The invention discloses a nitrogen gas cooling type cooling water device used for a space environment simulation appliance. The nitrogen gas cooling type cooling water device comprises the space environment simulation appliance, a gas inflow pipeline, a bypass emptying valve, a bypass emptying pipeline, a gas inflow valve, a booster fan, a refrigerating machine, an inner circulation water outflowpipe, an inner circulation pump, an inner circulation water return pipe, a water flow stirrer, a water tank temperature sensor, a gas outflow valve, a gas outflow pipeline, a heat exchanger, a water tank, a water outflow temperature sensor, an outer circulation water outflow pipe, an outer circulation pump, an outer circulation water return pipeline and a water use appliance. The heat exchanger, the water flow stirrer and the water tank temperature sensor are located in the water tank, the two ends of the heat exchanger are connected with the gas inflow pipeline and the gas outflow pipeline, the gas inflow valve and the booster fan are sequentially installed on the gas inflow pipeline, and the gas outflow valve is installed on the gas outflow pipeline. Low-temperature nitrogen gas emittedby the space environment simulation appliance is used as a cold source to cool cooling water, the resource use rate can be greatly increased, meanwhile, the refrigerating machine is reserved as an auxiliary refrigerating appliance, and it is guaranteed that a system can normally work when the cooling capacity of the nitrogen gas is insufficient.

Nitrogen gas cooling type cooling water device used for space environment simulation appliance

The invention discloses a transient-state temperature simulation system and method under the low air pressure environment. Simulation of a temperature curve of the low air pressure environment is achieved under the ground environment. The system is composed of a compressor, a heat exchanger, an air regulator, an electric furnace, a heat sink and a vacuum container. The adjustable environment temperature within 150K to 350k range is achieved in the vacuum container by controlling the temperature of the heat sink. The simulation method is correspondingly disclosed as well. Transient-state temperature simulation under the low air pressure environment is achieved, and accurate temperature control of transient-state temperature simulation at the corresponding low air pressure under the condition of convective heat transfer is achieved.

Transient-state temperature simulation system and method under low air pressure environment

The invention discloses a waveguide ring mold vacuum container with a concave spherical-crown gate. The waveguide ring mold vacuum container comprises a horizontal cylinder, the concave spherical-crown gate, a temperature control baseboard, a pre-tightening hand wheel, a waveguide connector, a gate-wheel-type support, a ground guide rail, a fork-shaped mechanism and a container inner guide rail, the horizontal cylinder and the openable concave spherical-crown gate form a closed space, the pre-tightening hand wheel is utilized for conducting vacuum sealing and pressing on the horizontal cylinder and the openable concave spherical-crown gate, and the waveguide connector is reserved on the gate; the gate is supported by the gate-wheel-type support and is manually pushed to move transversely to be opened and closed along the ground guide rail; the fork-shaped mechanism has the up-and-down lifting fine adjusting function, the upper part of the fork-shaped mechanism supports the temperaturecontrol baseboard and a to-be-tested test piece, one end of the fork-shaped mechanism moves transversely along the container inner guide rail through idler wheels, and the other end of the fork-shapedmechanism is detachably connected with the concave spherical-crown gate to obtain translation thrust. The large-caliber concave spherical-crown high-vacuum negative pressure tolerance gate is adopted, the weight is reduced, and the short-distance requirement for the waveguide connector of the gate to be close to the test piece on the temperature control baseboard to the greatest extent during wireless testing is met, the situation that potential safety hazards are caused by yielding and failure of the gate under the external pressure of the atmosphere, the shortest distance for transmission of electromagnetic waves can be achieved, and the position of the satellite test piece can be manually adjusted in multiple dimensions by one person.

