Outer Space Simulation Test Chamber

Introduction:

The Outer Space Simulation Test Chamber and Thermal Vacuum Test System of Grande Electronics Technology Limited are applied to simulate the outer space,space, environmental testing for satellite products . The temperature range could reach -180℃ ~+200 ℃,and Max. pressure to 1*10 -6Pa. Even it could be installed an artificial sun to simulate the light environment in space. Our company adopts the internationally advanced heat sink temperature Cutting-edge Heat sink temperature technology control,transfer the temperature,and make the uniformity more excellent, can meet the U.S. army standard space test standards.

Main Technology Parameters:

(1) Ultimate vacuum: better than 1×10 ^-5Pa

(2) Working vacuum:better than 1.3×10 ^-4Pa

(3) Temperature range:  -180℃~200℃

(4) Temperature Accuracy:±0.5℃

(5) Temperature of the heat sink: ≤100K

(6) Uniformity of heat sink temperature: ≤±5℃

(7) Black paint for inner wall of heat sink, Absorption of sunlight by heat sink≥0.95 Hemispheric emittance≥0.90, The outer surface is equipped with radiation shield.

(8) Infrared heating heat flux density 100W/m2~1800W/m2

(9) With vacuum degree and temperature measurement function

Product Detail:

The vastness of space is both familiar and strange to human. Familiar, because manned space activities have been carried out for decades, man has been into space hundreds of times. Strange, because the space environment is so complex, that every manned space activities, is still full of numerous changes and great risks. Facing the complicated and changeable environment of manned spaceflight, the astronauts can successfully complete the mission of manned spaceflight only when they make full preparation of test and training on the earth. Ground test and training cannot be separated from simulation technology simulation equipment.As to understand the simulation technology and simulation equipment, first of all should understand the manned space environment.

2,Solar irradiation environment and simulation

The sun radiates enormous energy into space all the time. The wavelengths of sunlight cover a wide area from10-14 M(γgamma rays) to 14 meters (gamma rays) to 104 meters (radio waves), Different wavelengths of sunlight radiates different amounts of energy. Visible light radiates the most energy. With visible and infrared radiation accounting for more than 90 percent of the sun's total radiation energy.

In the orbit flight, the spacecraft and the Eva spacesuit mainly receive three parts of radiation energy: Energy from the sun's visible and infrared radiation ,the earth reflects energy from the sun and heat from the earth's atmosphere. The energy absorbed by spacecraft and Eva spacesuit affects its temperature and distribution. The energy absorbed depends on the surface material characteristics of its structure and shape and flight trajectory. At wavelengths less than 300 nanometers, the radiation energy is a tiny fraction of the sun's total, However, the optical properties of the material surface will be greatly changed. The ultraviolet radiation effects are mainly reflected by photochemical effects and photoquantum effects.

The solar radiation simulation test can simulate the solar spectrum thermal effect and solar spectrum photochemical effect produced by solar radiation environment on spacecraft and Eva spacesuit. If only the thermal effect is simulated, it is called outer space heat flow simulation. There are two ways to simulate heat flow outside space, one is the in-jet simulation method, also known as solar simulation method; The other is absorption heat flow simulation, also known as infrared simulation. The solar simulation method should be used for the specimen with complex shape and surface material; If the shape is regular and the surface material is single, infrared simulation method can be used. If the photochemical effect of ultraviolet irradiation environment needs to be simulated, the ultraviolet irradiation simulator can be used.

3,Space cold black environment and simulation

The equivalent temperature of the space is about 3K and the thermal absorption rate is 1, It can be thought of as an ideal black body without thermal radiation or reflection . When there is no solar irradiation, space is a completely cold and dark space . In this cold and dark environment, all the heat energy emitted by the object is completely absorbed .Therefore, it is also called heat sink environment. The cold black environment has great influence on the thermal performance of spacecraft and Eva spacesuit, To develop spacecraft and Eva spacesuit, it is necessary to conduct thermal vacuum and thermal balance tests in the simulated cold and black environment. Verify whether its thermal design and thermal performance meet the requirements

In order to simulate the space cold and dark environment, Components usually made of aluminum, copper or stainless steel. The inner surface is coated with special black paint with high absorbency and liquid nitrogen is injected into the structure. This device is called heat sink. At present, all the spaceflight countries use this kind of heat sink with liquid nitrogen as the cold source to simulate the space cold and black environment. Because the thermal analysis theory calculation and the test data analysis indicated, heat sink with 77K liquid nitrogen temperature and absorption rate above 0.9 was used to simulate the space cold and black environment, and the simulation error was only about 1%. It can fully meet the requirements of simulation test of cold and black environment. In addition, the pursuit of lower temperatures is unnecessary and will greatly increase the technical difficulties and investment in analog equipment.

Application:

The main components of space vehicles and other products, Performance test and reliability test are carried out under the combined action of thermal vacuum environment (hot and cold temperatures )in the thermal vacuum environment simulation equipment.

The vacuum environment test equipment is composed of the vacuum chamber,heat sin,Infrared heating cage,Electrical control and environmental parameter testing system.

Main technical parameters:

Vacuum container

The empty container is a horizontal cylinder with an open gate at one end. Effective container size:φ800×1200mm.length of straight flange 1200mm

Vacuum pumping system

vacuum pumping system divided into molecular pump set coarse pumping pump for oil pump and valve pipeline and other accessories

Room temperature and space load limit pressure : ≤6.7×10 -5Pa(Need to be roasted)

Low temperature no load limit pressure(≤100K): ≤2.0×10 ^-5Pa.(Need to be roasted)

Working vacuum : (The product is aviation plug-in) ≤5.0×10 ^-5Pa; (Need to be roasted)

Pump-down time: 30min~1h

Cold light; Surface temperature of heat sink:5.0×10 ^-5Pa,Start with pre-pumping≤20min;

Cold light; Surface temperature of heat sink: 5.0×10 ^-5Pa,Start with pre-pumping≤30min;

Heat sink:

effective size φ450×900mm length of straight flange

Surface temperature of heat sink : ≤200K

Homogeneity: ±5℃

Surface temperature≤+130℃,Teperature control precision,±3℃

Sample temperature range:limiting temperature -70℃~+130℃.

Control accuracy:Error ≤±1℃.

Heating rate:≥2℃/min,

Cooling rate:≥2℃/min;

Low-temperature system:mechanical refrigeration

Uninterrupted working time of equipment:more than 20 days

Separate grounding of equipment,Grounding resistance is not greater than

A power supply flange is left on the side of the test box,Pin number ≥55 core,Meet the requirement of 1000V withstand voltage 5mA leakage current

System configuration and program description.

Specification: