Microgravity in low earth orbit with continuous electric propulsion
Systems and methods for achieving pristine microgravity in low earth orbit (LEO) using electric propulsion. Long-duration, low thrust, electric thrusters provide a constant thrust force for a pristine microgravity environment within a given volume of a space vehicle experiencing drag forces in LEO. Large space vehicles in LEO configured to be pressurized for human habitation, for instance having a mass of at least 40,000 kg and an internal volume of at least 400 m 3 , can use the electric propulsion systems and methods to achieve a quasi-steady acceleration less than or equal to 1.0 μg for durations of 180 consecutive days or longer.
1 . A control system for controlling a space vehicle in low earth orbit, the control system comprising:
a propellant storage tank configured to hold propellant;
a plurality of solar electric propulsion thrusters configured to collectively generate a continuous thrust force in a forward direction using electrical power to accelerate the propellant for a time period; and
one or more sensors configured to generate acceleration data related to acceleration of the space vehicle, wherein the control system is configured to adjust the thrust force of the plurality of solar electric propulsion thrusters based on the acceleration data so that the space vehicle maintains a microgravity environment for an entirety of the time period.
2 . The control system of claim 1 , wherein the time period is at least 1800 days.
3 . The control system of claim 1 , wherein the propellant storage tank is configured to hold at least 300 kg of Xenon.
4 . The control system of claim 1 , wherein the thrust force is adjusted such that an acceleration of the space vehicle is maintained at less than or equal to 1.0 μg during the entirety of the time period.
5 . The control system of claim 1 , wherein the space vehicle has an internal volume of at least 400 m 3 configured to be pressurized for human habitation.
6 . The control system of claim 1 , further comprising a solar array configured to generate electrical energy for use by the plurality of solar electric propulsion thrusters.
7 . The control system of claim 6 , wherein the solar array comprises a plurality of solar panels.
8 . The control system of claim 1 , wherein the thrust force is adjusted such that an orbital altitude of the space vehicle is maintained between +/−10 km of a desired orbital altitude during the entirety of the time period.
9 . The control system of claim 8 , wherein the desired orbital altitude is between about 350 km and about 450 km.
10 . The control system of claim 8 , wherein a first derivative of the orbital altitude with respect to time exists over the entirety of the time period.
11 . A method for controlling a space vehicle in low earth orbit, the method comprising:
generating a thrust force on the space vehicle with a plurality of solar electric propulsion thrusters;
receiving data related to acceleration of the space vehicle in response to generating the thrust force;
analyzing the data related to acceleration of the space vehicle in response to receiving the data related to acceleration;
adjusting the thrust force in response to analyzing the data related to the acceleration; and
maintaining a microgravity environment within the space vehicle for an entirety of a time period in response to adjusting the thrust force.
12 . The method of claim 11 , wherein the microgravity environment is maintained within an internal volume of at least 400 m 3 within the space vehicle configured to be pressurized for human habitation, and wherein the space vehicle comprises a total mass of at least 40,000 kg.
13 . The method of claim 11 , wherein maintaining the microgravity environment comprises maintaining a quasi-steady acceleration of less than or equal to 0.1 μg within at least 8 m 3 of an internal volume of the space vehicle, and wherein the time period is at least 180 days.
14 . The method of claim 11 , wherein an orbital altitude of the space vehicle is maintained between +/−10 km of a desired orbital altitude during the entirety of the time period.
15 . The method of claim 14 , wherein a first derivative of the orbital altitude with respect to time exists over the entirety of the time period.
16 . A space vehicle configured to travel in low earth orbit, the space vehicle comprising:
a habitable module having an internal volume of at least 400 m 3 configured to be pressurized for human habitation; and
a control system comprising a plurality of solar electric propulsion thrusters configured to collectively generate a continuous thrust force, wherein the control system is configured to adjust the thrust force of the plurality of solar electric propulsion thrusters such that a microgravity environment is maintained within the internal volume during an entirety of a time period.
17 . The space vehicle of claim 16 , wherein the plurality of solar electric propulsion thrusters comprises a plurality of Hall effect thrusters each having at least 1 kW power output.
18 . The space vehicle of claim 16 , wherein the control system is further configured to adjust the thrust force such that the microgravity environment is maintained with a drag force acting on the space vehicle of at least 0.050 Newtons.
19 . The space vehicle of claim 16 , wherein the plurality of solar electric propulsion thrusters are gimballed.
20 . The space vehicle of claim 16 , further comprising a solar array configured to generate electrical energy for use by the plurality of solar electric propulsion thrusters.