Waveguide ring mold vacuum container with concave spherical-crown gate

The invention provides a temperature and pressure monitoring system of a condenser, belonging to the technical field of condensation test and solving the technical problem that the existing condensation test system cannot realize the study on effectiveness of pressure and temperature on the condensation effect of the condenser. The temperature and pressure monitoring system of a condenser comprises a horizontal condenser, wherein the top of the horizontal condenser is provided with a plurality of pressure detecting ports spaced apart in the longitudinal direction, one sides of the pressure detecting ports are provided with temperature detecting ports, temperature sensors for detecting internal temperature are disposed in the temperature detecting ports, measuring tanks with the number corresponding to that of the pressure detecting ports are spaced apart below the horizontal condenser in the longitudinal direction, the tops of the measuring tanks are connected to the bottom of the horizontal condenser, a detecting valve for detecting air pressure is provided on the outer side of the horizontal condenser, and the plurality of pressure detecting ports are connected to the detecting valve. The system provided by the invention facilitates systematic research on the working performance of the horizontal condenser through control variables.

Temperature and pressure monitoring system of condenser

The invention discloses a lifting type heat sink assembly for a space environment simulator. The lifting type heat sink assembly comprises a top heat sink, a detachable liquid inlet pipeline, a detachable liquid outlet pipeline, a fixed winching system, a lifting hanger, an upper connecting device and a control system, wherein the upper part of the heat sink is hung on the lower part of the lifting hanger on the inner wall of an upper sealing head of a space environment simulator container through a heat sink hanging point and ascends or descends along with the hanger, the fixed winching system is composed of an electric ring chain hoist and a mounting portal, the electric ring chain hoist is arranged at the top of the container through the mounting portal and drives the lifting hanger toascend and descend, and thus a hanging hook arranged on the ring chain hoist penetrates through a top flange of the container to enter the space environment simulator container. The lifting type heatsink assembly is simple in structure, the detachable liquid inlet pipeline and the detachable liquid outlet pipeline are adopted, thus the heat sink moves, and when the heat sink moves to the corresponding fixed position, connection of the heat sink and an external pipeline is restored.

Lifting type heat sink assembly for space environment simulation

The invention discloses a temperature and pressure adjusting device for a spacecraft environment test. The temperature and pressure adjusting device comprises a vacuum container, a container gate, a heat sink, a control cabinet, a refrigerator and the like. The heat sink is placed in the vacuum container. The heat sink and the refrigerator are connected through a refrigerating pipeline. A refrigerating valve is connected with the middle of the refrigerating pipeline. A heat exchanger communicates with the refrigerating pipeline through a heat exchanger pipeline. The vacuum container and a vacuum pump are connected through a vacuum pipeline. A vacuum valve is connected with the middle of the vacuum pipeline. A gas supplying pipeline is connected with the vacuum container. A gas flow controller is installed on the gas supplying pipeline. Gas in the gas supplying pipeline firstly enters the heat exchanger for heat exchanging before entering the vacuum container. A nitrogen pipeline and anair pipeline are arranged in parallel. A nitrogen source is connected with the gas supplying pipeline through the nitrogen pipeline. An air source is connected with the gas supplying pipeline throughthe air pipeline. An air dryer is connected to the middle of the air pipeline. The control cabinet is connected with the refrigerator, the refrigerating valve, the vacuum pump, the vacuum valve and the gas flow controller by controlling cables.

Temperature and pressure adjusting device for spacecraft environment test

The invention discloses a test method for accelerating the temperature rising and lowering in a temperature control test of a low-pressure chamber At the early stage of the test, air in a test chamber is replaced by drying gas; that is, the test chamber is vacuumized by using a pressure control system and then re-pressing is carried out by using the drying gas; and the ambient temperature in thetest chamber is controlled by using a temperature control heat sink at a normal pressure and a pressure control system is used for adjust the environmental pressure in the test chamber, thereby reducing the time of low-pressure temperature control test Therefore, the time of the low-pressure temperature control test is shortened

Test method for accelerating temperature rising and lowering in temperature control test of low-pressure chamber

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Temperature and pressure adjusting device for spacecraft environment test

Test method for accelerating temperature rising and lowering in temperature control test of low-pressure chamber