The presently disclosed subject matter includes a method, apparatus and computer storage device for reducing dispersion of a rocket caused by jet-stream misalignment, the rocket comprising a rocket engine. Information indicative of a division of total operation time of the rocket engine into a first time period and a second time period is obtained; wherein an impulse which is generated during the first time period is at least approximately the same as an impulse generated during the second time period; a period of time which equals to the first time period starting from time of activation of the rocket engine is measured; upon termination of the period of time, the rocket is rotated around the rocket's longitudinal axis; and the angle of rotation measured; and the rotation is stopped once a 180? rotation is completed.

The presently disclosed subject matter includes a method, apparatus and computer storage device for reducing dispersion of a rocket caused by jet-stream misalignment, the rocket comprising a rocket engine. Information indicative of a division of total operation time of the rocket engine into a first time period and a second time period is obtained; wherein an impulse which is generated during the first time period is at least approximately the same as an impulse generated during the second time period; a period of time which equals to the first time period starting from time of activation of the rocket engine is measured; upon termination of the period of time, the rocket is rotated around the rocket's longitudinal axis; and the angle of rotation measured; and the rotation is stopped once a 180? rotation is completed.

Methods, systems, and devices solving Euler's rotational rigid body equation of motion, formed within two non-inertial frames of reference, that determine the vector inconstant variables of angular acceleration, velocity, and trajectory using a single piezoresistive accelerometer sensor, an ?C coupling algorithm and 1.sup.st and 2.sup.nd running integrals to in-flight acquire rotational inconstants in high-density Terramedia Terraflight and determine a Penetrator's loading profiles and method to parse vector Terraflight for rotational Pitch and Yaw enabling precision trajectory tracking utilizing three axial facing piezoresistive accelerometers, a differencing algorithm and 1.sup.st and 2.sup.nd running integrals enabling Penetrator flight control and precision guidance.

There is provided a projectile, a system and a related method of operation of a projectile comprising: a front ogive section; an aft section; and a control module; wherein the front ogive section is rotatably connected to the aft section by a coupling device, the front ogive section further comprising an asymmetric surface such that the asymmetric surface exerts an imbalance upon the projectile, where in use, the angular rotation of the front ogive section can be selectively adjusted relative to the aft section by commands from the control module to the coupling device influencing a helical trajectory of the projectile in flight thereby causing a change in direction thereby steering the projectile towards a target.

A guidance unit system is configured to be used for a ground-launched projectile. The system includes a housing configured to be attached to a ground-launched projectile. The housing is coupled to an attachment region that attaches to the projectile, wherein the housing is configure to rotate relative to the attachment region. A motor is contained within the housing and a bearing surrounding the motor. The bearing is rigidly attached to the housing such that the motor rotates with the housing and shields the motor from inertial loads experienced by the housing.

A method for steering a steerable interceptor missile driven by an engine for intercepting a moving target during a midcourse phase of an interception, includes steering the missile with real steering commands produced at respective steering times based on free control parameters formed as a current parameter vector. The free control parameters are constantly and repeatedly optimized during the midcourse phase by an optimization method for optimizing the control parameters. The optimization method is carried out in parallel with the actual steering. Newly detected information about the movement of the target and/or information about the flight of the missile is used in the optimization method as soon as the information is available. Optimized control parameters are accepted into the current parameter vector after being provided by the optimization method. An interceptor missile contains the current parameter vector and a control and evaluation unit for carrying out the method.

A method for steering a steerable interceptor missile driven by an engine for intercepting a moving target during a midcourse phase of an interception, includes steering the missile with real steering commands produced at respective steering times based on free control parameters formed as a current parameter vector. The free control parameters are constantly and repeatedly optimized during the midcourse phase by an optimization method for optimizing the control parameters. The optimization method is carried out in parallel with the actual steering. Newly detected information about the movement of the target and/or information about the flight of the missile is used in the optimization method as soon as the information is available. Optimized control parameters are accepted into the current parameter vector after being provided by the optimization method. An interceptor missile contains the current parameter vector and a control and evaluation unit for carrying out the method.

An afterbody flow control system is used for aircraft or missile flow control to provide enhanced maneuverability and stabilization. A method of operating the flow control system is also described. The missile or aircraft comprises an afterbody and a forebody; at least one activatable flow effector on the missile or aircraft afterbody; at least one sensor having a signal, the at least one sensor being positioned to detect forces or flow conditions on the missile or aircraft afterbody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one activatable flow effector based on at least in part the signal of the at least one sensor.

A method is presented by which a missile body roll angle relative to earth coordinates can be deciphered onboard the missile from ground-data relayed to the missile during flight The present method comprises of a horizontal pair and a vertical pair of antennas on the ground and an up-down pair and a right-left pair of antennas onboard the missile. The ground to pairs signals are sinusoidally amplitude modulated in 90 phase difference between the two pairs, causing the transmitted wave polarity to rotate in the modulation frequency. A reference pulse is transmitted from the ground whenever the wave polarity vector crosses a prescribed ground antenna direction, thereby enabling the missile to measure its body up, down, right and left directions relative to earth up, down, right and left directions and to further respectively align them together.

A method is presented by which a missile body roll angle relative to earth coordinates can be deciphered onboard the missile from ground-data relayed to the missile during flight The present method comprises of a horizontal pair and a vertical pair of antennas on the ground and an up-down pair and a right-left pair of antennas onboard the missile. The ground to pairs signals are sinusoidally amplitude modulated in 90 phase difference between the two pairs, causing the transmitted wave polarity to rotate in the modulation frequency. A reference pulse is transmitted from the ground whenever the wave polarity vector crosses a prescribed ground antenna direction, thereby enabling the missile to measure its body up, down, right and left directions relative to earth up, down, right and left directions and to further respectively align them together.