Solid-propellant-powered maneuvering system for spacecraft
AssigneeUnited States Government, as represented by the Secretary of the Navy
InventorsCharles W. Goddard, John T. Lucas, Paul A. Galvan
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Abstract
An improvement to a variable-pressure solid-propellant-powered maneuvering ystem for spacecraft, enabling the system to operate for longer than one propellant burn time. At least two solid propellant gas generators are connected via a manifold to a plurality of nozzle valve clusters; at least one of the gas generators is connected to the manifold via a sequence valve which isolates that generator from the manifold until such time as it is desired to put that generator into operation.
Claims4
In combination with a solid-propellant-powered maneuvering system for spacecraft having (1) a first gas generator set for providing a hot gas output said first set consisting of at least one gas generator each generator containing solid propellant and having an ignition means responsive to an ignition command, the burn rate of said propellant being directly related to the pressure of said gas output so that the rate of said gas output is directly related to the pressure of said gas output, (2) at least three nozzle valve clusters disposed to be mounted on the spacecraft and radiosymmetrically arranged about the spacecraft roll axis, each nozzle valve cluster having a first and a second high thrust nozzle valve having a corresponding first and second high thrust nozzle attached and fluidly connected thereto the first high thrust nozzle oriented to produce thrust in a direction along and defining a high-thrust-line axis and the second high thrust nozzle oriented to produce thrust in a direction directly opposite to that of the first high thrust nozzle and along said high-thrust-line axis which is spaced from and is parallel to said roll axis, and each nozzle valve cluster also having a first and a second low thrust nozzle valve having a corresponding first and second low thrust nozzle attached and fluidly connected thereto the first low thrust nozzle oriented to produce thrust in a direction along and defining a low-thrust-line axis and the second low thrust nozzle oriented to produce thrust in a direction directly opposite to that of the first low thrust nozzle and along said low-thrust-line axis which intersects said high-thrust-line axis and is perpendicular to a plane containing both said high-thrust-line axis and said roll axis, each nozzle valve having means for individually operating in response to valve commands, (3) a gas conducting manifold fluidly connecting each gas generator of said first gas generator set to each nozzle valve cluster inlet port, (4) a gas pressure transducer fluidly connected to said manifold, and (5) command generating means responsive to guidance command inputs and resposive to pressure feedback from said gas pressure transducer for generating valve commands to individual nozzle valves and for generating ignition commands to individual gas generator ignitors, the improvement which comprises:
- a second gas generator set for providing a hot gas output said second set consisting of at least one gas generator each generator containing solid propellant and having an ignition means responsive to an ignition command, the burn rate of said propellant being directly related to the pressure of said gas output so that the rate of said gas output is directly related to the pressure of said gas output;
- and
- a set of sequence valves equal in number to the number of gas generators of the second gas generator set, each sequence valve uniquely associated with a particular gas generator of said second set and fluidly connecting that associated gas generator to the gas conducting manifold, each sequence valve installed in a direction to permit gas flow from the associated gas generator into said manifold.
In combination with a solid-propellant-powered maneuvering system for spacecraft having (1) a first gas generator set for providing a hot gas output said first set consisting of two gas generators each generator containing solid propellant and having an ignition means responsive to an ignition command, the burn rate of said propellant being directly related to the pressure of said gas output so that the rate of said gas output is directly related to the pressure of said gas output, (2) four nozzle valve clusters disposed to be mounted on the spacecraft and radiosymmetrically arranged about the spacecraft roll axis, each nozzle valve cluster having a first and a second high thrust nozzle valve having a corresponding first and second high thrust nozzle attached and fluidly connected thereto the first high thrust nozzle oriented to produce thrust in a direction along and defining a high-thrust-line axis and the second high thrust nozzle oriented to produce thrust in a direction directly opposite to that of the first high thrust nozzle and along said high-thrust-line axis which is spaced from and is parallel to said roll axis, and each nozzle valve cluster also having a first and a second low thrust nozzle valve having a corresponding first and second low thrust nozzle attached and fluidly connected thereto the first low thrust nozzle oriented to produce thrust in a direction along and defining a low-thrust-line axis and the second low thrust nozzle oriented to produce thrust in a direction directly opposite to that of the first low thrust nozzle and along said low-thrust-line axis which intersects said high-thrust-line axis and is perpendicular to a plane containing both said high-thrust-line axis and said roll axis, each nozzle valve having means for individually operating in response to valve commands, (3) a gas conducting manifold fluidly connecting each gas generator of said first gas generator set to each nozzle valve cluster inlet port, (4) a gas pressure transducer fluidly connected to said manifold, and (5) command generating means responsive to guidance command inputs and responsive to pressure feedback from said gas pressure transducer for generating valve commands to individual nozzle valves and for generating ignition commands to individual gas generator ignitors, the improvement which comprises:
- a second gas generator set for providing a hot gas output said second set consisting of two gas generators each generator containing solid propellant and having an ignition means responsive to an ignition command, the burn rate of said propellant being directly related to the pressure of said gas output so that the rate of said gas output is directly related to the pressure of said gas output;
- and
- a set of two sequence valves, each sequence valve uniquely associated with a particular gas generator of said second set and fluidly connecting that associated gas generator to the gas conducting manifold, each sequence valve installed in a direction to permit gas flow from the associated gas generator into said manifold.
Dependencies are inferred from the claim text.