Sidney E Goldstein

US Patent:

45387796, Sep 3, 1985

Filed:

Sep 30, 1982

Appl. No.:

6/429259

Inventors:

Sidney E. Goldstein - Kirkland WA

Assignee:

The Boeing Company - Seattle WA

International Classification:

B64C 510

US Classification:

244 87

Abstract:

An empennage assembly for supersonic aircraft includes longitudinally and rearwardly extending booms (12) mounted upon the wings (16) or fuselage of the aircraft. The booms (12) include aft rotatable sections (22) upon which are mounted larger (18) and smaller (20) tail surfaces. The boom sections (22) are angularly rotated through angular displacements. theta. such that the dispositions of the tail surfaces (18, 20) are interchanged between their dispositions during low subsonic and high supersonic flight conditions. In this manner, the directional and longitudinal aerodynamic static stability components of the aircraft are rendered substantially constant at an optimum low or near-neutral level of stability in order to enhance the flight maneuverability capabilities of the aircraft throughout the subsonic, transonic, and high supersonic speed ranges. The empennage (10) is also advantageously employed for enhancing the directional stability characteristics of all aircraft under varied angle of attack conditions, and still further, can likewise enhance the lift characteristics of STOL aircraft employing vectored thrust. In connection with the use of the present invention empennage system upon supersonic aircraft, the rotational orientation of the empennage system (10) and its associated boom sections (22) is automatically programmed by suitable feed-back control means (23) in response to sensed changes in Mach number.

US Patent:

47212713, Jan 26, 1988

Filed:

Feb 14, 1985

Appl. No.:

6/701381

Inventors:

Sidney E. Goldstein - Kirkland WA
Ronald J. Pera - Seattle WA

Assignee:

The Boeing Company - Seattle WA

International Classification:

B64C 1512

US Classification:

244 75R

Abstract:

Rocket booster motor vectoring system and method for shortening take-off distance of aircraft, the aircraft being airborne before it is going fast enough for its conventional controls to provide adequate stability and control. A rocket booster motor (52) is coupled to aircraft (50) by means of thrust arm link (56) is pivotal engagement with the aircraft and fixed to the booster, and coupled by rearwardly positioned links (62, 64, 66) having ball and socket joints at both ends, one end being connected to the aircraft through aerodynamic surfaces (68, 70) or through actuators (124, 126), the aerodynamic surfaces being operable by conventional systems within the basic aircraft, and the actuators also being operated by motion sensing systems within the aircraft to vector the thrust of the booster to provide stability augmentation of the aircraft during the boosted launch phase to provide pitch, roll, and yaw control. The thrust vector is rotated or directed in response to signals generated in the basic aircraft control systems.