Takeoff/landing touchdown protection management system
First Claim
1. A logic management system for determination of air/ground status of an aircraft, comprising:
- a landing gear system, having;
a first landing gear, having at least a first sensor configured to provide an output signal of a condition of the first landing gear;
a second landing gear, having at least a first sensor configured to provide an output signal of a condition of the second landing gear; and
a third landing gear, having at least a first sensor configured to provide an output signal of a condition of the third landing gear;
a logic management system in communication with all of the first sensors, the logic management system being configured to receive and process the output signals and automatically classify a mode of the aircraft as being within a transition region wherein a portion of the aircraft contacts the ground; and
a controller in communication with the logic management system to receive signal data from the logic management system, the controller being in communication with a control axis actuator to regulate a level of control authority provided to a pilot based upon the mode of the aircraft in the transition region.
2 Assignments
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Accused Products
Abstract
An air/ground contact logic management system for use with fly-by-wire control systems in an aircraft. The system includes a first sensor configured to provide an output signal to determine when the aircraft is in a transition region. A logic management system is in communication with the first sensor and is configured to receive and process the output signal and classify a mode of the aircraft. A controller receives signal data from the logic management system and communicates with a control axis actuator to regulate a level of control authority provided to a pilot. The control authority is individually regulated within each integrator as a result of the individual landing gear states.
4 Citations
20 Claims
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1. A logic management system for determination of air/ground status of an aircraft, comprising:
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a landing gear system, having; a first landing gear, having at least a first sensor configured to provide an output signal of a condition of the first landing gear; a second landing gear, having at least a first sensor configured to provide an output signal of a condition of the second landing gear; and a third landing gear, having at least a first sensor configured to provide an output signal of a condition of the third landing gear; a logic management system in communication with all of the first sensors, the logic management system being configured to receive and process the output signals and automatically classify a mode of the aircraft as being within a transition region wherein a portion of the aircraft contacts the ground; and a controller in communication with the logic management system to receive signal data from the logic management system, the controller being in communication with a control axis actuator to regulate a level of control authority provided to a pilot based upon the mode of the aircraft in the transition region. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13)
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14. An aircraft comprising:
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a landing gear coupled to the aircraft; a fly-by-wire control system used to control the aircraft; and an air/ground contact logic management system configured to communicate with the fly-by-wire control system to regulate control authority during selected maneuvers, the air/ground contact logic management system including; a first sensor coupled to the landing gear and configured to transmit an output signal pertaining to a discrete landing gear state condition; a second sensor configured to transmit an output signal pertaining to a landing gear engagement force condition; a logic management system in communication with the first sensor and with the second sensor, being configured to receive and process the output signal of the first sensor and the output signal of the second sensor, and automatically classify a mode of the aircraft based upon the discrete landing gear state condition and the landing gear engagement force condition; and a controller in communication with the logic management system to receive signal data from the logic management system, the controller being in communication with a control axis actuator to selectively regulate the level of control authority provided to a pilot based upon the mode of the aircraft in the transition region. - View Dependent Claims (15, 16)
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17. A computer-implemented method for regulating the control authority of an aircraft, the method being performed using one or more processing units, the method comprising:
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receiving an output signal from at least one sensor, the sensor configured to detect contact between the aircraft and ground; assigning an integer value to the output signal, the integer value being predetermined by a mathematical method programmed into a logic management system; compiling the integer values from the at least one sensor into a total score; transmitting the integer values and the total score to a score management logic; determining a mode of the aircraft through the score management logic, the mode of the aircraft being based upon the total score; classifying the mode of the aircraft automatically into at least one of an in flight mode, an air/ground transit mode, and an on ground mode; and regulating an axial control actuator to adjust the control authority of a pilot, the axial control actuator being controlled through a controller in communication with the score management logic and existing fly-by-wire control laws in the aircraft; wherein a range of the integer value is based upon the at least one sensor being in an in flight mode, an air/ground mode, or an on ground mode. - View Dependent Claims (18, 19, 20)
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Specification