of the Invention

[0003] In view of the above-mentioned defects or deficiencies in the prior art, it is desired to provide a rocket compartment separation test device with more accurate measurements.

[0004] The specific technical solutions are as follows:

[0005] The present application provides a rocket compartment separation test device, comprising:

[0006] A test vehicle, at least two of which are provided, each of which is used to carry and connect to two compartments to be separated. The test vehicle is provided with a first measurement module, which is used to measure the acceleration of the two compartments in the horizontal plane during separation;

[0007] The test platform has a horizontal bearing surface, the axes of the two compartments to be separated are parallel to the bearing surface, and the bearing surface is used to bear the test vehicle.

[0008] Optionally, the test vehicle is further provided with a first steering assembly, the first steering assembly comprising:

[0009] A support ring, the support ring being coaxially connected to the compartment to be separated;

[0010] A support frame, one end of the support frame is connected to the test vehicle, and the other end forms a rotatable connection structure with the support ring with a first axis as the axis, wherein the first axis is perpendicular to the axis of the support ring and passes through the center of the support ring;

[0011] The second measurement module is used to respectively measure the angular acceleration of the two compartment sections rotating around the first axes when the connection between the two compartment sections is separated.

[0012] Optionally, the support ring is connected to the compartment to be separated via a rolling bearing, and the rolling bearing is coaxial with the support ring;

[0013] The rocket compartment separation test device also includes a third measurement module, which is used to measure the angular acceleration of the two compartments rotating around their respective axes when they are separated.

[0014] Optionally, the system further comprises: a first verification module, the first verification module also being used to measure the angular acceleration of the connection between the two compartments when the connection is separated and rotating around each of the first axes;

[0015] The second verification module is also used to measure the angular acceleration of the two compartments rotating around their respective axes when they are separated.

[0016] Optionally, it also includes: a force meter, which is used to measure the first force required for the test vehicle carrying two compartments to be separated to perform uniform linear motion on the test platform, and is used to measure the second force required for the two compartments to rotate uniformly around the first axes after separation, and is also used to measure the third force required for the two compartments to rotate uniformly around their respective axes after separation.

[0017] The beneficial effects of this application are:

[0018] Because the two test vehicles carrying the two compartments to be separated are connected to the test platform via a sliding or rolling connection with a high degree of freedom, a universal wheel structure is preferably provided on the bottom of the test vehicle. When the separation mechanism between the two compartments is triggered, the two compartments are subjected to corresponding forces. Since the two compartments are each connected to a test vehicle, both test vehicles are driven by the horizontal component of the aforementioned forces and move on the support surface. The acceleration of the two compartments can be measured using the first measurement module, and the horizontal component of the force applied by the separation mechanism on the two compartments can be calculated. This conversion can then determine the component of the force applied to the two compartments within a predetermined plane after the actual separation of the spacecraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Other features, objects and advantages of the present application will become more apparent upon reading the detailed description of non-limiting embodiments made with reference to the following drawings:

[0020] Figure 1 A side view of a rocket compartment separation test device provided in an embodiment of the present application;

[0021] Figure 2 Rear view of the rocket compartment separation test device provided in an embodiment of the present application.

[0022] Numbers in the figure: 1, test vehicle; 2, test platform; 31, support ring; 32, support frame; 33, rolling bearing. DETAILED DESCRIPTION

[0023] The present application will be further described in detail below with reference to the accompanying drawings and examples. It should be understood that the specific embodiments described herein are merely for the purpose of explaining the relevant invention and are not intended to limit the invention. It should also be noted that, for ease of description, only portions relevant to the invention are shown in the accompanying drawings.

