WO2023029148A1

WO2023029148A1 - Height-adjustable spacecraft storage tank simulated loading static experiment device and method

Info

Publication number: WO2023029148A1
Application number: PCT/CN2021/122748
Authority: WO
Inventors: 张宝康; 刘炳立; 臧博; 张超; 张凯
Original assignee: 北京空间机电研究所
Priority date: 2021-09-06
Filing date: 2021-10-09
Publication date: 2023-03-09
Also published as: CN113607403B; CN113607403A

Abstract

Provided in the present invention is a height-adjustable spacecraft storage tank simulated loading static experiment device and method, relating to the technical field of aerospace mechanics testing. The device comprises a simulated storage tank structure, a vertical connecting flange base, a longitudinal loading connector, and a transverse loading device, wherein the vertical connecting flange base is connected to a satellite body or an aircraft; the longitudinal loading connector applies a longitudinal load, and a clamping block thereof is arranged between link plates on two sides and is fixed by means of a connecting pin; the transverse loading device comprises a hoop and an adjustment cushion block; and the adjustment cushion block fixes the position of a loading connecting lug by means of a connecting screw, the loading connecting lug determines the direction in which a load is applied, the adjustment cushion block determines the position where a transverse load is applied, and the transverse loading device applies a transverse load to a single simulated storage tank structure. The device can achieve load application for a satellite structure static experiment storage tank, and simulates the overall load-bearing requirement of an aircraft structure. The method can longitudinally apply a load without an additional bending moment, thereby improving the experiment reliability and scientificity.

Description

A height-adjustable static test device and method for simulated loading of spacecraft storage tanks

technical field

The invention relates to the technical field of aerospace mechanics testing, in particular to a height-adjustable space vehicle storage tank simulated loading static test device and method.

Background technique

During the development of the satellite structure, it is necessary to simulate its load-bearing form through static tests under laboratory conditions, and to assess and verify its structure. The actual storage tank products of the satellite are generally not included in the test with its structure during the static test of the structure, and the load of the storage tank is the main content of the load-bearing assessment of its main structure. The overall structure of the satellite must meet the load-carrying capacity of its fuel storage tanks in order to realize the load-bearing integrity of its overall structure. The storage tank simulation loading test device is a device for implementing the static test storage tank load of the satellite structure.

Due to the difference of the aircraft, the load of the storage tank is also different. Therefore, during the static test of the satellite structure, the position of the center of mass of the storage tank load will change due to the difference in the platform, which is the need to envelop the storage tank load of many platforms of the aircraft to the greatest extent. , the center of mass of the storage tank simulated loading test device should also be adjusted accordingly. At present, there is still no device in the existing technology that can satisfy the simulated loading of satellite storage tanks in static tests, and the center of mass of the load can be adjusted, and the simulated loading test device needs to be comprehensively considered from design, processing, implementation, installation and adjustment to carry out satellite storage tanks. The box simulates the loading static test, and realizes the load-carrying requirement of the simulated aircraft structure as a whole.

technical solution

In order to solve the load imposed on the satellite structure and some aircraft static test storage tank simulations, on the premise of completely simulating the boundary connection of the storage tank, the real simulation of the satellite's working state storage tank's own structural load; ensure the structure of the star and the aircraft In order to assess the integrity and reliability of the static test, the present invention provides a height-adjustable space vehicle storage tank simulated loading static test device and method, and the specific technical scheme is as follows.

A height-adjustable spacecraft storage tank simulated loading static test device, including a simulated storage tank structure, an upper and lower connection flange seat, a longitudinal loading connection and a lateral loading device. The upper and lower connection flanges are connected to the aircraft at both ends, and The loading connection applies a longitudinal load, and the clamp blocks of the longitudinal loading connection are arranged between the connecting plates on both sides and fixed by connecting pins; the lateral loading device includes a clamp and an adjustment pad, and the adjustment pad is fixed by a connecting screw to the loading connection lug The position of the loading connection lug determines the direction of the applied load, the adjustment pad determines the application position of the lateral load, and the lateral loading device applies a lateral load to the single simulated tank structure.

