CN104655417A - Device for testing high and low temperature performance of certain indexing mechanism of space station - Google Patents

Abstract

The invention discloses a high and low temperature performance testing device for a certain indexing mechanism of a space station, which belongs to the field of testing devices for an indexing mechanism of a space station, and includes a high and low temperature box, a middle support and flywheel device, and a lower end control device; the middle support and flywheel device includes a rotary Position mechanism, support body, shaft system, flywheel, wherein: the upper end of the index mechanism is placed in the high and low temperature box, the lower end is connected with the flywheel through the shaft system, the support body is provided with bolt holes and different interfaces, and the index mechanism is fixed on the On the support body; the lower end control device includes an air flotation platform, an electric cylinder, a sliding trolley, a linear guide rail, and an electrical control, wherein: the air flotation platform is located below the top support part of the flywheel, the electric cylinder is located below the flywheel, the sliding trolley, the linear guide rail It is installed under the electric cylinder; the electric control is located under the whole device. The present invention solves the current lack of simulation equipment for indexing mechanisms to be launched into space.

Description

A high and low temperature performance test device for an indexing mechanism of a space station

technical field

The invention relates to a high and low temperature performance testing device of a certain indexing mechanism of a space station, which belongs to the field of physical experiment devices.

Background technique

From the Soviet Union's Salyut 1 space station to the International Space Station still serving in space, the performance and working life of large mechanisms such as the indexing mechanism, docking mechanism, and deployment mechanism affect the service life of the space station. Therefore, in order to obtain the performance parameters of the indexing mechanism, analyze the possible problems of the indexing mechanism for corresponding improvement and optimization, and increase the working life of the indexing mechanism, ground simulation experiments are required before the indexing mechanism is launched into space. However, China has not launched the International Space Station so far. When building the international space, the United States refused to join China because it believed that the space station technology would be used for military purposes. Therefore, China is still very deficient in performance testing devices for indexing mechanisms.

The high and low temperature performance test device for the indexing mechanism during the indexing process is a necessary test device for the indexing mechanism development stage. It is mainly used for load simulation of the indexing arm indexing process after the assembly of the indexing mechanism unit is completed, and tests the indexing starting torque, speed, Data such as rotation angle and starting time are used to evaluate the joint performance of the transposition mechanism.

Contents of the invention

In order to solve the deficiencies in the prior art, the present invention provides a high and low temperature performance test device for a ground simulation space station indexing mechanism, which can test the comprehensive performance of a space station indexing mechanism in the high and low temperature environment during the indexing process. The technology used The scheme is:

A high and low temperature performance testing device for an indexing mechanism of a space station, characterized in that it includes a high and low temperature box 1, a middle support and flywheel device, and a lower end control device;

The middle support and flywheel device includes an indexing mechanism 2, a support body 3, a shafting 4, and a flywheel 5, wherein: the upper end of the indexing mechanism 2 is placed in the high and low temperature box 1, and the lower end is connected with the flywheel 5 through the shafting 4, supporting Bolt holes and different interfaces are provided on the body 3, and the indexing mechanism 2 is fixed on the support body 3 through the interface;

The lower end control device includes an air flotation platform 6, an electric cylinder 7, a sliding trolley 8, a linear guide rail 9, and an electrical control 10, wherein: the air flotation platform 6 is located below the top support part of the flywheel 5, and the electric cylinder 7 is located below the flywheel 5. The sliding trolley 8 and the linear guide rail 9 are installed under the electric cylinder 7; the electric control 10 is located under the entire device.

The frame of the high and low temperature box 1 is made of stainless steel thin-walled plates and reinforcing ribs, and a lifting lug structure is designed on the upper end to facilitate the installation and disassembly of the indexing mechanism; the high and low temperature box 1 is sealed to control the temperature of the high and low temperature box. The temperature simulates the high and low temperature environment in space.

The shaft system 4 is equipped with a speed increaser, which can reduce the size of the inertia mechanical simulation parts and the motor demand; the shaft system 4 is a common shaft system for the inertia electrical simulation and the inertia mechanical simulation, and transmits the mechanical inertia to the indexing mechanism 2. The shafting 4 is equipped with a sensor and a signal collector, which collects the signal, collects it into the electrical device, processes and analyzes the signal, and obtains the performance parameters of the indexing mechanism.

The overall structure of the flywheel 5 is combined, and the lower part is provided with counterweights of different masses to simulate different mechanical inertias, and the electric cylinder 7 can install and disassemble the counterweights progressively.

The flywheel 5 supports a motor for simulating electrical inertia inside.

The flywheel 5 is placed on the air-floating platform 6 as a whole, and the air-floating platform 6 air-supports the flywheel 5 to simulate the weightless environment in space. The electric control 10 controls the work of the whole device, collects and processes signals.

The electrical control 10 is provided with a control cabinet, which is connected to the sensors and signal collectors installed on the shafting 4, controls and collects signals, and exchanges product information with the single testing equipment.

The ratio of length, width and height of the high and low temperature performance testing device of a certain indexing mechanism of the space station is: length: width: height = 9420:5055:8364.

The ratio of the diameter of the flywheel 5 to the length and width of the support body 3 is: diameter of the flywheel: length of the support body: width of the support body = 6550:5600:5600.

The indexing mechanism 2 that needs to be simulated is installed on the support body 3, and the whole is placed in the high and low temperature box. The high and low temperature box 1 is sealed. By controlling the temperature of the high and low temperature box 1, the temperature change in space is simulated. The high and low temperature box 1 is also placed on the support body 3 .

The shaft system 4 transmits the inertia of the torque, and at the same time, a speed increaser is installed on the shaft system, which can reduce the size of the inertia mechanical simulation parts and the motor demand.

The support body 3 is the basis of the whole set of devices, and acts as a support in the whole set of devices. There are bolt holes and other corresponding interfaces on the support body 3, which is convenient for the installation, disassembly and adjustment of the indexing mechanism. The mechanism 2 is installed on the support body 3, and the whole is placed in the high and low temperature box 1, and the high and low temperature box 1 is sealed. By controlling the temperature of the high and low temperature box 1, the temperature change in space is simulated.

The flywheel 5 is placed on the air-floating platform 6 as a whole. When the inertia simulation is performed, the flywheel 5 is supported by the air-floating platform 6 to reduce the friction force at the lower end, so as to simulate the weightless environment in space.

The overall structure of the flywheel 5 is made into a combined type to facilitate the simulation of different inertias, and fully simulate the physical inertia of the experimental cabins of different specifications in space; the bottom of the flywheel 5 is equipped with counterweights with different masses. , no need to replace the device, only need to increase or decrease the number of counterweights at the lower end of the flywheel. The flywheel counterweight is disassembled and installed through the electric cylinder 7. When it is necessary to change the inertia of the flywheel for simulation, it only needs to be raised and lowered to a suitable height by the electric cylinder 7 to loosen or tighten the corresponding bolts without manpower. Easy to install, greatly facilitates installation and disassembly, and greatly reduces the consumption of manpower and material resources.

In the lower part of the whole set of devices, a linear guide rail 9 and a slide block are installed to adjust the position of the whole set of devices.

The electrical gas device 10 plays a controlling role in the whole device, and is responsible for signal analysis and processing of the whole device.

In the present invention, the transposition device is fixed on the support body, placed in a high and low temperature box, and the temperature environment in space is simulated by changing the different temperatures in the high and low temperature box; the flywheel inertia simulation device is placed on the air flotation device to simulate space in a weightless environment. And the flywheel structure is made into a combined type, which can simulate different mechanical inertias. When changing the inertia, you only need to replace the flywheels with different specifications. The mechanical inertia of the flywheel is transmitted to an indexing mechanism of the space station through the shaft system. And a certain number of sensors and signal collectors are installed in the whole device to collect signals, and finally collect the signals to the electrical device for signal processing and analysis to obtain the performance parameters of the indexing mechanism.

