General Dynamics Corp., Pomona Division

General Dynamics Corporation

Aerojet-general Corporation

Inge Maudal

Larry D Wedertz

Byron M Niemeier

Kenneth M Yost

John F Moss

A rate gyro instrument primarily for use in a gun fired spinning projectile eliminates all associated bearings by affixing the rotor to the spinning projectile body to obviate spin rotor bearings and by employing a flexible joint or constriction as a gimbal substitute to eliminate gimbal bearings.

Torque balanced rate gyro deriving its spin from a host projectile

An open-loop system for controlling a plant, including a sampling circuit for providing an actuating signal as a series of impulse signals, and a computer for providing a control signal to operate the plant in response to the actuating signal in accordance with a control function defined by a control algorithm based upon a calculated response of the plant in an equivalent closed-loop linear control system. The computer provides the control signal as a function of time following the application of each impulse signal. The control algorithm is a time-domain algorithm based upon an inverse LaPlace transform of the equivalent system. The interval between impulse signals, as defined by the sampling rate, is on the order of the time constant of the equivalent system; and the computation speed of the computer is sufficiently fast to provide a control signal that is effectively continuous relative to the operating dynamics of the plant.

Open-loop control system and method utilizing control function based on

A missile is disclosed which utilizes elastic deformation of structural members in order to control missile flight. The elastic deformation may be in the mounting of the rocket nozzle, the provision of deformable control surfaces, or provision of deformable sections of rocket body, all of which are controlled by independent actuating means.

Directional control of rockets using elastic deformation of structural

A projectile trajectory correction system, the projectile itself including a unique steering arrangement. The projectile, initially part of a shell cartridge, is fired, and its position is automatically sensed. A corrected trajectory necessary to hit a target is calculated and data commands are transmitted to the projectile. The data command signals are sensed by an antenna on the projectile. The antenna in turn generates a signal which is fed to the projectile steering mechanism which is deflected in response thereto to steer the projectile onto the correct trajectory. The steering mechanism includes an elongated rod extending from the rear of the projectile into the surrounding air stream. Deflection of the rod provides the actual steering.

Steering mechanism for an explosively fired projectile

A fragile, movable apparatus such as a rotatable infrared optical prism assembly is mounted in a projectile housing on a crushable support pad. When the projectile is launched, the fragile, movable apparatus crushes the pad and receives effective support from the pad. After launch, a resilient member positions the fragile, movable apparatus away from the crushed pad and provides the necessary freedom of movement for the fragile, movable apparatus.

High acceleration support and positioning device

A delivery system for multiple sub-missiles including in the sub-missiles a marking system, a detection system, a diverter for elimination of targets identified by the detector system, a scanner for initial determination of multiple targets, a logic circuit utilizing input from both the diverter and the scanner to eliminate targets and a sub-missile guidance system.

Sequential time discrimination system for sub-delivery systems

A retractable, self-erecting wing for a low speed missile, having a double walled fabric body held in extended position by spring loaded struts, the fabric enclosing an air pocket which acts as a damper to prevent the wing from fluttering under certain aerodynamic conditions. The wing is extended by a hinged strut structure and folds into a very small space adjacent the outer wall of the missile body. The structure enables a large area wing to be stowed in a minimum of space so that the maximum internal volume is available for payload. In stowed condition the wing is completely enclosed in the body for minimum drag during any high speed portion of the missile flight, multiple wings being released when required by a simple mechanism.

Double fabric, retractable, self-erecting wing for missle

In a closed loop servo system in which the input signal is inaccessible and not available for measurement, but the error signal and output signal are both accessible and measurable, a filter configuration is provided which can be inserted into the error signal path of the system to reduce the undesirable effects of noise or other unwanted signals without appreciably affecting the closed loop dynamics of the overall system. In the generalized system a filter having the characteristics g(s) in LaPlace notation is inserted into the error signal path of the system to filter selected components of the error signal. A second filter having the characteristics h(s) which satisfies the equation g(s)+h(s)=1, is coupled between the output signal and the output of the filter having the characteristics g(s). The signal passing through the filter having the characteristic h(s) is summed with the signal leaving the filter having the characteristics g(s) to cancel the filtering effect relative to the output signal and thus to decouple both filters from the control loop. Thus the filtering is accomplished without appreciably altering the characteristics of the control loop. In one application, the invention is utilized in connection with the proportional navigation guidance system for a homing missile. This permits extraneous signal components due to, for example, radome loop coupling and noise to be filtered from the error signal without affective the closed loop dynamics of the missile guidance.

Selective filter for closed loop servo system

An inertial guidance system including a true space stable platform is provided while retaining a simple two-degree-of-freedom gimbal system. An added third degree of freedom is provided by motions of the support itself which maintains desired platform orientation. The output of a third axis instrument is used to maneuver the frame itself about the axis of the frame which most nearly will null any rotation about the platform roll or longitudinal axis. A rotational rate gyroscope is positioned on the space stable platform, and actuates the movement of the frame about the longitudinal or roll axis directly from the reading of the rotational movement along the roll axis of the platform.

Quasi-inertial attitude reference platform

A missile is disclosed on which constant burning thrust reaction motors are provided integral with the tail panels of the missile to enhance the effect thereof, particularly during the boost phase of flight. The motors provide thrust along the chord of the tail panel and are moved about the axis of rotation of the tail panel by the servo motor associated therewith. The servo motors are activated by central missile control circuitry.

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Claremont, CA, United States of America

Inge Maudal