Methods and systems for interacting with simulated phenomena are provided. Example embodiments provide a Simulated Phenomena Interaction System 'SPIS,' which enables a user to incorporate simulated phenomena into the user's real world environment by interacting with the simulated phenomena. In one embodiment, the SPIS comprises a mobile environment (e.g., a mobile device) and a simulation engine. The mobile environment may be configured as a thin client that remotely communicates with the simulation engine, or it may be configured as a fat client that incorporates one or more of the components of the simulation engine into the mobile device. These components cooperate to define the characteristics and behavior of the simulated phenomena and interact with users via mobile devices. The characteristics and behavior of the simulated phenomena are based in part upon values sensed from the real world, thus achieving a more integrated correspondence between the real world and the simulated world. Interactions, such as detection, measurement, communication, and manipulation, typically are initiated by the mobile device and responded to by the simulation engine based upon characteristics and behavior of the computer-generated and maintained simulated phenomena.

Method and system for interacting with simulated phenomena

The output of a transducer providing a signal in accordance with the instantaneous air speed of an aircraft is differentiated and fed to a summing device which subtracts therefrom a signal in accordance with the horizontal acceleration of the aircraft, this signal being derived from the output of an inertial instrument such as an accelerometer. The output of the summing device represents the magnitude of the wind shear condition (rate of change of wind velocity with changes in altitude). This signal is fed to appropriate indicator means which may comprise an appropriate display, a peak magnitude storage device, a warning device indicating a dangerous wind shear condition, or a telemetering device providing a wind shear reading to a ground station for use in advising other aircraft.

System for providing an indication of wind shear

A rugged microsensor assembly is disclosed that measures both the velocity and angular direction of an incoming air stream. The microsensor assembly includes at least two flow sensors, each orientated to measure a different velocity component of the incoming air stream. The velocity components are related by the geometry between the sensors, and the angular direction and velocity of the incoming air stream are determined by examining the measured velocity components. The preferred sensor is a fully passivated thermal differential microanemometer with back contacts, designed to operate in harsh environments.

Microsensor for measuring velocity and angular direction of an incoming air stream

An aircraft control system for computing a yaw compensated angle of attack is disclosed. The system includes an angle of attack sensor for generating a signal which represents an aircraft's angle of attack as determined by an angle of attack vane and a transverse accelerometer for generating a signal in response to the lateral acceleration of the aircraft. A summing device sums the two signals to thereby provide a yaw compensated angle of attack signal. The system may also include a rudder deflection sensor for generating a signal which represents the deflection of an aircraft's rudder. The rudder deflection signal is then subtracted from the yaw compensated angle of attack in the summing device. A stall warning system incorporating the yaw compensation system includes a stall warning computer for comparing the yaw compensated angle of attack signal to a predetermined value. The stall warning computer then triggers a stall warning device when the yaw compensated angle of attack signal exceeds the predetermined value.

Aircraft control system

A system for providing an optimum lift demand signal for aircraft maneuvers such as "go-around" includes a computer for generating a reference angle of attack signal which is functionally related to the aircraft's vertical velocity. The reference signal is compared with a signal corresponding to the aircraft's actual angle of attack, thereby producing an error signal. The error signal is utilized as a control to the aircraft's dynamics for optimizing the aircraft's climb-out performance.

Control system for aircraft vertical path guidance

This invention relates to a method and apparatus for obtaining the angle of attack of an aircraft developed as a result of an appropriate processing of the vertical speed, the airspeed, and the pitch attitude of the aircraft. The latter involves resolving the inverse sine of the vertical speed signal over the airspeed signal, and subsequently differentially combining the end product of the inverse sine computation and the chord line angle signal. The air speed signal is corrected by a corrective network which receives a feedback signal proportional to the angle of attack as well as a signal proportional to drift angle.

Jean-Guy Hache

Papers

Method and apparatus for obtaining accurately the angle of attack of an aircraft