A take-off-landing-movement implementation method for a lunar probe
An implementation method and detector technology, applied in attitude control and other directions, can solve complex problems, and water ice is likely to exist in the permanent shadow area at the bottom of the impact crater, limited terrain adaptability, and undetectable, etc., to achieve rapid large-scale Range transfer detection, realize the effect of light miniaturization, fast and large-scale transfer
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[0027] A take-off-landing-movement realization method for a lunar probe, the method includes a low temperature resistance design method, a flight dynamic design method, a miniaturization design method and a movement design method:
[0028] Among them, the design method of low temperature resistance includes:
[0029] Twelve cylindrical gaps with a diameter of 5mm and a height of 20cm are reserved on the 20cm*30cm flat panel structure wall, and filled with ammonia thermal control medium to realize the temperature control of the equipment;
[0030] The passive temperature control part of the outer shell of the lunar surface detector is covered with ten layers of double-sided aluminized polyimide film. In the state, the adjacent aluminized surfaces are not in contact.
[0031] Flight dynamics design methods include:
[0032] When the mass of the lunar probe is 180-220Kg, the configuration of the lunar probe is a pyramid, the number of A-type thrusters is eight, the thrust of A-...
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