Multimode propulsion system
Systems and methods for a multimode propulsion system (MMPS) are presented. The MMPS includes a chemical thruster, an electric thruster, and a shared propellant tank. The MMPS further includes a propellant decomposition chamber that transforms, via a catalytic and/or electrolytic process, the propellant from the tank into vapor form for use as gas propellant by the electric thruster. The electric thruster can be configured for targeted ionization of one or more constituent species present in the vapor form of the propellant. Flow activation/control from the tank to the chemical and electric thrusters is provided by a fluidic feed system. The branches include a check valve and a pressure regulator in series connection. A normally closed squib valve prevents propellant flows/leaks from the tank to either the chemical or the electric thrusters when the MMPS is not in operation.
1. A multimode propulsion system, comprising:
a propellant tank configured to contain a liquid propellant;
a chemical thruster configured for operation with the liquid propellant;
an electric thruster configured for operation with a vaporized form of the liquid propellant;
a propellant decomposition chamber configured to transform the liquid propellant into the vaporized form of the liquid propellant, the propellant decomposition chamber comprising a vaporization zone configured to perform the catalytic process and/or the electrolytic process, and a vapor storage zone configured to store the vaporized form of the liquid propellant;
an additional vapor storage zone arranged between the propellant decomposition chamber and the electric thruster, and
a propellant feed system configured to provide flow paths for the liquid propellant and the vaporized form of the liquid propellant between the propellant tank, the chemical thruster, the electric thruster and the propellant decomposition chamber,
wherein an inner volume of the additional vapor storage zone is larger than an inner volume of the vapor storage zone.
2. The multimode propulsion system of claim 1 , wherein:
the propellant decomposition chamber is configured to transform the liquid propellant into the vaporized form via a combination of a catalytic process and/or an electrolytic process.
3. The multimode propulsion system of claim 1 , wherein:
the vaporized form includes a single species gas.
4. The multimode propulsion system of claim 3 , wherein:
the electric thruster is configured for targeted ionization of one species of the multiple species gas.
5. The multimode propulsion system of claim 1 , wherein:
the vaporized form includes multiple species gas.
6. The multimode propulsion system of claim 1 , further comprising:
a propellant switch/valve system that is configured to selectively activate flow of the liquid propellant from the propellant tank in a direction of the chemical thruster and the propellant decomposition chamber.
7. The multimode propulsion system of claim 6 , wherein:
the propellant switch/valve system includes a normally closed squib valve.
8. The multimode propulsion system of claim 7 , wherein:
the propellant switch/valve system further includes a liquid latch valve and a gas check valve in series connection between the normally closed squib valve and the propellant decomposition chamber, and
the gas check valve is configured to prevent gas leak from the propellant decomposition chamber in a direction of the squib valve.
9. The multimode propulsion system of claim 6 , wherein the propellant feed system comprises:
a first flow path coupled between the propellant switch/valve system and the chemical thruster that is configured to control flow of the liquid propellant to the chemical thruster, and
a second flow path coupled between the propellant decomposition chamber and the electric thruster that is configured to control flow of the vaporized form of the liquid propellant to the electric thruster.
10. The multimode propulsion system of claim 9 , wherein:
each of the first and second flow paths includes a check valve and a pressure regulator in series connection.
11. The multimode propulsion system of claim 10 , wherein:
each of the first and second flow paths includes a filter.
12. The multimode propulsion system of claim 1 , wherein:
the electric thruster is an electrodeless electric thruster that is configured to ionize the vaporized form of the liquid propellant via inductive heating and produce a primary source of thrust by ambipolar acceleration of resulting ions.
13. The multimode propulsion system of claim 12 , wherein:
the thrust produced by the ambipolar acceleration of the resulting ions is in a range from 5 millinewtons (mN) to 10 mN.
14. The multimode propulsion system of claim 13 , wherein:
a specific impulse provided by the electric thruster is in a range from 400 seconds to 800 seconds.
15. The multimode propulsion system of claim 13 , wherein:
a specific impulse provided by the electric thruster is greater than 800 seconds.
16. The multimode propulsion system of claim 1 , further comprising:
an auxiliary tank configured to contain a liquid propellant additive for operation of the chemical thruster; and
an auxiliary feed system configured to provide a flow path for the liquid propellant additive between the auxiliary tank and the chemical thruster.
17. The multimode propulsion system of claim 1 , further comprising:
additional one or more chemical thrusters configured for operation with the liquid propellant; and
additional one or more electric thrusters configured for operation with the vaporized form of the liquid propellant;
wherein the flow paths of the propellant feed system are shared for provision of:
the liquid propellant to the chemical thruster and the additional one or more chemical thrusters, and
the vaporized form of the liquid propellant to the electric thruster and the additional one or more electric thrusters.
18. The multimode propulsion system of claim 17 , wherein:
each of the additional one or more chemical thrusters or electric thrusters are configured for independent operation.
19. The multimode propulsion system of claim 17 , wherein:
any two or more of the additional one or more chemical thrusters or electric thruster are configured for operation at a same time.
20. The multimode propulsion system of claim 1 , wherein the liquid propellant comprises at least one of:
high purity hydrazine (HPH); AF-M315E (ASCENT); high test peroxide (HTP); nitrogen tetroxide (NTO), ammonium dinitramide (AND); LMP-103S; red fuming nitric acid (RFNA); nitrous oxide (N2O); mono-methyl-hydrazine (MMH); ethane (C2H6); or kerosene.
21. The multimode propulsion system of claim 1 , wherein:
the vaporization zone comprises at least one of: a propellant catalyst; a joule heating element; or discharge electrodes.
22. A method for operating a multimode propulsion system, comprising:
providing a chemical thruster;
providing a liquid propellant for operation of the chemical thruster;
storing the liquid propellant in a storage tank;
providing an electric thruster;
during a first mode of operation of the multimode propulsion system:
feeding the liquid propellant to the chemical thruster for producing a first thrust; and
during a second mode of operation of the multimode propulsion system:
decomposing the liquid propellant into a vaporized form;
storing the vaporized form of the liquid propellant into a first vapor storage zone;
feeding the vaporized form of the liquid propellant from the first vapor storage zone to a second vapor storage zone; and
feeding the vaporized form of the liquid propellant from the second vapor storage zone to the electric thruster for producing a second thrust,
wherein the electric thruster is an electrodeless electric thruster that is configured to ionize the vaporized form of the liquid propellant via inductive heating and produce a primary source of the second thrust by ambipolar acceleration of resulting ions, and
wherein an inner volume of the second vapor storage zone is larger than an inner volume of the first vapor storage zone.
23. The method according to claim 22 , wherein:
the decomposing of the liquid propellant is performed prior to the producing of the second thrust.
24. The method according to claim 22 , wherein:
the decomposing of the liquid propellant is performed concurrently to the producing of the second thrust.