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US 12,442,350 B2Granted
Small satellite propulsion system utilizing liquid propellant ullage vapor
AssigneeThe Aerospace Corporation
InventorBrandie L Rhodes
Life of this patent
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Abstract
A novel approach provides a small satellite propulsion system that uses vapor to generate thrust for the small satellite. The vapor naturally sits on top of liquid propellant(s), which are stored within a propellant tank. The vapor may flow from the propellant tank and through a membrane to interact with a reacting surface to generate thrust.
Claims24
An apparatus, comprising:
- a propellant tank comprising liquid propellant with a reactive vapor phase,
- a catalyst located downstream of the propellant tank along a vapor flow path, wherein
- the propellant tank is configured to be selectively exposed to the pressure of space, generating a pressure differential causing a flow of vapor from the propellant tank and through a valve, a membrane, a collection of tubes, or a combination thereof,
- to interact with the catalyst to generate thrust while maintaining the liquid propellant in the propellant tank;
- and
- a propellant management device configured to prevent the liquid propellant from escaping the propellant tank and propagating through the apparatus.
3 more elements
An apparatus, comprising:
- a first propellant tank comprising liquid propellant having a reactive vapor phase;
- a catalyst located downstream of the propellant tank along a vapor flow path;
- a valve, when open, causes the reactor vapor phase to be pulled from the first propellant tank and flow through a membrane to interact with the catalyst to generate thrust, wherein the first propellant tank is configured to be selectively exposed to the pressure of space, generating a pressure differential causing a flow of vapor from the first propellant
- tank and through the valve, the membrane, a collection of tubes, or a combination thereof, to interact with the catalyst to generate thrust while maintaining the liquid propellant in the first propellant tank;
- and
- a propellant management device configured to prevent the liquid propellant from escaping the first propellant tank and propagating through the apparatus.
3 more elements
An apparatus, comprising:
- a first propellant tank comprising liquid propellant having a reactive vapor phase;
- a catalyst located downstream of the first propellant tank along a vapor flow path;
- a second propellant tank comprising a second propellant, wherein
- the reactive vapor phase and the second propellant is mixed prior to passing through a membrane, and
- the first propellant tank is configured to be selectively exposed to the pressure of space, generating a pressure differential causing a flow of vapor from the first propellant tank and through a valve, the membrane, a collection of tubes, or a combination thereof, to interact with the catalyst to generate thrust while maintaining the liquid propellant in the first propellant tank;
- and
- a propellant management device configured to prevent the liquid propellant from escaping the first propellant tank and propagating through the apparatus.
4 more elements
An apparatus, comprising:
- a first propellant tank comprising liquid propellant having a reactive vapor phase with a vapor pressure of less than 1 atmosphere at 25 degrees Celsius;
- a second propellant tank comprising a second propellant, wherein
- the reactive vapor phase and the second propellant is mixed prior to passing through a membrane, and
- the reactive vapor phase is pulled without pulling or pushing the liquid propellant from the first propellant tank and through a valve and the membrane by way of a pressure differential, the pressure differential being generated between the vapor pressure of the propellant and space;
- and
- a propellant management device configured to prevent the liquid propellant from escaping the propellant tank and propagating through the apparatus.
3 more elements
Dependencies are inferred from the claim text.