EXTENSION OF THREE LOOP CONTROL LAWS FOR SYSTEM UNCERTAINTIES, CALCULATION TIME DELAY AND COMMAND QUICKNESS
First Claim
1. A vehicle, comprising:
- a plurality of actuators; and
a control system operably associated with at least one actuator of the plurality of actuators, the control system having a control logic architecture having;
a dynamic command input shaping model associated with an input command;
a robust inner loop associated with the dynamic command input shaping model; and
a time delay cancellation model;
wherein the input command is received by the control system, analyzed with the control logic architecture, and thereafter commands the at least one actuator of the plurality of actuators.
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Accused Products
Abstract
A system includes a plurality of actuators and a control system operably associated with the plurality of actuators. The control system having a control logic architecture having a dynamic command input shaping model associated with an input command, a robust inner loop associated with the dynamic command input shaping model, and a time delay cancellation model. The method includes selecting a control law based upon a flight performance of an aircraft, decoupling the control law into a first individual component and a second individual component of the aircraft flight motion, analyzing each individual component separately, regrouping the component of flight motion, analyzing the control law with a time delay cancellation model and providing the necessary dynamic flight quickness with a different command input condition.
19 Citations
20 Claims
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1. A vehicle, comprising:
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a plurality of actuators; and a control system operably associated with at least one actuator of the plurality of actuators, the control system having a control logic architecture having; a dynamic command input shaping model associated with an input command; a robust inner loop associated with the dynamic command input shaping model; and a time delay cancellation model; wherein the input command is received by the control system, analyzed with the control logic architecture, and thereafter commands the at least one actuator of the plurality of actuators. - View Dependent Claims (3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13)
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14. An aircraft, comprising:
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an interface; a plurality of actuators; and a flight control computer operably associated with the interface and at least one of the plurality of the actuators, the flight control computer having a control logic architecture having; a dynamic command input shaping model associated with an input command; a robust inner loop associated with the dynamic command input shaping model; and a time delay cancellation model; wherein the input command is received by the control system, analyzed with the control logic architecture, and thereafter commands the at least one actuator of the plurality of actuators. - View Dependent Claims (15, 16, 19, 20)
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17. A method, comprising:
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selecting a control law based upon a flight performance of an aircraft; decoupling the control law into a first individual component and a second individual component of the aircraft flight motion; analyzing each individual component separately; regrouping the component of flight motion; and analyzing the control law with a time delay cancellation model. - View Dependent Claims (18)
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Specification