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5 Thermal Control Technology of Lunar Lander
Fig. 5.20 Diagram of driving force simulation
5.6.5 Flight Testing on Orbit
On December 2, 2013, the Chang’E-3 lunar lander was launched in the Xichang
Satellite Launch Center. After LTO and circumlunar flight, the probe was landed on
lunar surface and the lunar lander was successfully separated with the lander. During
the entire flight and separation process, the thermal control subsystem of the lunar
lander worked normally. The characteristic of VCHP was consistent with the expectation (the temperature change curve in circumlunar phase is shown in Fig. 5.22).
The high-temperature heat shield effectively protected the safety of structure and
instruments of the lunar lander during LOI and landing process (the temperature
change curve of the heat shield itself is shown in Fig. 5.23). The lunar lander had
been working on lunar surface for several lunar days. It had passed multiple hibernation, awakening and lunar eclipses. After wakened up, the instruments of the lunar
lander were operated normally, which proved that the two-phase fluid loop, VCHPs,
RHUs and the thermal control subsystem worked normally. The temperature change
of the two-phase fluid loop during hibernation is shown in Fig. 5.24. The temperature of instruments and structure in all phases met the requirements. During the
lunar daytime, scientific payloads such as lunar observatory were operated normally
5 Thermal Control Technology of Lunar Lander
Fig. 5.20 Diagram of driving force simulation
5.6.5 Flight Testing on Orbit
On December 2, 2013, the Chang’E-3 lunar lander was launched in the Xichang
Satellite Launch Center. After LTO and circumlunar flight, the probe was landed on
lunar surface and the lunar lander was successfully separated with the lander. During
the entire flight and separation process, the thermal control subsystem of the lunar
lander worked normally. The characteristic of VCHP was consistent with the expectation (the temperature change curve in circumlunar phase is shown in Fig. 5.22).
The high-temperature heat shield effectively protected the safety of structure and
instruments of the lunar lander during LOI and landing process (the temperature
change curve of the heat shield itself is shown in Fig. 5.23). The lunar lander had
been working on lunar surface for several lunar days. It had passed multiple hibernation, awakening and lunar eclipses. After wakened up, the instruments of the lunar
lander were operated normally, which proved that the two-phase fluid loop, VCHPs,
RHUs and the thermal control subsystem worked normally. The temperature change
of the two-phase fluid loop during hibernation is shown in Fig. 5.24. The temperature of instruments and structure in all phases met the requirements. During the
lunar daytime, scientific payloads such as lunar observatory were operated normally