Unusual state alarm and recovery director
OwnerWilliam L. Hinksinventor
Life of this patent
Estimating the term…
Abstract
An inexpensive stall warning device for the instrument panel of an airplane or glider operates on the principle of balancing dynamic pressure against normal acceleration forces. It requires only static and pitot pressure inputs and electric power and employs a differential pressure transducer, MEMS rate gyros and accelerometers. These sensors will be monitored by a microprocessor to derive the aerodynamic states of the aircraft, thereupon issuing explicit display and vocal announcements to a pilot to prevent or guide recovery from a stall or spin state as well as overspeed or spiral dive.
Claims7
A dangerous aerodynamic state warning device for an airplane experiencing normal acceleration and accepting static and pitot pressure inputs, comprising:
- a differential pressure sensor that accepts said pressure inputs and outputs a signal representing dynamic pressure;
- at least one accelerometer, said accelerometer being aligned with the normal axis of said airplane, producing a signal representing acceleration along said normal axis, including a component of gravity;
- devices to produce warning alarms;
- and
- a computer system responsive to said dynamic pressure signals and said acceleration signals to calculate the coefficient of lift of said airplane, to compare said coefficient against warning levels of sad coefficient, and to issue signals evoking said alarms if said comparison meets a given criterion.
A dangerous aerodynamic state warning device for an airplane experiencing normal acceleration and accepting static and pitot pressure inputs, comprising
- a sensitive mass that is subjected to a force of acceleration in a direction substantially aligned with the lift vector applied to the wings of said airplanes;
- a device operatively connected to said mass and having an area upon which said static and pitot pressures act together to create a dynamic force applied upon said mass in opposition to said acceleration force;
- adjustable orifices between said pressure inputs that permit substantially proportional reductions of said dynamic force;
- a sensor to detect the consequence of said forces applied upon said mass;
- and
- a device to produce an alarm signal when said sensor indicates that said acceleration force is greater than said dynamic force.
Dependencies are inferred from the claim text.