Takeoff/landing touchdown protection management system
First Claim
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1. An air/ground contact 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 located on the first landing gear, the first sensor configured to provide an output signal of a condition of the first landing gear;
a logic management system in communication with the first sensor, the logic management system comprises;
a sensor logic configured to receive and process the output signal from the first sensor of the first landing gear and use a mathematical process to assign an integer value to the output signal; and
a score management logic in communication with the sensor logic to receive and process the integer value, the score management logic being configured to classify the mode of the aircraft, the logic management system being configured to receive and process the output signal 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.
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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.
25 Citations
15 Claims
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1. An air/ground contact 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 located on the first landing gear, the first sensor configured to provide an output signal of a condition of the first landing gear; a logic management system in communication with the first sensor, the logic management system comprises; a sensor logic configured to receive and process the output signal from the first sensor of the first landing gear and use a mathematical process to assign an integer value to the output signal; and a score management logic in communication with the sensor logic to receive and process the integer value, the score management logic being configured to classify the mode of the aircraft, the logic management system being configured to receive and process the output signal 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)
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7. 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 located on the landing gear, the first sensor configured to transmit an output signal pertaining to a discrete landing gear state condition; a second sensor configured to transmit a second 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 second 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 a level of control authority provided to a pilot based upon the mode of the aircraft in a transition region. - View Dependent Claims (8, 9, 10)
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11. An air/ground contact 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; a second landing gear; and a third landing gear; at least a first sensor located on the first landing gear, the first sensor configured to provide an output signal of a condition of the first landing gear; a logic management system in communication with the first sensor, the logic management system comprises; a sensor logic configured to receive and process the output signal from the first sensor of the first landing gear and use a mathematical process to assign an integer value to the output signal; and a score management logic in communication with the sensor logic to receive and process the integer value, the score management logic being configured to classify the mode of the aircraft, the logic management system being configured to receive and process the output signal 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 (12, 13, 14, 15)
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Specification
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Current AssigneeTextron Innovations Incorporated (Textron Inc)
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Original AssigneeTextron Innovations Incorporated (Textron Inc)
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InventorsShue, Shyhpyng Jack
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Primary Examiner(s)Hilgendorf, Dale W
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Application NumberUS15/438,412Publication NumberTime in Patent Office791 DaysField of SearchUS Class CurrentCPC Class CodesB64C 13/04 actuated personallyB64C 13/16 actuated automatically, e.g...B64C 2025/325 specially adapted for helic...B64C 25/001 Devices not provided for in...B64C 25/34 wheeled type, e.g. multi-wh...B64C 27/57 automatic or condition resp...B64D 45/00 Aircraft indicators or prot...G05D 1/0669 specially adapted for verti...G05D 1/0676 specially adapted for landingG05D 1/0858 specially adapted for verti...
