Messerschmitt-bolkow-blohm Gmbh

Messerschmitt-boelkow-blohm Gesellschaft MIT Beschraenkter Haftung

Messerschmitt-bolkow-blohm Gesellschaft MIT Beschrankter Haftung

Walter Kranz

Heinz Tillmann

Werner Schnabele

Lynn Hohnecker

A device for controlling aerodynamic bodies with at least one setting member for generating a transversal force on the aerodynamic body. To achieve a simple compact design, setting members are arranged on a rotor where the rotor extends forward from the tip of the aerodynamic body. The setting members are arranged here so that they set the rotor in rotation by the oncoming flow; they are designed, for instance, as a crossed pair of rudders. In addition, the setting members are located asymmetrically to the longitudinal axis of the aerodynamic body, so that they exert at least in some positions of the rotor a transversal force on the aerodynamic body. The position of the rotor can be influenced by means of a braking system.

Device for controlling aerodynamic bodies

A device for controlling an aerodynamic body having a searching head, a sensor and setting members for exerting a transversal force on the aerodynamic body into a target due to the sensor signals. In order to make possible a simple design of this device which can also be used for small aerodynamic bodies, the sensor and the setting members are arranged at a common rotor which rotates, driven about the longitudinal axis of the aerodynamic body, and can be influenced by means of a braking system as to its angular position relative to the aerodynamic body, generating a transversal force on the aerodynamic body.

The invention relates to a stepping mechanism for rotary motions with a driven switching wheel (9) which comprises at least one wheel-side stop (10), with an escapement mechanism having at least one pawl (12) which cooperates with said wheel-side stop, and with an actuating device (3, 17) for the pawl. Pursuant to the invention, a miniaturizable stepping mechanism is provided which is of a simple design and which permits reliable positioning of the switching wheel into preselected individual rotational positions. According to the invention, this is achieved in that the escapement mechanism of the stepping mechanism comprises a brake (20) displaceable under the action of force, with a run-up edge (21) lying in the region of each pawl (12) on to which the wheel-side stop (10) runs up before striking the pawl (12) to thereby displace the brake. Preferably, the brake and the pawls are arranged on a rocker (20, 13) for each, these being pivotable about a common rotary shaft (14) not lying in the axis of rotation (A) of the stepping mechanism. The stepping mechanism can be used for the control (i.e. steering) of missiles. To this end the switching wheel is preferably connected with a rotary nozzle body (1) which, via a thrust nozzle (8), delivers a propellant jet approximately in a radial direction.

Stepping mechanism for rotary motions

A guided missile with a hot-gas generator, whose gas penetrates a plurality of blow-out nozzles, which are arranged at regular intervals along the circumference and extend essentially perpendicularly to the longitudinal missile axis, whereby the flow rate of the gas through the individual blow-out nozzles can be regulated by a control device. The control device has a star coupling, which contains a number of arms corresponding to the number of blow-out nozzles, whereby each arm has a positioning element assigned to it, the corresponding blow-out nozzle can close completely or partially, and each arm has a control element assigned to it.

Guided missile

A control propulsion unit with a solid propellant (4) and a discharge nozzle, through which the propellant gases emerge into the open air, especially to exert transverse forces on a missile. To be able to precisely, quantitatively regulate the transverse forces, in accordance with the invention, it is proposed to extinguish the propellant in a controlled operation by reducing the clamping of the control propulsion unit, for example, by enlarging the discharge port for the propellant gases.

Control propulsion unit, especially for exerting transverse forces on a

A fluid distributor with a body of revolution, which is arranged around an axis of rotation and has a fluid passage communicating with a fluid source, as well as an exhaust passage, which is connected to this fluid passage and emerges from the side wall of the body of revolution, and fluid flows out of this exhaust passage as a fluid jet, in a direction which does not intersect the axis of rotation of the body of revolution, such that the body of revolution is set into rotation. To enable a back and forth motion of the body of revolution, with such an arrangement, between two stops, a jet baffle is provided, which is not connected to the body of revolution and which, when the body of revolution contacts the second stop, diverts the major portion of the fluid jet emerging from the exhaust passage in the direction of rotation, so that the fluid jet then acts on a supporting surface provided on the body of revolution to reverse the direction of rotation. A releasable brake is provided to retain the body of revolution in both positions. The fluid distributor can be used to guide missiles, for example in connection with quick-motion hot-gas valves.

Fluid distributor

A missile having a rotor ring, which has at least one adjustable fin actuated by the relative rotation between the rotor ring and the missile. At least one motor is arranged between the rotor ring and the missile, and a control device is provided which allows the motor to work as a generator and performs the fin adjustment.

Missile having rotor ring

A rotor setting system in conjunction with an aerodynamic-body control. The setting system is characterized by a rotor which comprises a console, a rotary drive for the rotor, setting members for the control of the aerodynamic body, especially rudders or spoilers, as well as a control unit for the rotor, and further including a control unit on the sides of the aerodynamic body, wherein the two control units cooperate with each other for adjusting the setting members.

Rotor setting system in conjunction with aerodynamic body controls

An apparatus for changing the flight path of a missile is disclosed. The apparatus comprises the tip of the missile which is installed so as to be pivotable in the nose of the missile and at least one actuator to tilt the pivotable nose cone. One end of the actuator is coupled to the internal outer edge of the nose cone and the other end of the actuator is coupled internally within the main missile body. The outer wall of the forward part of the missile additionally contains at least one annular flexible element extending perpendicularly to the axis of the missile body which facilitates the tilting of the nose cone.

Flight path control apparatus for missiles

A missile with adjustable flight controls capable of altering the missile's flight path is disclosed. The missile comprises an electric generator and control electronics. The electric generator is used in this invention both to provide electrical power to the control electronics and to regulate the flight controls. A mechanical connection is created between the generators rotor and the flight controls. The generator is electrically coupled to the control electronics through an electrically variable load. The control electronics alters the load which varies the rotational speed of the generator. This in turn affects the flight controls and the flight path is altered accordingly. The invention is small and compact, allowing its use in small missiles such as mortar or artillery shells.

Missile with adjustable flying controls

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. In addition, guiding means (4, 11, 12, 13, 14) are provided for the gas jet which steer the latter, depending on the angular position of the rotary nozzle body (3), substantially crosswise to the longitudinal axis (A) of the projectile for steering said projectile or into a direction substantially parallel to the longitudinal axis (A) of the projectile to provide an additional propulsion to the projectile. Preferably, the rotary nozzle body (3) comprises an offset thrust nozzle (4) and is incident with its axis of rotation (a) to the longitudinal axis (A) of the projectile in an acute angle (beta).

Apparatus for controlling a projectile

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.

Missile with aerodynamic control

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.

High velocity aerodynamic body having telescopic pivotal tip

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.

Brake and release apparatus for a rotary nozzle body

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.

Growing community of inventors

Taufkirchen, Germany

Walter Kranz