[0024] It should be noted that, in the absence of conflict, the embodiments and features of the embodiments in this application can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0025] Please refer to Figure 1 , which is a side view of a rocket compartment separation test device provided in this embodiment, comprising:

[0026] A test vehicle 1, at least two of which are provided, each of which is used to carry and connect to two compartments to be separated. The test vehicle 1 is provided with a first measurement module, which is used to measure the acceleration of the two compartments in the horizontal plane during separation;

[0027] The test platform 2 has a horizontal bearing surface, the axes of the two compartments to be separated are parallel to the bearing surface, and the bearing surface is used to bear the test vehicle 1.

[0028] Since the two test vehicles 1 carrying two compartments to be separated are connected to the test platform 2 in a sliding or rolling connection with a relatively high degree of freedom, a universal wheel structure is preferably provided on the bottom of the test vehicle. When the separation mechanism between the two compartments is triggered, the two compartments are respectively subjected to corresponding forces. Since the two compartments are respectively connected to one test vehicle 1, the two test vehicles 1 are driven by the components of the above forces in the horizontal plane and move on the bearing surface. The acceleration of the two compartments can be measured by the first measurement module, and then the components of the forces applied by the separation mechanism to the two compartments in the horizontal direction can be calculated, and the components of the forces applied to the two compartments in a certain set plane after the actual separation of the spacecraft can be obtained through conversion. The above conversion process is common knowledge in this field and will not be elaborated here.

[0029] In a preferred embodiment to further improve the accuracy of force measurement, the test vehicle is further provided with a first steering assembly, which includes:

[0030] A support ring 31, wherein the support ring 31 is coaxially connected to the compartment to be separated;

[0031] A support frame 32, one end of which is connected to the test vehicle 1, and the other end of which forms a rotatable connection structure with the support ring 31 about a first axis, wherein the first axis is perpendicular to the axis of the support ring 31 and passes through the center of the support ring 31;

[0032] The second measurement module is used to respectively measure the angular acceleration of the two compartment sections rotating around the first axes when the connection between the two compartment sections is separated.

[0033] like Figure 2 As shown in , since a support frame 32 is provided on the upper side of the test vehicle 1, the upper side of the support frame 32 is connected to the support ring 31, and the support ring 31 on each test vehicle 1 is connected to the corresponding cabin, and the support ring 31 can rotate around the first axis. Therefore, when the two cabins are separated, the angular acceleration of the two cabins in the rotation around the first axis can be measured by the second measurement module, and then the force on the two cabins in the rotation direction around the first axis can be calculated, and then the force on the two cabins around a set axis when the two cabins of the spacecraft are separated at high altitude can be inferred through conversion. This measurement result can also be used to avoid the situation where the lower cabin affects the flight trajectory of the upper cabin after separation.

[0034] In a preferred embodiment for further improving the accuracy of force measurement, the support ring 31 is connected to the compartment to be separated via a rolling bearing 33, and the rolling bearing 33 is coaxial with the support ring 31;

[0035] The rocket compartment separation test device also includes a third measurement module, which is used to measure the angular acceleration of the two compartments rotating around their respective axes when they are separated.

[0036] In the existing separation test device, since the two compartments are fixedly connected to the test vehicle, it is impossible to measure the force in the rotation direction generated by the separation mechanism on the two compartments. In this embodiment, by setting the rolling bearing 33 between the support ring 31 and the corresponding compartment, the angular acceleration of the two compartments rotating around their respective axes during separation can be measured by the third measurement module, and then the force in the rotation direction generated by the separation mechanism on the two compartments can be calculated. By superimposing the force in this dimension with the force in the two dimensions in the previous two steps, the precise values ​​of the force on the two compartments can be obtained respectively, and the force conditions of the two compartments during separation can be predicted in advance, so as to set the corresponding balancing mechanism to maintain the accuracy of the spacecraft's flight trajectory.

[0037] In a preferred embodiment for further improving the accuracy of force measurement, the system further includes: a first verification module, the first verification module also being used to measure the angular acceleration of the connection between the two compartments when the connection is separated and rotating around each of the first axes;

[0038] The second verification module is also used to measure the angular acceleration of the two compartments rotating around their respective axes when they are separated.

