Abstract: The invention relates to an apparatus for controlling a projectile (1) having a nozzle arrangement (2) rotatably arranged in the projectile housing. The nozzle arrangement comprises a rotary nozzle body (3) with a thrust nozzle (4) which nozzle body can be brought into any desired angular position by means of a positioning drive. The rotary nozzle body (3) is coupled to a gas generator (7) for a propellant gas supply. For optimum utilization of the propellant gas of the gas generator, in all angular positions of the rotary nozzle body (3), the axis of rotation (a) of the rotary nozzle body (3) is arranged to be non-parallel to the longitudinal axis (A) of the projectile.

Abstract: A missile, and in particular a shell flying at supersonic velocity, having aerodynamic control. The missile comprises a missile housing and a missile tip which is tiltably connected to the missile housing. Between the missile housing and the shell tip, a positioning device consisting of at least one piezoelectric positioning member and a control circuit is arranged which comprises a voltage source. By applying a voltage to the piezoelectric positioning members, their lengths are changed, whereby the tilting motion of the shell tip is executed.

Abstract: A high velocity aerodynamic body, particularly a shell flying at supersonic velocity, having a device for stabilizing the aerodynamic body and for reducing its oscillation. The aerodynamic body has in the vicinity of its tip, a rotation symmetrical tip enclosure which is supported, with balanced mass, about a support point located on the longitudinal axis of the aerodynamic body, freely tiltably on all sides.

Abstract: A brake and release means for a rotary nozzle body. The rotating shaft of the nozzle body is mounted in a missile casing and delivers a gas thrust jet substantially perpendicularly to the direction of the longitudinal axis of the missile for guiding the missile. To be able to adjust the angular position between the rotary nozzle body and missile with high control frequency and exactly, a brake and release device is provided which comprise a friction coupling and an electromagnetic setting means. The frictional engagement and the release of the rotary nozzle body occur through a force control in that through the setting means, a control force axially directed counter to the tensioning force which assures the frictional engagement is exerted on the rotary nozzle body. To support the release of the rotary nozzle body, it may be provided further to build up a gas pressure between the friction faces of the friction coupling.

Abstract: An apparatus for correcting the flight path of a missile, such as a high speed shell or projectile, includes a missile body with a distributor for flow means rotatable in the missile body. An outlet opening for the flow means from the distributor is positionable relative to a blow-out opening on the outer circumference of the missile body for effecting a correcting thrust and for switching rapidly between different transverse forces, a missile tip provided with the blow-out openings is arranged to communicate with the outlet openings from the distributor. The extent to which the blow-out openings and the outlet openings align or overlap can be adjusted by a drive for the distributor acting in cooperation with the braking arrangement.

Abstract: The flight path of a flying body, such as an artillery shell, is stabilized gainst disturbing forces and against pendulum type motions by fluid steering jets ejected from said flying body for causing forces countering the disturbing forces. The steering jets pass through a fluid jet distributing member which has inlet openings communicating with fluid ducts leading to a fluid supply chamber. The distributing member is mounted in the flying body by a spring which permits a deflection or shifting of the distributing member in a direction across a central longitudinal axis of the body.

Abstract: A controllable flow deflection system for guiding the flow of a fluid medium in a desired discharge direction includes a steered deflection device mounted in a body or support member. The deflecting device includes a rotatable element containing at least one outlet opening for discharging the fluid medium which flows to the element from a reservoir. A driving and braking device is connected to the rotatable element. The one or more outlet openings are arranged so that the discharged fluid medium does not cause any torque on the rotatable element, or a torque is developed from a combination of two torque vectors symmetrical with respect to the axis of rotation of the element. Such a system may be used in a thrust system for steering a flying body member, in a secondary injection system, or in a hot gas motor, such as a vane motor.

Abstract: The invention relates to a thrust nozzle system, especially for steering a rojectile, having a nozzle arrangement (3) which is fed by a propellant source, for example a gas source. The nozzle system is arranged in a housing having at least one exhaust port (11) provided in the housing, and has a control (14) for steering a thrust jet (18) of the nozzle arrangement through the exhaust port. The invention provides a thrust nozzle system of simple construction which is especially suitable for a high miniaturization, and which permits a flexible thrust impulse forming. For this purpose the thrust nozzle system (2) has a rotating nozzle or a swinging nozzle body (3) which is rotatable relative to the housing about an axis, driven by the propellant, for example by the gas stream (P) from the gas source. The drive of the rotating nozzle body is preferably achieved by an acentric thrust nozzle (10) itself. Due to the low mass and hence low inertia of the nozzle body (3), it may be caused to rotate fast.

Abstract: A jet engine comprises a housing which defines a combustion chamber section, a narrowed diameter neck thrust nozzle section and an outwardly diverging portion which includes a part of the thrust nozzle section end in an extension outwardly from the thrust nozzle section. The outer end of the extension or the continuation of the thrust nozzle ends in a discharge opening for thrust gases and the vector of these thrust gases is controlled by control fluid which is selectively added into the divergent section at a location along its length such that it will be added in a selected narrow thrust jet zone in which the internal pressure on the nozzle edge of the thrust jet attains the ambient pressure or even drops below it.

Abstract: A shaft drive alternately for both directions of rotation, comprises, a shaft rotatably supported on bearings having first and second turbines connectable thereto, each including a respective first and second turbine wheel freely rotatable on the shaft in respective opposite first and second directions. The turbine wheels are driven by fluid which rotates the wheels in a selected direction and, in addition, displaces the turbine wheels so that a friction disc carried thereby is engaged with a respective first and second clutch to connect it to the shaft to impart the selected direction of rotation. When the turbine is stopped by not directing the fluid into the blades, in which case the clutch mechanism is moved out of engagement and the turbine wheel may run free of the shaft, the second turbine wheel may be connected in a similar manner by effecting engagement of the associated second clutch with the shaft when the fluid is directed to the second turbine for rotating the turbine wheel.

Abstract: A pressure gas reservoir for supplying pressure gas to control mechanisms of a projectile which is to be discharged from a gun tube by means of a propellant charge comprises a projectile body which has a reservoir therein with a wall portion which is adapted to be exposed to the pressure gases of the propellant charge and includes check valve means in the wall portion permitting the inflow of the pressure gases into the reservoir during firing for the storage therein, and for the subsequent use in operating the control mechanism.

Abstract: The converter comprises a plurality of series-connected bistable fluidic elements each having a supply input, two outputs separated by a jet splitter, and two conical inputs. The outputs of each bistable fluidic element are connected to respective control inputs of the next preceding bistable element. Feedback conduits are branched off the outputs of the last fluidic element and connected to the control inputs of the first fluidic element. The feedback conduits are closed or cleared by an electromagnetically operated valve which opens in the direction of fluid flow through the then blocked feedback conduit responsive to a signal from an electric control circuit.

Abstract: The converter includes a pressure fluid operated, bistable fluidic element, n the form of a fluid oscillator, having a pressure fluid supply inlet opening into an interaction chamber, two outlets extending downstream from the interaction chamber to the exterior and diverging in direction at an acute angle, two control inlets communicating with the interaction chamber, and a magnetic system actuated by electric input signals and influencing the control pressure in the control inlets to deviate the pressure fluid from one outlet to the other outlet. Respective feedback conduits are branched from the outlets to respective associated control inlets. Valve arrangements are selectively actuable by the magnetic system to close or open the feedback conduits. In one embodiment of the invention, a single valve is provided in the form of an armature of the magnetic system. In another embodiment of the invention, each control inlet has a respective valve therein in the form of an armature of the electromagnetic system.