# US 8,788,122 B1 · Wing load alleviation methods and apparatus > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 8,788,122 B1 - Document ID: US8788122B1 - Status: Granted - Kind: B1 - Application number: 13/594,446 - Filed: 2012-08-24 - Granted: 2014-07-22 - Earliest claimed: 2012-08-24 - Assignees: The Boeing Company - Applicants: Mithra M. K. V. Sankrithi; Joshua Frommer - Inventors: Mithra M. K. V. Sankrithi; Joshua Frommer - Web page: https://patentgrep.com/patent/US8788122B1 ## CPC - B64C 23/076: {the wing tip airfoil devices comprising one or more separate moveable members thereon affecting the vortices, e.g. flaps} - B64C 13/16: actuated automatically, e.g. responsive to gust detectors - G05D 1/0066: {for limitation of acceleration or stress} - G05D 1/0808: {specially adapted for aircraft} - Y02T 50/10: Drag reduction - B64C: AEROPLANES; HELICOPTERS - G05D: SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract Wing load alleviation methods and apparatus are disclosed. An example method includes collecting data related to a condition of an aircraft; and when a condition identifier implemented via a logic circuit indicates that the condition comprises a high load condition, automatically generating a plurality of control signals to coordinate a first deflection of a first control surface of a configurable winglet and a second deflection of a second control surface of a wing adjacent to the winglet. ## Claims ### Claim 1 A method, comprising: collecting first data related to a condition of an aircraft; when a condition identifier implemented via a logic circuit indicates that the condition exists, automatically generating a plurality of control signals to coordinate a first deflection of a first control surface and a second deflection of a second control surface; and collecting second data related to a mode of the aircraft and, when the mode is a non-cruise mode, coordinating a third deflection of the first control surface and a fourth deflection of the second control surface. ### Claim 2 (depends on 1) The method as defined in claim 1, wherein coordinating the first and second deflections comprises deflecting the first and second control surfaces simultaneously. ### Claim 3 (depends on 1) The method as defined in claim 1, further comprising coordinating the first and second deflections to generate a modified pressure field at a juncture of a winglet and a wing. ### Claim 4 (depends on 1) The method as defined in claim 1, wherein the non-cruise mode comprises a climbing mode. ### Claim 5 (depends on 1) The method as defined in claim 1, wherein the first deflection is different from the third deflection. ### Claim 6 (depends on 1) The method as defined in claim 1, wherein the second deflection is different from the fourth deflection. ### Claim 7 An apparatus, comprising: a condition identifier to, via a logic circuit, determine a mode of an aircraft; and a signal generator to respond to the determined mode of the aircraft by conveying signals to actuators of the aircraft, wherein the signal generator is to respond to the mode being a flight condition mode comprising a non-cruise mode by: conveying a first signal to a first actuator associated with a first control surface of a wing to cause the first control surface to deflect; and conveying a second signal to a second actuator associated with a winglet to cause a second control surface of the winglet to deflect. ### Claim 8 (depends on 7) The apparatus as defined in claim 7, further comprising at least one of: a response calculator to generate responses to different conditions or modes of the aircraft; and a response database to store a plurality of responses corresponding to different conditions or modes of the aircraft. ### Claim 9 (depends on 8) The apparatus as defined in claim 8, wherein at least one of the responses includes coordination information indicative of a relationship between the deflection of the first control surface and the deflection of the second control surface. ### Claim 10 (depends on 7) The apparatus as defined in claim 7, wherein the condition identifier is to factor an expected condition into a determination of a condition of the aircraft. ### Claim 11 (depends on 7) The apparatus as defined in claim 7, wherein the first signal is to cause the first control surface to deflect upwards and the second signal is to cause the second control surface to deflect inwards. ### Claim 12 (depends on 7) The apparatus as defined in claim 7, wherein the first and second deflections are to cause a modified pressure field at a juncture of the winglet and the wing. ### Claim 13 An aircraft, comprising: a winglet having a first control surface, the winglet being mounted to a wing; a second control surface; a sensor to collect data related to a condition of the aircraft; and a signal generator to coordinate a deflection of the first control surface of the winglet and a deflection of the second control surface in response to a detection of the condition. ### Claim 14 (depends on 13) The aircraft as defined in claim 13, wherein the second control surface comprises an outboard spoiler. ### Claim 15 (depends on 13) The aircraft as defined in claim 13, wherein the second control surface comprises an aileron at a trailing edge of the wing. ### Claim 16 (depends on 13) The aircraft as defined in claim 13, wherein the first control surface is to be deflected inward and the second control surface is to be deflected upward in response to a high load condition. ### Claim 17 (depends on 13) The aircraft as defined in claim 13, wherein deflecting the first and second control surfaces in the coordinated manner includes deflecting the first and second control surfaces simultaneously. ### Claim 18 (depends on 13) The aircraft as defined in claim 13, wherein the first and second control surfaces are to be deflected in response to the aircraft being in a non-cruise mode. ### Claim 19 (depends on 13) The aircraft as defined in claim 13, wherein the condition includes at least one of a high load factor maneuver or a high gust.