The working principle of the invention is as follows: the flywheel inertia simulation device simulates the inertia load in the transposition process, and tests the start and stop characteristics of the transposition arm under the flywheel inertia load. The lower part of the flywheel is an air-floating platform, which supports the take-off wheel during work to reduce friction and simulate the weightless environment in space; at the same time, a motor with a specific specification is installed inside the flywheel, and the electrical inertia simulation has been completed; the electrical inertia The simulation and mechanical inertia simulation can be done through the electromagnetic clutch installed on the shaft system; the overall inertia is transmitted to the upper part of the indexing mechanism through the shafting, and the indexing mechanism is placed on the support body and placed in the high and low temperature box together with the support body , to simulate the high and low temperature environment in space; the control cabinet is used for equipment control and signal acquisition, and for product information interaction with single-test equipment.

Beneficial effects of the present invention:

(1) On the overall plan: in order to make the testing process of the indexing mechanism simple and convenient, and reduce the cost. The whole set of devices can perform different simulations for different types of indexing mechanisms, and the structure of the lower section does not need to be changed, only the upper interface needs to be changed.

(2) Place the inertia simulation device on the flywheel to simulate the weightless environment in space; place the indexing mechanism in the high and low temperature box, and simulate the temperature change in space by controlling the internal temperature of the high and low temperature box. The device can realistically simulate the working environment of the indexing mechanism in space.

(3) Mechanical simulation of different inertias can be carried out. The lower flywheel adopts a combined structure. For different inertias, it only needs to install or remove different numbers of counterweights. Even if the current flywheel inertia still cannot meet the requirements, It is only necessary to process the flywheel with a specific inertia 2 instead of remaking the whole set of devices.

(4) The lower end is designed with a linear guide rail, which can adjust the position of the whole device to meet the work needs.

Description of drawings

Fig. 1 is the front view of overall structure assembly drawing of the present invention;

(1, high and low temperature box; 2, indexing mechanism; 3, support body; 4, shafting; 5, flywheel; 6, air bearing platform; 7, electric cylinder; 8, slider; 9, linear guide rail; 10, electrical controls).

Fig. 2 is the local enlargement figure of front view of the present invention;

(2, indexing mechanism; 3, support body; 4, shaft system).

Fig. 3 is the partial enlarged view of front view of the present invention;

(5, flywheel; 6, air bearing platform; 7, electric cylinder; 8, slider; 9, linear guide rail; 10, electric control).

Fig. 4 is a side view of the assembly diagram of the overall structure of the present invention.

Fig. 5 is a top view of the assembly diagram of the overall structure of the present invention.

