Orbital Research Inc.

University of Notre Dame Du Lac

Other

Orbitel Research Inc.

Innovative Technology Applications

Alan B Cain

Mehul P Patel

T Terry Ng

Jack M DiCocco

Zak Sowle

Eric J Jumper

Thomas C Corke

David Anthony Cavalieri

Donald J Wittich, Iii

Stanislav Gordeyev

Edward J Kerschen

R Mark Rennie

Terry Ng

An 'air-data probe' system measures at least one component of freestream velocity by tracking the motion of a laser-induced breakdown ('LIB') spark created in a freestream flow. Neutral density filters are positioned or deployed so that the brightness of the initial LIB spark doesn't over saturate the LIB sensor system. This allows for more consistent tracking of the LIB spark throughout the duration of the LIB spark, including the later stages where the LIB spark is not nearly as bright as the initial LIB spark, thereby allowing all or substantially all of the light generated by the LIB spark to reach the sensors. This provides for enhanced visibility and more accurate detection of the LIB spark over time and as air density changes.

Apparatus and method for non-intrusive off-body measurements in hypersonic flight experiments

The present invention relates to an aircraft, missile, projectile, or underwater vehicle with an improved control system and a method for increasing the maneuverability or stability of an aircraft, missile, projectile, or underwater vehicle. More particularly, the present invention relates to a method for increasing the maneuverability or stability of an aircraft, missile, underwater vehicle or projectile through the use of removable control surfaces. The technical advantage of the removable control surface system (or 'removable control surface') over other systems is that the removable control surface system enables the aircraft, missile, underwater vehicle or projectile to have two or more design configurations, each configuration being tailored to the aircraft, missile, projectile, or underwater vehicle's specific stability or maneuverability requirements during a specific portion of the flight.

Aircraft, missile, projectile or underwater vehicle with reconfigurable control surfaces and method of reconfiguring

The present invention relates to a method of designing or optimizing a control surface for use with plasma actuators for controlling an aircraft, missile, munition or automobile, and more particularly to controlling fluid flow across their surfaces or other surfaces using plasma actuators, which would benefit from such a method. The various embodiments provide the steps to increase the efficiency of aircraft, missiles, munitions and automobiles. The method of flow control also provides a means for reducing aircraft, missile's, munition's and automobile's power requirements. These methods also provide alternate means for aerodynamic control using low-power hingeless plasma actuator devices.

Plasma optimized aerostructures for efficient flow control

Aircraft, missile, projectile, or underwater vehicle with reconfigurable control surfaces

An aircraft turret and fairing assembly for facilitating transmission of a directed energy beam from a directed energy device includes a turret section for directing an energy beam. The assembly also includes a fairing section aft of and adjacent to the turret section. Each of the turret section and the aft fairing section are coupled to an aircraft. The assembly also includes at least one sensor for detecting air speed of the aircraft and air pressure. The turret section and the aft fairing section are configured and positioned relative to one another to direct airflow for generating an aeroacoustic resonance within a desired frequency range in an area aft of the turret section.

Methods and apparatus for optical propagation improvement system

The present invention relates to an aircraft, missile, projectile, or underwater vehicle with an improved control system and an improved control system for maneuvering an aircraft, missile, projectile, or underwater vehicle. More particularly, the present invention relates to an aircraft, missile, underwater vehicle or projectile with removable control surfaces. The technical advantage of the removable control surface system (or 'removable control surface') over other systems is that the removable control surface system enables the aircraft, missile, underwater vehicle or projectile to have two or more design configurations, each configuration being tailored to the aircraft, missile, projectile, or underwater vehicle's specific stability or maneuverability requirements during a specific portion of the flight.

Aircraft, missile, projectile or underwater vehicle with reconfigurable control surfaces

Aircraft, missile, projectile or underwater vehicle with improved control system

Methods and systems are described for a system for measuring aberrations in a wave front. In the improved system multiple closely-spaced, small-aperture laser beams traverse an aberrating flow that introduces deflections of small-aperture laser beams from which aberrated wavefronts can be constructed. These beams may then be focused on position sensing devices using focusing lenses. The position sensing devices may then detect the positions of these beams and a difference between the detected position and the unaberrated position of the beams detected. This information may then be used to determine information regarding the optical aberrations introduced by the flow that may be used, for example, in improving communications systems and/or laser weapon systems.

Methods and systems for measuring an aberated wave front

Growing community of inventors

Chesterfield, MO, United States of America

Alan B Cain