Lockheed Martin Corporation

Joseph R Chovan

Daniel Walter Steele

A small, reusable interceptor unmanned air vehicle (UAV), an avionics control system for the UAV, a design method for the UAV and a method for controlling the UAV, for interdiction of small scale air, water and ground threats. The UAV includes a high performance airframe with integrated weapon and avionics platforms. Design of the UAV first involves the selection of a suitable weapon, then the design of the interceptor airframe to achieve weapon aiming via airframe maneuvering. The UAV utilizes an avionics control system that is vehicle-centric and, as such, provides for a high degree of autonomous control of the UAV. A situational awareness processor has access to a suite of disparate sensors that provide data for intelligently (autonomously) carrying out various mission scenarios. A flight control processor operationally integrated with the situational awareness processor includes a pilot controller and an autopilot controller for flying and maneuvering the UAV.

Unmanned air vehicle, integrated weapon platform, avionics system and control method

Micro electromechanical, MEM, components are created which include at least one integrated circuit die ( ). A cavity in the MEM component modules ( ) further allows for the flush mounted attachment of component modules when the component modules are stacked to create MEM system structures. Commonly positioned via holes within the component modules provide for communication among the dies ( ) on the stacked modules. In one embodiment of the invention, module layers are stacked in an alternating manner that further creates, within in the structure horizontal interlocking slots and vertical chambers. The interlocking slots can be used to join a plurality of structures together and the vertical chambers can be used to draw heat from the structure ( ).

Micro eletro-mechanical component and system architecture

A method and system for determining atmospheric disturbances or turbulence is disclosed. The system includes a plurality of sensor arrays, including at least one sensor element, distributed in a predetermined manner. Each of the sensor elements is in communication with a corresponding receiving system that is operable to receive and process energy received from the aircraft. A determination is then made regarding air turbulence by determining a rate of change of signal phase among selected sets of signals received at the receiving systems. A turbulence map is then determined from the determined rate of change of the phase and the angle of the received signal. When the rate of phase change exceeds known levels an indication of turbulence is made.

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North Syracuse, NY, United States of America

Joseph R Chovan