Preferably, the upper and lower connecting flanges include an upper connecting flange and a lower connecting flange, and the upper connecting flange and the lower connecting flange are provided with internal threads.

Preferably, the pitch circles of the upper connecting flange and the lower connecting flange are provided with a plurality of holes to connect with the structure of the star or the aircraft.

Preferably, the connection for longitudinal loading includes connecting plates, clips and pins, the connecting plates symmetrically arranged on both sides apply longitudinal loads together, and the resultant force of the longitudinal loading acts on the center of the simulated tank structure.

Preferably, the clamping block is fixedly connected to the connecting plate through a pin, and the adjacent simulated tank structure exerts a longitudinal resultant force.

It is also preferred that multiple lateral loading devices are provided, and the lateral loading device adjusts the height of the center of mass.

It is also preferable that the lateral loading device includes a hoop, an adjusting cushion block and a loading connecting lug, the hoop is in the shape of a semicircle, and the hoop is fixed to the loading connecting lug by screws.

A height-adjustable spacecraft storage tank simulated loading static test method, using the above-mentioned a height-adjustable spacecraft storage tank simulated loading static test device, including: a structural installation designed according to the requirements of the simulated storage tank load The form is connected with a star or an aircraft; adjust the height of the center of mass and the application position of the lateral load; there is no bending moment when the longitudinal load is applied, and the lateral load is applied according to the design square.

It is further preferred that the experiment is repeated after the centroid height is adjusted to simulate tank structures of various types of satellites.

Further preferably, the height-adjustable static test device for simulating loading of the spacecraft tank is used to simulate the load-bearing requirements of the entire aircraft structure.

Beneficial effect

The invention provides a height-adjustable spacecraft storage tank simulated loading static test device and method. The beneficial effects are: the device realizes the application of a single simulated storage tank structure longitudinal load without additional bending moment, and is compatible with adjacent storage tanks. Or a better combination of other load application points, in conjunction with other lever systems, enables the device to fully simulate the load of the storage tank applied to the corresponding load-bearing structure of the star or aircraft, improving the reliability and scientificity of the test.

It is convenient to adjust the height of the center of mass by using this method for testing, and it provides convenience for the design, processing, installation and adjustment of the storage tank. It truly simulates the effect of the satellite's storage tank on its own structure load in the working state, and can ensure the structure of the star and the aircraft. The integrity and reliability of the static test assessment.

Description of drawings

Figure 1 is a schematic diagram of the main structure of a height-adjustable storage tank simulated loading static test device;

Fig. 2 is a partial cross-sectional schematic diagram of Fig. 1;

Fig. 3 is the local schematic diagram of simulated loading static test device;

Fig. 4 is a partial schematic diagram of the direction A of the simulated loading static test device;

Fig. 5 is a schematic diagram of assembling the simulated storage tank structure;

Fig. 6 is a partial structural schematic view of the loading mechanism;

Figure 7 is a schematic diagram of multiple tank structures applying longitudinal and lateral loads;

In the figure: 1-simulated storage tank structure, 2-upper and lower connection flange seat, 3-longitudinal loading connection, 4-lateral loading device;

21-upper connection flange, 22-lower connection flange; 31-connecting plate, 32-clamp block, 33-pin; 41-clamp, 42-adjusting spacer, 43-loading connection lug, 44-first Loading link, 45-the second loading link, 46-the third loading link, 47-the fourth loading link.

Embodiments of the present invention

1 to 7, the specific implementation of a height-adjustable spacecraft storage tank simulated loading static test device and method provided by the present invention will be described.

A height-adjustable spacecraft storage tank simulated loading static test device specifically includes a simulated tank structure 1, an upper and lower connecting flange seat 2, a longitudinal loading connection 3 and a lateral loading device 4, wherein the simulated tank structure 1 can simulate aircraft The storage tanks of the same structure are used in indoor experiments to realize the parameter design of the storage tanks and other structures; the connecting structure provided by the upper and lower connecting flanges 2 is connected with the structure of the star or the aircraft, simulating the storage tank structure of the actual aircraft; the longitudinal loading device 3 The longitudinal load can be applied without applying an additional bending moment, and the lateral loading device 4 adjusts the position of the center of mass and can adjust the position where the load is applied.