Detailed ways

This embodiment is described in conjunction with accompanying drawings 1-5. The high and low temperature performance test device of a certain indexing mechanism of a space station in this embodiment includes a high and low temperature box 1, an indexing mechanism 2, a support body 3, a shafting 4, a flywheel 5, and an air bearing platform 6. Electric cylinder 7, sliding trolley 8, linear guide rail 9, electrical control 10. The frame of the high and low temperature box 1 is mainly composed of stainless steel thin-walled plates and reinforcing ribs, and a lifting lug structure is designed on the upper end to facilitate the installation and disassembly of the indexing mechanism. The high and low temperature box 1 is placed on the support body 3 . In the whole device, the support body 3 is the basis of the whole device, and the support body 3 acts as a support in the whole device, and there are bolt holes and other corresponding interfaces at the upper end, which are convenient for the installation, disassembly and adjustment of the indexing mechanism. The transposition mechanism 2 that needs to be simulated is installed on the support body 3 through the corresponding interface on the support body 3, and placed in the high and low temperature box as a whole, and the high and low temperature box is sealed. By controlling the temperature of the high and low temperature box, the high and low temperature in space is simulated. Low temperature environment. The indexing mechanism 2 is connected with the lower flywheel component through the shaft system 4, and the shaft system component 4 transmits the moment of inertia of the torque. A speed increaser is installed on the shaft system, which can reduce the size of the inertia mechanical simulation parts and the motor demand. The flywheel 5 is placed on the air-floating platform as a whole. When performing inertia simulation, the flywheel 5 is supported by air-floating through the air-floating platform to reduce the friction force at the lower end, so as to simulate the weightless environment in space. The overall structure of the flywheel 5 is made into a combined type to facilitate the simulation of different inertias and fully simulate the physical inertias of the experimental cabins of different specifications in space. When simulating different inertias, there is no need to replace the device, just increase or decrease the number of counterweights at the lower end of the flywheel. The flywheel counterweight is disassembled and installed through the electric cylinder 7. When the flywheel inertia needs to be changed for simulation, it only needs to be raised and lowered to a suitable height by the electric cylinder to loosen or tighten the corresponding bolts. In the lower part of the whole structure, a linear guide rail 9 is installed, which can slightly adjust the position of the whole set of devices. The electrical device 10 controls the work of the entire device and is responsible for signal collection and processing.

Shaft system 4 is a shared shaft system for inertia electrical simulation and inertia mechanical simulation, in which the motor for electrical inertia simulation is placed inside the flywheel support; a speed increaser is installed on shaft system 4, which can reduce the size of inertia mechanical simulation components and motor requirements ; Shaft 4 is a common shaft for inertia electrical simulation and inertia mechanical simulation, and transmits mechanical inertia to indexing mechanism 2 .

The shafting 4 is equipped with a sensor and a signal collector, which collects the signal, summarizes it to the electrical device, processes and analyzes the signal, and obtains the performance parameters of the indexing mechanism.

The electrical control 10 is provided with a control cabinet, which is connected to the sensors and signal collectors installed on the shafting 4, controls and collects signals, and exchanges product information with the unit testing equipment.

The ratio of length, width and height of a high and low temperature performance test device for an indexing mechanism in a space station is: length: width: height = 9420:5055:8364.

The ratio of the diameter of flywheel (5) and the length and width of support body (3) is: flywheel diameter: support body length: support body width=6550:5600:5600.

The overall structure of the flywheel 5 is made into a combined type to facilitate the simulation of different inertias, and fully simulate the physical inertia of the experimental cabins of different specifications in space; the bottom of the flywheel 5 is equipped with counterweights with different masses. , no need to replace the device, only need to increase or decrease the number of counterweights at the lower end of the flywheel. The flywheel counterweight is disassembled and installed through the electric cylinder 7. When it is necessary to change the inertia of the flywheel for simulation, it only needs to be raised and lowered to a suitable height by the electric cylinder 7 to loosen or tighten the corresponding bolts without manpower. Easy to install, greatly facilitates installation and disassembly, and greatly reduces the consumption of manpower and material resources.

Working principle: The flywheel inertia simulation device simulates the inertia load during the indexing process, and tests the start and stop characteristics of the indexing arm under the flywheel inertia load. The lower part of the flywheel is an air-floating platform, which supports the take-off wheel during operation to reduce friction and simulate the weightless environment in space. At the same time, inside the flywheel, a motor with specific specifications is installed, and the electrical inertia simulation has been completed. The electrical inertia simulation and mechanical inertia simulation can be done through the electromagnetic clutch installed on the shaft system. The overall inertia is transmitted to the upper part of the indexing mechanism through the shaft system. The indexing mechanism is placed on the support body and placed in a high and low temperature box together with the support body to simulate the high and low temperature environment in space; the control cabinet is used for equipment control and Signal collection and product information interaction with single test equipment.

