Abstract: A control system for a guided missile or projectile in which signals to compensate the steering commands of the guided missile or projectile for the effects of gravity are dynamically produced and stored while the missile or projectile is in flight. The system includes a gyroscope mounted in the missile or projectile for establishing an attitude reference axis independent of the attitude of the missile or projectile. Gravity compensation signals are generated in response to sensed angular differences between the attitude at the missile or projectile and the reference axis, and the generated gravity compensation signals are stored. The missile or projectile steering commands are then compensated for gravity effects by use of the stored gravity compensation signals during the guidance mode of operation.

Abstract: A ballistic missile guidance apparatus for compensating the trajectory of a allistic missile just prior to thrust termination by comparing the nominal trajectory with the actual flight parameters encountered during the powered stage of the flight and introducing compensating corrections to provide for an accurate ballistic flight. The comparison is made by storing the nominal kinematic parameters and comparing thereto the actual flight parameters obtained from the inertial guidance system.

Abstract: Attitude of a pitch momentum biased satellite in a low inclination orbit is controlled by a closed loop magnetic torquing control system. A magnetic dipole oriented perpendicular to the satellite's pitch axis in the roll/yaw plane and at a predetermined azimuth angle relative to the roll axis minimizes roll and yaw errors by interaction with the earth's magnetic field. Signals from an on-board roll attitude sensor are used by satellite mounted detection and driver circuits to control the compensating torques. Magnetic torquing is initiated whenever the roll error as measured by the roll attitude sensor exceeds a predetermined threshold.

Abstract: A balloon has an airfoil-shaped member connected to its top surface. The airfoil-shaped member has a top curved skin with a plurality of parallelly-spaced partitions which form therebetween a plurality of air passageways for air. Upon the descent or lateral movement of the balloon, the airfoil-shaped member is expanded to provide a vertical stabilization of the balloon and to afford better control of the balloon during the lateral travel thereof.

Abstract: A lifting body missile is controlled by pitch and roll commands wherein the aw autopilot is caused to change in accordance with the roll and estimated angle of attack input information. A command logic is provided to determine the polarity of the command signals to the autopilot.

Abstract: A self-contained, strapped down guidance system combining all axes, all attitude navigation having two wide angle, two-degree-of-freedom gyros which provide attitude angle and angular rate signals along three axes. Accelerometer means provide signals representative of the acceleration along three orthogonally displaced independent axes. A first transformation matrix connected to the attitude angle output of the gyros and to the accelerometers transforms the gyro and accelerometer signals from body coordinates to gyro coordinates. A second transformation matrix connected to the output of the gyros, transforms the gyro coordinates into navigation coordinates. In order to perform navigational computations, computing means compute a transformation from gyro momentum vector (referenced to coordinate frame) to a navigational coordinate frame such as a locally vertical frame wherein the Z axis is always along the local vertical direction.

Abstract: The invention provides an angular position reference device for measuring changes in the attitude of a moving body and comprising a closed chamber filled with a liquid and rotatable about an axis by drive means, and position sensing means such as a vane assembly mounted within the chamber for rotation with the liquid independently of the chamber about an axis co-axial with the chamber axis and which, with the liquid, defines a reference position fixed in space in a plane normal to said axis, and which co-operate with the chamber to define a datum position of the chamber relatively to the reference position, in use, rotation of the chamber about said axis tending to cause relative rotation between the chamber and the liquid from said datum position which is sensed by the position sensing means which produces an output proportional to said rotation, said output so controlling the drive means to rotate the chamber to return the chamber to the datum position and, in use, providing a measure of a change in the pos

Abstract: A low cost shipboard reference system for carrying out the rapid alignment of aircraft inertial platforms in which an aircraft quality inertial reference is installed on shipboard and is operated in conjunction with a shipboard Kalman filter providing updating information thereto with the update connection from the Kalman to the shipboard inertial system normally kept opened and always kept opened during aircraft platform alignment to result in reference outputs for use in the aircraft system which are free of correlated noise but of sufficient accuracy for rapid alignment with a small azimuth error.

Abstract: A sensor system that measures flight motions with respect to a classical Euler angle system of coordinates by aligning itself with the plane of total angle of attack via a pendulum mass. The system permits a simple determination of lift and drag for a spinning vehicle at angle of attack whereby the measurements are used as inputs to a flight control system to control the motions of the spinning vehicle.

Abstract: A pair of conductive spherical shells are carried by a balloon or other means into an electrical field which induces equal and opposite charges on the shells. Rotation of the shells causes the charges to alternate. The alternating sinusoidal charge is applied to an amplifier and the amplified output modulated and applied to a transmitter. The spherical shells become a telemetry antenna for transmitting the sensed electrical field information to a remote receiver.

Abstract: A transportation machine such as a ballistic missile disposed for operation n a linear path is provided with a chassis including an aerate atmosphere and a gyroscopic rotor for development therearound of a pressurized aerate ring and for axial orientation in the linear path. A stabilizer develops signals responsive to differences in pressures between the aerate atmosphere and the pressurized ring for rotation of the chassis to axial coincidence with the rotor responsive to the signals.