An aerial vehicle comprising an airframe, an aircraft flight controller to provide an output control signal, and a planar printed circuit board positioned on the airframe. The printed circuit board may include coupled thereto a processor, a rate gyroscope, and at least three accelerometers. The processor is configured to generate an actuation signal based at least in part on a feedback signal received from at least one of said rate gyroscope and the at least three accelerometers. The processor communicates the actuation signal to said aircraft flight controller, which is configured to adjust the output control signal based on said actuation signal.
Distributed acceleration sensing for robust disturbance rejection
2021-02-16
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge / G01B MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS , Messen der Länge, der Dicke oder ähnlicher linearer Abmessungen / G01C Messen von Entfernungen, Höhen, Neigungen oder Richtungen , MEASURING DISTANCES, LEVELS OR BEARINGS / G01P MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION OR SHOCK , Messen der Linear- oder Winkelgeschwindigkeit, der Beschleunigung, der Verzögerung oder des Stoßes / G05D SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES , Systeme zum Steuern oder Regeln nichtelektrischer veränderlicher Größen |
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