Among them, the simulated storage tank structure 1 is set according to the structural installation form designed to simulate the load capacity of the storage tank, the upper and lower connecting flanges 2 are connected to the aircraft or satellite structure at both ends, the longitudinal loading connection 3 applies longitudinal load, and the clamping block of the longitudinal loading connection 3 is set Between the connecting plates 31 on both sides and can be fixed by connecting pins 33 . The lateral loading device 4 includes a clamp 41 and an adjusting pad 42. The adjusting pad 42 fixes the position of the loading connecting lug 43 through a connecting screw. The loading connecting lug 43 determines the direction of the applied load, and the adjusting pad 42 determines the application of the lateral load. position, the lateral loading device 4 applies lateral loads to a single simulated tank structure.

The upper and lower connecting flanges 2 include an upper connecting flange 21 and a lower connecting flange 22, and the upper connecting flange 21 and the lower connecting flange 22 are provided with internal threads for threaded connection. The index circles of the upper connecting flange 21 and the lower connecting flange 22 are provided with a plurality of holes to connect with the structure of the star or the aircraft. The flange is processed with corresponding holes on the index circle to connect with the star or aircraft structure, which can be connected with the star or aircraft structure through connecting screws, ensuring the firmness in the longitudinal direction and the stability of loading.

The longitudinal loading connection 3 includes connecting plates 31, clamping blocks 32 and pins 33. The connecting plates symmetrically arranged on both sides apply longitudinal loads together, and equal loads are applied to the left and right sides. The resultant force of the longitudinal loading acts on the center of the simulated tank structure . The clamping block 32 is fixedly connected to the connecting plate 31 through the pin 33, and the adjacent simulated tank structure exerts a longitudinal resultant force. The position of the resultant force is at the center of the simulated tank loading device, and no additional bending moment will be applied to the structure. The clamp block 32 is connected to the connecting plate through connecting pins, and can be used for applying longitudinal resultant force of two adjacent tanks.

Multiple lateral loading devices 4 can be provided, and the lateral loading device 4 can adjust the height of the center of mass. The lateral loading device 4 includes a hoop 41 , an adjusting pad 42 and a loading connecting lug 43 , wherein the hoop 41 is semicircular, and the hoop fixes the loading connecting lug 43 by screws. The two semicircular clamps fix the loading lugs in the direction in which the load needs to be applied through connecting screws, and the lateral centroid position is laid on the lateral loading connection position of the simulated storage tank structure by adjusting the spacer to complete the installation of a single storage tank. application of lateral loads.

The positions of the longitudinal loading connection 3 and the lateral loading device 4 can be adjusted arbitrarily along the length direction of the simulated tank structure 1, and after adjustment, the simulated

The center of mass height is adjusted and the test is repeated to simulate the storage tank structure of various types of satellites. The height-adjustable spacecraft tank simulated loading static test device is used to simulate the overall load-bearing requirements of the aircraft structure.

As shown in Figure 7, in this embodiment, four storage tank structures can be set for simulation. The simulated storage tanks are evenly arranged on the circumferential structure of the cylindrical cabin section, and the lateral loading device is connected with the lateral loading mechanism, which applies lateral load. , the lateral loading mechanism includes a link mechanism, a loading transmission cylinder, a load-bearing platform and a force-measuring sensor. The link mechanism includes a first loading link 44, a second loading link 45, a third loading link 46 and a fourth loading link 47, and the two ends of the first loading link are respectively connected to the second loading link and the second loading link Three loading links; one end of the second loading link applies lateral load to the storage tank, and the other end is connected to the fourth loading link; one end of the third loading link applies lateral load to the storage tank, and the other end is connected to the fourth loading link ; Both ends of the fourth loading link apply transverse loads to the tank respectively. Each longitudinal loading connection 3 applies equal loads on the left and right sides, and applies longitudinal loads through each longitudinal loading connection.

