Model based sensor system for loads aware control laws
First Claim
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1. A fly-by-wire flight control system comprising:
- a model-based sensor system which estimates an angular acceleration of an aircraft flight control with at least one model and data from at least one sensor in communication with said at least one model to obtain an angular acceleration estimate; and
a flight control law in communication with said model based sensor system to control a moment applied to the aircraft flight control using at least said angular acceleration estimate to reduce a load applied to an aircraft.
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Abstract
A flight control system includes a model-based sensor system which estimates angular accelerations to control rotor system moment such that loads on the aircraft structure are reduced to thereby allow an aircraft structural envelope to more closely follow an aircraft service flight envelope.
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Citations
21 Claims
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1. A fly-by-wire flight control system comprising:
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a model-based sensor system which estimates an angular acceleration of an aircraft flight control with at least one model and data from at least one sensor in communication with said at least one model to obtain an angular acceleration estimate; and a flight control law in communication with said model based sensor system to control a moment applied to the aircraft flight control using at least said angular acceleration estimate to reduce a load applied to an aircraft. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9)
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10. A method of flight control for, a rotary-wing aircraft comprising:
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estimating angular accelerations of an aircraft flight control using at least one model and data from at least one sensor to obtain an angular acceleration estimate; and using at least said angular acceleration estimate, controlling a moment applied to said aircraft flight control to reduce a load applied to said aircraft. - View Dependent Claims (11, 12, 13, 14)
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15. A method of estimating angular acceleration of a rotary-wing aircraft rotor system comprising the steps of:
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performing a first estimation of angular acceleration from a stick input; filtering the angular acceleration determined using the first estimation; filtering the angular acceleration determined using the second estimation; and combining filtered results from said filtering the angular acceleration determined using the first estimation and said filtering the angular acceleration using the second estimate to obtain an estimate of the angular acceleration of the rotary-wing aircraft rotor system. - View Dependent Claims (16, 17, 18, 19, 20, 21)
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Specification