Ralph H Klestadt

6614012, Sep 2, 2003

Feb 28, 2001

09/795577

Arthur J. Schneider - Tucson AZ
Ralph H. Klestadt - Tucson AZ
David A. Faulkner - Tucson AZ

Raytheon Company - El Segundo CA

F42B 1522

244 31

A precision-guided hypersonic projectile weapon system. The inventive system includes a first subsystem for determining a target location and providing data with respect thereto. A second subsystem calculates trajectory to the target based on the data. The projectile is then launched and guided in flight along the trajectory to the target. In the illustrative application, the projectile is a tungsten rod and the first subsystem includes a forward-looking infrared imaging system and a laser range finder. The second subsystem includes a fire control system. The fire control system includes an optional inertial measurement unit and predicts target location. The projectile is mounted in a missile launched from a platform such as a vehicle. After an initial burn, the missile launches the projectile while in flight to the target. The missile is implemented with a rocket with a guidance system and a propulsion system.

6848648, Feb 1, 2005

Feb 25, 2003

10/374845

Ralph H. Klestadt - Tucson AZ, US
Robert D. Stratton - Tucson AZ, US
Christopher P. Owan - Tucson AZ, US
Laurence F. Prudic - Sahuarita AZ, US

Raytheon Company - Waltham MA

F42B 1002
F42B 1000

244 323, 244 31, 102501

A system and method for controlling roll in a projectile. The novel system () includes first () and second () sections adapted to counter-rotate relative to each other and a mechanism () for inducing the counter-rotation to generate a roll torque on the projectile (). In the preferred embodiment, the mechanism () is a motor comprised of a rotor () affixed to the first section (), and the second section () which acts as a stator that rotates around the rotor () when a current is applied to the armature. In an alternative embodiment, the second section () is turned by a motor () attached to the first section () which drives a small gear engaging a full-diameter ring gear () on the second section (). In the illustrative examples, the first () and second () sections are a missile forebody and a tail section of the projectile.

8367993, Feb 5, 2013

Jul 16, 2010

12/837587

Javier Velez - Tucson AZ, US
Ralph H. Klestadt - Tucson AZ, US

Raytheon Company - Waltham MA

F42B 15/01

244 328, 244 329, 244 327

A missile has a flight termination system that includes deployable lift surfaces that deploy forward of a center of gravity of the missile. When deployed, the lift surfaces cause the missile to rotate about its longitudinal axis. This rotation eventually increases in rate until the missile nears a natural roll frequency of the missile. As the missile nears or reaches its natural roll frequency, the missile's nose pitches up, angle of attack diverges and the missile tumbles, resulting in rapid termination of flight by loss of aerodynamic lift, vertical plunging and crashing. The lift surfaces may be curved surfaces that conform to the shape of a fuselage of the missile, prior to the deployment of the lift surfaces. The lift surfaces may be canted slightly relative to a missile longitudinal axis when the lift surfaces are deployed, so as to provide a sufficient rolling moment to overcome aerodynamic damping or resistance (roll drag) of the missile.

50057812, Apr 9, 1991

Mar 27, 1989

7/328828

Scott D. Baysinger - Chatsworth CA
Ralph H. Klestadt - Encino CA

Hughes Aircraft Company - Los Angeles CA

F42B 1012

244 326

A staged missile which is reconfigured in-flight solely by changing vehicle dynamics enabling packaging of kinetric energy kill capability in severely constrained envelopes, thus retaining the use of existing tactical assets to counter advanced armored threats.

54173930, May 23, 1995

Apr 27, 1993

8/052985

Ralph H. Klestadt - Sherman Oaks CA

Hughes Aircraft Company - Los Angeles CA

F42B 1016

244 327

A vehicle such as a missile (20) includes an aerodynamically shaped missile body (22) having a longitudinal centerline, a set of control surfaces (26) joined to the missile body (22), and, preferably, a propulsion system (28) operable to drive the missile body (22) forwardly. A cylindrical rotational bearing (32) is mounted on the missile body (22) with its cylindrical axis parallel to the longitudinal centerline (24) of the missile body. A flexible band wing (38) is supported from the rotational bearing (32). The flexible band wing (38) may rotate about the centerline (24) of the missile body (22) responsive to aerodynamic forces exerted on the missile body (22) and the flexible band wing (38) to aid in making maneuvers without requiring the missile (20) to bank to align the flexible band wing (38) with the direction of the maneuver.

56428677, Jul 1, 1997

Jun 6, 1995

8/471469

Ralph H. Klestadt - Tucson AZ

Hughes Missile Systems Company - Los Angeles CA

B64C 338
B64C 356
F42B 1016

244 49

An aerodynamic lifting and control surface comprising an external box structure that encloses an internal grid whose members are parallel to the box structure. The external box structure comprises four panels connected at their comers by spring hinges. When the hinges are unconstrained, the external box structure is compressed into a flat, thin parallelogram shape. The internal grid comprises a plurality of plates connected to each other and to the external box structure by flexible hinges. Control apparatus for use with an aerodynamic vehicle is also disclosed. The control apparatus comprises at least one aerodynamic lifting and control surface that is coupled to an actuator disposed within the vehicle and connected to the aerodynamic lifting and control surface for rotating it.

53335287, Aug 2, 1994

Aug 28, 1992

7/937251

Ralph H. Klestadt - Sherman Oaks CA
Richard R. Finn - Palmdale CA

Hughes Aircraft Company - Los Angeles CA

F41F 3042

89 151

A multiple missile ejection system (10) by which first and second missiles (14) and (16) are stored in a single launch tube (12). Each missile is ejected by a gas bag. In a particular embodiment, two gas bags are used. The first gas bag (18) is mounted between the first and second missiles (14) and (16) respectively. The second gas bag (20) is mounted between the second missile (16) and an end of the launch tube. When deflated, the first gas bag (18) has a longitudinal aperture (28) through the center thereof which allows for the ejection of the second missile (16) by the second gas bag (20).