Device and system for controlling missiles and kill vehicles operated with gel-like fuels
AssigneeBayern-Chemie Gesellschaft fur Flugchemische Antriebe mbH
InventorsJürgen Ramsel, Pedro Caldas-Pinto, Karl Wieland Naumann, Helmut Niedermaier, Tobias Meyer, Albert Thumann, Susanne Risse
Life of this patent
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Abstract
Apparatus for trajectory control and/or position control of a missile (99), comprising a controllable gas generator (109, 200) with a fuel flow control valve (124, 213), an injector head (112, 202), a combustion chamber (111) and at least one outflow nozzle (103, 204) or at least one throttle.
Claims24
Apparatus for trajectory control and/or position control of a missile, comprising a controllable gas generator with a fuel flow control valve, an injector head with one or more injector elements, a combustion chamber generating combustion gases and at least one outflow nozzle, which has one of a variable nozzle throat cross-section, which is adjustable, and at least one throttle to vary discharge of said combustion gases from said outflow nozzle and vary nozzle thrust generated thereby.
System for trajectory control and/or position control of a missile, comprising an apparatus with a controllable gas generator and a fuel flow control valve with an injector head having one or more injector elements, and a combustion chamber generating combustion gases and at least one outflow nozzle, which has one of a variable nozzle throat cross-section, which is adjustable, and at least one throttle to vary discharge of said combustion gases from said outflow nozzle and vary nozzle thrust generated thereby, as well as a tank arrangement arranged separate from the combustion chamber and a gel fuel as propellant medium.
Apparatus for trajectory control and/or position control of a missile, comprising a controllable gas generator, which comprises:
- a fuel flow control valve controlling a fuel flow of gel fuel;
- an injector head with one or more injector elements which receive said fuel flow from said fuel flow control valve;
- a combustion chamber operatively connected to said injector head to combust said gel fuel in said combustion chamber wherein said one or more injector elements inject said fuel flow of said gel fuel into said combustion chamber with sufficient fuel flow to maintain combustion and form pressurized combustion gases;
- and
- at least one outflow nozzle, which receives said combustion gases from said combustion chamber and discharges said combustion gases from said outflow nozzle to an exterior of said missile to generate lateral thrust oriented laterally relative to a longitudinal axis of said missile, said outflow nozzle including one of a variable nozzle throat cross-section, which is adjustable to vary the variable nozzle throat cross-section, and at least one throttle to vary said discharge of said combustion gases and said lateral thrust generated therefrom.
Dependencies are inferred from the claim text.