Fix the indexing device on the support body, place it in a high and low temperature box, and simulate the temperature environment in space by changing the different temperatures in the high and low temperature box; place the flywheel inertia simulation device on the air flotation device to simulate the weightlessness in space environment. And the flywheel structure is made into a combined type, which can simulate different mechanical inertias. When changing the inertia, it is only necessary to replace the flywheels of different specifications. The mechanical inertia of the flywheel is transmitted to an indexing mechanism of the space station through the shaft system. And a certain number of sensors and signal collectors are installed in the whole device to collect signals, and finally collect the signals to the electrical device for signal processing and analysis to obtain the performance parameters of the indexing mechanism.

Although the present invention has been disclosed above with preferred embodiments, it is not intended to limit the present invention. Any person familiar with this technology can make various changes and modifications without departing from the spirit and scope of the present invention. Therefore The scope of protection of the present invention should be defined by the claims.

Claims (10)

1. a space station indexing mechanism high temperature performance proving installation, is characterized in that, comprises high-low temperature chamber (1), midfoot support and flywheel gear, lower end control device;

Described midfoot support and flywheel gear comprise indexing mechanism (2), supporter (3), axle system (4), flywheel (5), wherein: indexing mechanism (2) upper end is placed in high-low temperature chamber (1), lower end is connected with flywheel (5) by axle system (4), supporter (3) is provided with bolt hole and distinct interface, and indexing mechanism (2) is fixed on supporter (3) by interface;

Described lower end control device comprises air floating platform (6), electric cylinder (7), sliding machine (8), line slideway (9), electrical control (10), wherein: air floating platform (6) is positioned at the below at flywheel (5) top braces position, electric cylinder (7) is positioned at flywheel (5) below, and sliding machine (8), line slideway (9) are arranged on the below of electric cylinder (7); Described electrical control (10) is positioned at the below of package unit.

2. space station according to claim 1 indexing mechanism high temperature performance proving installation, is characterized in that, described high-low temperature chamber (1), and framework adopts Thin Stainless Steel wallboard and strengthens fin, and is provided with shackle structure in upper end; Described high-low temperature chamber (1) seals, and controls high and low temperature environment in the temperature simulation space of high-low temperature chamber.

3. space station according to claim 1 indexing mechanism high temperature performance proving installation, is characterized in that, described axle system (4) is equipped with speed-increasing gear; Described axle system (4) is the common axis system of inertia electric simulation and inertia mechanical analogue, transmits mechanical inertia to indexing mechanism (2).

4. space station according to claim 1 indexing mechanism high temperature performance proving installation, is characterized in that, described axle system (4) is provided with sensor and signal picker, collection signal, be aggregated into electric device, process and analytic signal, obtain the performance parameter of indexing mechanism.

5. space station according to claim 1 indexing mechanism high temperature performance proving installation, it is characterized in that, described flywheel (5) one-piece construction is combined type, bottom is provided with the different balancing weight of quality, simulate different mechanical inertia, electric cylinder (7) mounts and dismounts the balancing weight property entered.

6. space station according to claim 1 indexing mechanism high temperature performance proving installation, is characterized in that, described flywheel (5) supports the inner motor being provided with electric inertia simulation.

7. space station according to claim 1 indexing mechanism high temperature performance proving installation, it is characterized in that, described flywheel (5) entirety is placed on air floating platform (6), air floating platform (6) air supporting support flying wheel (5), simulation space weightlessness.

8. space station according to claim 1 indexing mechanism high temperature performance proving installation, it is characterized in that, described electrical control (10) is provided with switch board, the sensor installed with axle system (4) and signal picker are connected, control and collection signal, and with single measurement equipment interactive product information.

9. space station according to claim 1 indexing mechanism high temperature performance proving installation, it is characterized in that, the ratio of length is: long: wide: height=9420:5055:8364.

10. space station according to claim 1 indexing mechanism high temperature performance proving installation, it is characterized in that, the ratio of the diameter of described flywheel (5) and the length and width of supporter (3) is: flywheel diameter: supporter is long: supporter is wide=and 6550:5600:5600.