A rocket booster has an annular shape, with a casing defining an annular space therewithin, and a solid rocket fuel in the annular spacing. The rocket booster also includes one or more nozzle pieces, mechanically coupled to the casing, that define one or more nozzles at the aft side of the rocket booster. The rocket booster may be mechanically coupled to an object protruding from the back of a fuselage of a flight vehicle, such as a missile. For example, the rocket booster may be placed around an aft turbojet nozzle of the flight vehicle. This allows the rocket booster to be used in situations where primary propulsion must be running both before and after (and perhaps during) the firing of the rocket booster.

A rocket propulsion system comprising a first cryogenic tank and a second cryogenic tank, wherein the first cryogenic tank is filled with a first propellant, and the second cryogenic tank is filled with a second propellant, for purposes of feeding at least one repeatedly ignitable main propulsion unit in a propulsion phase of the rocket propulsion system. For purposes of tank pressurization via at least a low level of acceleration in a ballistic phase, a first auxiliary propulsion unit can be operated by means of a first gas pressure accumulator, and at least one further auxiliary propulsion unit can be operated by means of a further gas pressure accumulator, and the rocket propulsion system is assigned an energy conversion unit, which is designed at least to charge the first and the second gas pressure accumulator, preferably in the ballistic phase.

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.

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.

A small satellite propulsion system using a gaseous oxidizer and a gaseous fuel as primary propellants with a liquid as a film coolant for the inner surface of the rocket motor. The gaseous fuel is also used as a pressurant for the coolant and as a cold gas propellant for attitude control system (hereinafter ACS) thrusters. The oxidizer, fuel, and coolant tanks, as well as most valves and plumbing, are integrated into a single core unit along with the rocket motor, rocket motor plumbing, and safety valves. Attitude control thrusters may be remotely located with plumbing to the fuel tank. The core unit is four inches high and less than four inches deep and wide. The small satellite propulsion system uses no pyrotechnics and no hazardous toxic materials.

A small satellite propulsion system using a gaseous oxidizer and a gaseous fuel as primary propellants with a liquid as a film coolant for the inner surface of the rocket motor. The gaseous fuel is also used as a pressurant for the coolant and as a cold gas propellant for attitude control system (hereinafter ACS) thrusters. The oxidizer, fuel, and coolant tanks, as well as most valves and plumbing, are integrated into a single core unit along with the rocket motor, rocket motor plumbing, and safety valves. Attitude control thrusters may be remotely located with plumbing to the fuel tank. The core unit is four inches high and less than four inches deep and wide. The small satellite propulsion system uses no pyrotechnics and no hazardous toxic materials.

A system for positioning at least one satellite in working orbit, characterized in that the system for positioning satellites in working orbit comprises: a first attachment device configured to attach a first satellite to the system for positioning satellites in working orbit; a main propulsion device with solid propulsion comprising a plurality of parallel solid-propellant cartridges; a secondary propulsion device which is re-ignitable; at least one position sensor configured to measure the position of said system; a monitoring unit connected to said at least one position sensor and which is configured to control a firing of the cartridges of the main propulsion device to move said system from a transfer orbit to a working orbit of the first satellite, said monitoring unit being further configured to control an opening of the first attachment device to separate said system from the first satellite.

A rocket booster has an annular shape, with a casing defining an annular space therewithin, and a solid rocket fuel in the annular spacing. The casing may itself at least in part define an annular gap that functions as a nozzle for the rocket booster, with protruding tabs on the casing aiding in maintaining a uniform height of the annular gap. The rocket booster may be mechanically coupled to an object protruding from the back of a fuselage of a flight vehicle, such as a missile. For example, the rocket booster may be placed around an aft turbojet nozzle of the flight vehicle. This allows the rocket booster to be used in situations where primary propulsion must be running both before and after (and perhaps during) the firing of the rocket booster.

A rocket booster has an annular shape, with a casing defining an annular space therewithin, and a solid rocket fuel in the annular spacing. The casing may itself at least in part define an annular gap that functions as a nozzle for the rocket booster, with protruding tabs on the casing aiding in maintaining a uniform height of the annular gap. The rocket booster may be mechanically coupled to an object protruding from the back of a fuselage of a flight vehicle, such as a missile. For example, the rocket booster may be placed around an aft turbojet nozzle of the flight vehicle. This allows the rocket booster to be used in situations where primary propulsion must be running both before and after (and perhaps during) the firing of the rocket booster.

Systems, apparatuses, and methods for generating hot gases based on catalyzation involving flowing catalyst. Catalysis occurs in a flow-type mixing catalyzation channel in which a liquid catalyst mixes with a liquid reactant flowing in a desired flow regime, such as a striated (laminar) flow regime or a slug flow regime. Devices such as micro-thrusters for satellite and other applications and hot gas generators for powering another device, such as an electrical generator, can be made using one or more flow-type mixing catalyzation channels.