What is the typical specification of a continuous thrust spacecraft propulsion system?
Answers
10kN is a very high thrust level. I don't know if such a level is available with a classical chemical engine. Usually the Isp of chemical engines is close to 300 s
The modulus of the acceleration produced by the thrust F/m depends on the mass m that varies according to:
dm/dt = -F/g0/Isp where g0 = 9.80665 m/s^-2
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Explanation:
The maximum total acceleration is about 5 m/s^2 and the specific impulse is 1000 sec
In my case, the mass of spacecraft is 2000 kg and the required acceleration is approximately 5 m/sec^2. So, it needs 10 kN of thrust. The mission time is approximately 10*T where T is the period of the target orbit (circular orbit with 3000 km altitude). The question is:
What kind of propulsion system should be used for this mission? Chemical? What is the appropriate Isp? I have chosen 1000 sec. Is that practical (as I know the Isp for regular chemical propulsion system is approximately 300 sec)?