The device realizes the application of a single simulated longitudinal load of the tank structure without additional bending moments, and better combination with adjacent tanks or other load application points. Cooperating with other lever systems, the device can completely simulate the load application of the tank To the corresponding load-bearing structure of the star or aircraft, the reliability and scientificity of the test are improved; the height of the center of mass can be adjusted conveniently by using this method for the test, which provides convenience for the design, processing, installation and adjustment of the storage tank, and truly simulates the satellite The effect of the storage tank on its own structural load in the working state can ensure the integrity and reliability of the structural static test assessment of the star and the aircraft.

Of course, the above descriptions are not intended to limit the present invention, and the present invention is not limited to the above examples. Changes, modifications, additions or replacements made by those skilled in the art within the scope of the present invention shall also belong to the present invention. protection scope of the invention.

Claims

A height-adjustable spacecraft storage tank simulated loading static test device is characterized in that it includes a simulated storage tank structure, an upper and lower connecting flange seat, a longitudinal loading connection and a lateral loading device, and the upper and lower connecting flanges are at both ends Connecting the aircraft, the longitudinal loading connection applies a longitudinal load, and the clamp blocks of the longitudinal loading connection are arranged between the connecting plates on both sides and fixed by connecting pins; the lateral loading device includes a clamp and an adjustment pad, and the adjustment pad is fixed by a connecting screw Loading the position of the connecting lug, the loading connecting lug determines the direction of the applied load, adjusting the spacer determines the position of applying the lateral load, and the lateral loading device applies a lateral load to the single simulated tank structure.
A kind of height-adjustable spacecraft storage tank simulation loading static test device according to claim 1, characterized in that, the upper and lower connecting flanges include an upper connecting flange and a lower connecting flange, the upper connecting flange and the lower connecting flange. The lower connecting flange is provided with internal threads.
A height-adjustable spacecraft storage tank simulated loading static test device according to claim 2, wherein a plurality of holes are arranged on the indexing circles of the upper connecting flange and the lower connecting flange Connect with the structure of the astral body or aircraft.
The height-adjustable static test device for simulated loading of spacecraft storage tanks according to claim 1, wherein the longitudinal loading connection includes connecting plates, clips and pins, and the connecting plates arranged symmetrically on both sides share a common A longitudinal load is applied, and the resultant force of the longitudinal load acts on the center of the simulated tank structure.
The height-adjustable static test device for simulated loading of a spacecraft storage tank according to claim 4, wherein the clamping block is fixedly connected to the connecting plate through pins, and the adjacent simulated storage tank structure exerts a longitudinal resultant force.
The height-adjustable spacecraft storage tank simulated loading static test device according to claim 1, wherein there are multiple lateral loading devices, and the lateral loading device adjusts the height of the center of mass.
A height-adjustable spacecraft storage tank simulated loading static test device according to claim 6, wherein the lateral loading device includes a clamp, an adjustment pad and a loading connection ear piece, and the clamp Semi-circular in shape, the clamp is screwed to load the connection lugs.
A height-adjustable spacecraft storage tank simulation loading static test method, using a height-adjustable spacecraft storage tank simulation loading static test device according to any one of claims 1 to 7, characterized in that, Including: the structural installation form designed according to the requirements of the simulated tank load is connected to the star or the aircraft; the height of the center of mass and the application position of the lateral load are adjusted; the longitudinal load is applied without bending moment, and the lateral load is applied according to the design square.
A height-adjustable spacecraft storage tank simulation loading static test method according to claim 8, characterized in that the test is repeated after the height of the center of mass is adjusted to simulate the storage tank structures of various types of satellites.
A height-adjustable spacecraft storage tank simulated loading static test method according to claim 8, wherein the height-adjustable spacecraft tank simulated loading static test device is used to simulate the overall structure of the aircraft load requirements.