[0039] In the above embodiment, the measurement of angular acceleration generally uses a conventional measuring device such as an inertial group. However, in order to improve the accuracy of the measurement, a circular grating scale can be set at the same position as the second measurement module and the third measurement module as a calibration device, namely the first calibration module and the second calibration module provided in this embodiment. This can effectively prevent errors in the inertial group measurement and further improve the accuracy of the force measurement.

[0040] In a preferred embodiment for further improving the accuracy of force measurement, it also includes: a force meter, which is used to measure the first force required for the test vehicle carrying two compartments to be separated to perform uniform linear motion on the test platform 2, and is used to measure the second force required for the two compartments to rotate uniformly around the first axes after separation, and is also used to measure the third force required for the two compartments to rotate uniformly around their respective axes after separation.

[0041] It can be seen from the above implementation scheme that during the test process, the test results will be affected by the following factors, namely: the friction between the test vehicle 1 and the test platform 2, the friction between the support ring 31 and the support frame 32, and the friction during the movement of the rolling bearing 33 itself. The above friction will have different dimensions of influence on the test results, but in the actual separation process of the spacecraft, it is not affected by the above friction. Therefore, in order to restore the real situation, the influence of the above friction on the test results needs to be eliminated. The corresponding values ​​of friction can be obtained by the test operation of the dynamometer in the above three dimensions. After eliminating its influence, the separation force of the two compartments is more accurate.

[0042] The above description is merely a preferred embodiment of the present application and an illustration of the technical principles employed. Those skilled in the art should understand that the scope of the invention herein is not limited to the technical solutions formed by the specific combination of the above-mentioned technical features, but also encompasses other technical solutions formed by any combination of the above-mentioned technical features or their equivalents without departing from the inventive concept. For example, a technical solution formed by replacing the above-mentioned features with (but not limited to) technical features having similar functions disclosed in this application.

Claims

1. A rocket compartment separation test device, characterized in that: include: A test vehicle (1), wherein at least two test vehicles (1) are provided, and are respectively used to carry and be connected to two compartments to be separated, and a first measurement module is provided on the test vehicle (1), and the first measurement module is used to measure the acceleration of the two compartments in the horizontal plane during separation; A test platform (2), the test platform (2) having a horizontal bearing surface, the axes of the two compartments to be separated being parallel to the bearing surface, the bearing surface being used to bear the test vehicle (1); The test vehicle is further provided with a first steering assembly, which includes: A support ring (31), wherein the support ring (31) is coaxially connected to the compartment to be separated; A support frame (32), one end of the support frame (32) is connected to the test vehicle (1), and the other end forms a rotatable connection structure with the support ring (31) with a first axis as an axis, wherein the first axis is perpendicular to the axis of the support ring (31) and passes through the center of the support ring (31); a second measuring module, configured to respectively measure the angular acceleration of the connection between the two compartments when the connection is separated and rotating around the first axes; It also includes a dynamometer, which is used to measure the first pulling force required when the test vehicle carrying the two compartments to be separated performs uniform linear motion on the test platform (2), and is used to measure the second pulling force required when the two compartments are separated and rotated at a uniform speed around the first axes, and is also used to measure the third pulling force required when the two compartments are separated and rotated at a uniform speed around their respective axes.

2. The rocket compartment separation test device according to claim 1, characterized in that: The support ring (31) is connected to the compartment to be separated via a rolling bearing (33), and the rolling bearing (33) is coaxial with the support ring (31); The rocket compartment separation test device also includes a third measurement module, which is used to measure the angular acceleration of the two compartments rotating around their respective axes when they are separated.

3. The rocket compartment separation test device according to claim 2, characterized in that: Also includes: a first calibration module, the first calibration module also being used to measure the angular acceleration of the connection between the two compartments when the connection is separated and rotating about the first axes; The second verification module is also used to measure the angular acceleration of the two compartments rotating around their respective axes when they are separated.

Images