FIELD OF THE DISCLOSURE

The disclosure generally relates to operating a spacecraft and more specifically to sharing energy and propellant resources among thrusters of different types.

BACKGROUND

With increased commercial and government activity in the near space, a variety of spacecraft are under development, for various missions. For example, some spacecraft may be dedicated to delivering payloads (e.g., satellites) from one orbit to another. In such orbital transfer missions, the spacecraft generally requires a thruster that consumes a propellant in order to achieve mission objectives.

SUMMARY

This disclosure generally relates to improving efficiency of using a propellant and collected solar energy in a spacecraft system. The propellant and/or the energy may be shared between two thrusters, operating according to different propulsion techniques. The system may use the propellant to store, direct, or transform collected solar energy.

In one embodiment, a propulsion system operating in a spacecraft includes a power system configured to collect solar energy, a first thruster operating according to a first propulsion technique, and a second thruster operating according to a second propulsion technique. A controller of the propulsion system is configured to control supply of the solar energy collected by the power system to the first thruster and the second thruster. In another embodiment, a propulsion system operating in a spacecraft comprises: a tank storing propellant, a first thruster fluidicly coupled to the tank and operating according to a first propulsion technique, and a second thruster fluidicly coupled to the tank and operating according to a second propulsion technique. A controller of the propulsion system is configured to control supply of the propellant from the tank to the first thruster and the second thruster.

In yet another embodiment, a system for storing solar energy in a spacecraft includes a tank storing propellant; a power system configured to (i) collect solar energy and store at least a portion of the collected solar energy in the propellant in a vaporized state, and (ii) use a first portion of the vaporized propellant to generate electric energy; and a thruster configured to consume a second portion of the vaporized propellant to generate thrust.

Still in another embodiment, a propulsion system operating in a spacecraft includes a tank storing propellant, a fuel cell fluidicly coupled to the tank and configured to operate using a first portion of the propellant as a working fluid, and a thruster fluidicly coupled to the tank and configured to consume a second portion of the propellant to generate thrust.

