DESIGN AND STUDY OF HEAT PIPES FOR SPACE THERMAL SUBSYSTEM

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1 Thermal and Power Department, Heat Pipes Laboratory DESIGN AND STUDY OF HEAT PIPES FOR SPACE THERMAL SUBSYSTEM V. Kravets, S. Khairnasov, B. Rassamakin, A. Snurnitsyn, A. Rassamakin, E. Alekseik, O. Alekseik, 1

2 Thermal and Power Department, Heat Pipes Laboratory Heat Pipes Laboratory (HPL KPI) has its cradle from the Thermal and Power Engineering Department of National Technical University of Ukraine Kiev Polytechnic Institute since Scientific and technological base for efficient designing and fabrication of advanced heat transferring devices Heat Pipes (HPs) was founded by the personnel of the named Laboratory. There more than HPs modifications were developed and applied in the various branches of industry. Today Laboratory is held by 20 staff workers that include 2 doctors and 10 candidates of science (PhD). Usual about 4 PhD students work at Laboratory. Annually about 10 students take part in R&D works. 2

3

4 Thermal and Power Department, Heat Pipes Laboratory 1. Design and production heat pipes and thermal stabilization systems based on heat pipes for space satellites (Design office CSKB Progress (Samara, Russia), Design office Yugnoe (Ukraine), Thales Alenia Space (France), DLR (Germany)) 4

5 Heat Pipes With Axial Grooves For Space Engineering Technical features: Type: axially grooved heat pipes with constant thermal resistance Material: АД-31 aluminum alloy (6060 aluminum alloy in accordance with AMS 4116 US standard) Heat pipes thermal resistance, K/W Operation temperature range, K: Working liquid (heat carrier): ammonia, water, propylene, alcohols, acetone, Freon, nitrogen, methane, ethane Life-time: up to 20 years Configuration: straight or 3d-curved Fin s width: 30 mm, for АС-КРА 7.5 Р mm Performances of heat pipes made of standard profiles (ammonia) Performances of heat pipes made of standard profiles (ammonia) 5

6 Thermal and Power Department R&D Project Design, production and tests heat pipes for cooling systems of Space Satellite BIRD for DLR (Germany) Information from 6

7 Thermal and Power Department INTAS Project Production and tests aluminium profile heat pies. Partners: Thales Alenia Space, Euro Heat Pipe, Ecole Nationale Supérieure Mécanique et Aérotechnique Heat Pipes Laboratory 7

8 Thermal and Power Department, Heat Pipes Laboratory 2. Design, production and tests honeycomb panels based on heat pipes for space satellites 1 covering; 2 film glue; 3 HP; 4 honeycomb foil; 5 foam glue, 6 mounting bush 8

9 Simulation of HCP With 2 Built-in HPs Test Sample Parameters HCPs dimensions х м; number of devices 2 pieces; number of HPs 2 pieces.; total heat emission from the devices 48 W; blackness degree 0.92; absorption coefficient 0.96; ambient temperature 4 К. 9

10 Thermal and Power Department, Heat Pipes Laboratory 3. Design, production and tests heat pipes for Space Rocket (example - CYCLON-4) Heat Pipes Laboratory 10

11 4 DESIGN AND STUDY OF HEAT PIPES FOR SPACE THERMAL SUBSYSTEM Two heat pipes (HPs) were designed for transportation of the heat from electronics components to the radiator during operative phases of The Mobile Asteroid Surface Scout (MASCOT). MASCOT is a lander built by DLR, in collaboration with CNES and JAXA for JAXA s Hayabusa-2, with aim to provide a scientific mission to study the asteroid JU3. HPs were designed, made and tested in Scientific Applying Firm Thermal Technology and Heat pipe laboratory of National Technical University of Ukraine KPI. Information from 11

12 View of copper heat pipes - type A and type B is shown on figure. Inner surface of HPs were coated with metal-fibrous structure (wick) with porosity 84%. It was made of copper fibre with diameter of m and length of 7 mm. Methanol was used as heat carrier. Overall length of HP type A was 482 mm and of HP type B was 428 mm. 12

13 13

14 Test programme included: - operation characteristics, - start-up, - vibration, - thermal cycling, - thermal shock, - hot burst, - life time, - pressure cycle and burst pressure tests. 14

15 OPERATION CHARACTERISTICS TEST and START-UP IN VACUUM CHAMBER Experimental setup for investigating heat pipes operation characteristics under vacuum consists of heating and cooling systems, system of temperature control and system of vacuum creating and keeping HP heat pipe; H1, H2 heater; LAT1, LAT2 autotransformers; Wm wattmeter; T1-T8 thermocouples; C condenser; DS Dewar vessel with liquid Nitrogen; RV regulation vessel; VC vacuum chamber; ADC analog-digital converter; PC computer; IP installation platform; LS leveling screws 15

16 Heat pipes were investigated at next conditions: frequency range, Hz g, m/s 2 Time, min , , , , , , ,5 Shock stress g, m/s 2 number time, ms

17 THERMAL CYCLING Thermal cycling test were provided in camera of extra low temperatures Tabai ESPEC MC71. During experiments it was: - average temperature in camera at cold regime: C; - average heat pipe transport zone temperature at cold regime: C; - average temperature in camera at hot regime: 75.6 C; - average heat pipe transport zone temperature at hot regime: 60.5 C; 17

18 Thermocycling diagrame T1 temperature in chamber; T2, T3 heat pipes transport zone temperature 18

19 LIFE TIME Life time tests were provided during 100 hours. It was determined that heat transfer characteristics of heat pipe didn't change during indicated time. HPA, HPB heat pipe; HA, HB heater; WA, WB wattmeter; LATA, LATB laboratory autotransformer; T1A T8A, T1B T8B thermocouples; TH laboratory thermometer; TA thermo-anemometer; F fan; M maze; AT aerodynamic tube; ADCA, ADCB analog-digital converter; IF interface; PC - computer 19

20 X-RAY X-rays investigations had shown that capillary-porous structure was sintered to the casing uniformly. On bends porous structure was not deformed and not plugged up cross section for vapor flowing. X-ray picture of heat pipe 90 -bend X-ray picture of heat pipe S-bend 20

21 Dependence of heat conductivity from saturation temperature for HP type A, obtained as a result of primary operational characteristics test, which was provided before all other tests, is shown on figure. HP type B has similar characteristic. Maximum transferred heat power of all tested HPs was 5 10 W. After providing of mentioned above tests, except pressure and burst tests, secondary operational characteristics test was conducted. As it can be seen, operation characteristics changed very slightly. 21

22 CONCLUSIONS Stability of characteristics and its accordance to the operating features of landing module were obtained by using of HP manufacturing procedure, developed in heat pipes laboratory of NTUU KPI, and due to special combination of capillaryporous structure characteristics and physical properties of heat carrier. 22

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