General Dynamics Corp., Pomona Division

Thomas W Bastian

Charles W Schertz

John M Speicher

Ronald T Inglis

Garry T Lacy

John J Vink

J Sydney Roberts

A rocket propelled missile assembly comprises an outer casing defining an internal solid rocket propellant chamber, the casing having an opening at its forward end aligned with an internal tube submerged in the rocket propellant chamber, and at least one exhaust nozzle at its rear end for venting exhaust gases from the propellant chamber. Solid propellant is contained within the propellant chamber surrounding the internal tube, and a separate terminal stage missile is partially or fully submerged in the tube with the capacity to separate from the tube forwardly through the front end of the casing. The missile separates from the remainder of the system on booster burn out.

Multiple stage rocket propelled missile system

An in-flight jettisonable protective cover device for protecting fragile, accurate, radomes or signal-responsive components for the major portion of a flight which is capable of being jettisoned in one piece at supersonic speeds from a guided missile, other air vehicles, or space vehicles. The cover device is for use, for example, in combination with a guided missile having a shell structure, a nose portion, and a radome in the missile nose. The cover device is attached to the missile nose for covering the radome such that an inner space is defined. A plurality of shear pins or other quick-release mechanisms attach and retain the cover device to the missile shell. A source of low pressure gas pressurizes the inner space to approximately 50 psi. A rapid-discharging, high pressure gas cartridge produces a high pressure gas for exerting a pressure force on the aft face of the cover device. The pressure forces are sufficient to shear the retaining pins and accelerate the cover device sufficiently forward to clear the missile body at supersonic speeds. The missile angle of attack creates lateral aerodynamic forces on the cover deivce to clear it from the missile. The sensitive radome can then be used for high precision detection and tracking as required at intercept.

Jettisonable protective cover device

A missile launching system adapted for installation in a standard commercial aircraft without modification of the aircraft structure. The system comprises a plurality of frame members, linear tracks which are movable longitudinally relative to the frame members, a plurality of launch tubes for storing the missiles, an exit port for installation in an pre-established aircraft fuselage opening, and associated equipment for selectively launching the missiles from the launch tubes through the exit port. The entire system is assembled from individual components, all of which are sized to be placed on board the aircraft through a standard passenger door opening. In preparation for installing the system in a commercial aircraft, the passenger seats and related equipment conventionally installed in the interior of such an aircraft are removed. The frame members of the system are then mounted to the standard seat tracks in the floor of the aircraft. The remaining portions of the system are thereafter assembled and installed on the frame. The frame is inclined to support the launch tubes at an angle extending upward and forward so that when a missile is ejected from the launch tube, it is given a trajectory which carries it clear of the aircraft wing and empennage.

Quick conversion missile system for widebody aircraft

A gimbal assembly includes an outer arcuate yoke gimbal member mounted on rollers to rotate about its axis and an inner gimbal member includes a platform pivotally mounted in the yoke to rotate about a second axis. Two drive motors are separately and independently connected through independent cable drive assemblies to separate ones of the inner and outer gimbal members and functions either individually or together to rotate the gimbal members selectively or both together in a combination of motion. In one form, the two drive motors are co-axially mounted in the base of the gimbal assembly. In another form the gimbal drive motors are co-axially mounted with the outer housing of one motor forming the drive pulley for the other drive assembly. In another arrangement the motors are disposed on adjacent parallel axes with one drive motor for the inner gimbal having co-axially disposed drive pulleys for the drive cable.

Dual cable drive rolling arc gimbal

A multi-burn restartable solid rocket fuel having plural layers, each independently ignitable, including a central core, and at least one outer cylindrical layer separated from the central core by a non-ignitable layer, and the method of utilization therefor including first igniting the central core in an end burned configuration, and subsequently or concurrently igniting the next adjacent layer or layers in an end burned configuration, as desired.

Multi-burn solid fuel restartable rocket and method of use

A missile jet tab actuator system for a thrust vector control coupled to aerodynamic controlled surfaces is disclosed. The device removes roll information present in commands to the aerodynamic surfaces. Only pitch and yaw information is thus supplied to the thrust vector control jet tabs. In this disclosure, the roll information is removed by a gear and slotted sleeve system. The resulting pitch and yaw output is used to drive the thrust vector control jet tabs. No separate set of independently powered actuators for such tabs is required.

Jet tab control mechanism for thrust vector control

A rocket thrust vector control system including jet tabs and aerodynamic control surfaces is disclosed. The control system removes roll information present in commands to the aerodynamic surfaces and provides only pitch and yaw information to the jet tabs for the thrust vector control. The roll information is removed by a geared summing mechanism. The resulting pitch and yaw output is used to drive the thrust vector control jet tabs. The same powered actuators are used for both the aerodynamic control surfaces and the jet tabs.

Growing community of inventors

Fullerton, CA, United States of America

Thomas W Bastian