Annular vortex tank valve for rocket motor and configuration in a rocket
AssigneeVaya Space, Inc.
InventorKineo Wallace
Life of this patent
Estimating the term…
Abstract
A rocket engine is provided with a propellant valve controlling the output of a propellant tank. The valve is configured to induce a vortex in the propellant as it passes the propellant valve. Plural rocket engines may be supplied by a single valve, the valve inducing a vortex in the propellant which is then supplied to plural propellant lines configured to enhance the vortex induced by the valve.
Claims14
A rocket comprising:
- plural engines;
- a single propellant tank providing propellant;
- a single propellant valve operatively connected to the single propellant tank and controlling
- the transfer of propellant from the single propellant tank to each of the plural engines;
- each of plural propellant lines extending from the single propellant valve to each of said plural engines, the propellant valve configured to produce an induced vortex around a periphery of the valve with each propellant line supplying the propellant to one of said plural engines in a direction generally tangential with the periphery of the vortex induced within the single propellant valve.
A propellant tank valve for using in a rocket engine, the propellant tank valve being adapted with plural output ports for plural propellant lines for attachment to plural rocket motors, the propellant tank valve being adapted for mounting to a single propellant tank adapted to supply propellant to each of said motors from the single tank,
- the propellant valve being configured to be operatively connected to the single propellant tank and controlling the transfer of propellant from the single propellant tank to plural engines;
- said tank being configured to connect to plural propellant lines, each extending from the propellant valve to one of said plural engines,
- the propellant valve configured to produce an induced vortex around a periphery of the valve with each propellant line supplying the propellant to one of said plural engines in a direction generally tangential with the periphery of the vortex induced within the single propellant valve.
Dependencies are inferred from the claim text.