# US 2014/0191078 A1 · Airplane Emergency Supplemental Braking System And Method > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2014/0191078 A1 - Document ID: US20140191078A1 - Status: Published application - Kind: A1 - Application number: 13/736,632 - Filed: 2013-01-08 - Published: 2014-07-10 - Earliest claimed: 2013-01-08 - Assignees: The Boeing Company - Inventors: Kelly L. Boren; Sergey D. Barmichev - Web page: https://patentgrep.com/patent/US20140191078A1 ## CPC - B64C 25/42: Arrangement or adaptation of brakes - B60T 1/14: directly on road (portable devices, e.g. chocks B60T3/00) - B64C 25/32: characterised by elements which contact the ground or similar surface (arrester hooks B64C25/68) - B64C 25/68: Arrester hooks - B64C: AEROPLANES; HELICOPTERS - B60T: VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL (electrodynamic brake systems for vehicle, in general B60L; brakes per se, i.e. devices where braking effect occurs, including ultimate brake actuators, F16D); ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES ## Abstract A system, an apparatus, and a method for an aerospace vehicle braking system for decelerating an aerospace vehicle on a landing surface. An arm is provided having a first portion connected to the aerospace vehicle and a second portion generally distal to the first portion. The second portion of the arm includes an engagement portion configured to engage the landing surface. The arm is movable between a first position, wherein the engagement portion is substantially disengaged from the landing surface, and a second position, wherein the engagement portion engages the landing surface with a force sufficient to significantly decelerate the aerospace vehicle. The engagement portion is configured to pivot with respect to the arm in response to the direction of travel of the aerospace vehicle upon the landing surface. An actuator is connected to the arm to selectively move the arm between the first position and the second position. ## Claims ### Claim 1 An aerospace vehicle braking system for decelerating an aerospace vehicle on a landing surface, the aerospace vehicle braking system comprising: an arm having a first portion connected to the aerospace vehicle and a second portion generally distal to said first portion; said second portion of said arm including an engagement portion configured to engage the landing surface; and said arm being movable between a first position wherein said engagement portion is substantially disengaged from the landing surface and a second position wherein said engagement portion engages the landing surface with a force sufficient to significantly decelerate the aerospace vehicle ### Claim 2 (depends on 1) The aerospace vehicle braking system of claim 1, further comprising: landing gear connected to said aerospace vehicle; and said arm being connected to said landing gear for movement with respect thereto between said first position and said second position. ### Claim 3 (depends on 1) The aerospace vehicle braking system of claim 1, wherein said arm is pivotally connected to aerospace vehicle for pivoting between said first position and said second position. ### Claim 4 (depends on 1) The aerospace vehicle braking system of claim 1, further comprising: landing gear connected to said aerospace vehicle; and said arm being pivotally connected to said landing gear for pivoting with respect thereto between said first position and said second position. ### Claim 5 (depends on 1) The aerospace vehicle braking system of claim 1, wherein said engagement portion is configured to physically damage the landing surface upon said arm being in said second position. ### Claim 6 (depends on 1) The aerospace vehicle braking system of claim 1, further comprising: a first component connected to said second portion of said arm and configured to pivot about a first axis with respect to said arm; a second component connected to said first component and configured to pivot with respect to said first component about a second axis generally perpendicular to said first axis in response to the direction of travel of the aerospace vehicle upon the landing surface; and at least one engagement member extending downwardly from said second component that engages the landing surface upon said arm being in said position. ### Claim 7 (depends on 1) The aerospace vehicle braking system of claim 1, further comprising: a braking device connected to said second portion of said arm and configured to pivot with respect to said arm in response to the direction of travel of the aerospace vehicle upon the landing surface; and at least one engagement member extending downwardly from said second component that engages the landing surface upon said arm being in said position. ### Claim 8 (depends on 1) The aerospace vehicle braking system of claim 1, further comprising: a braking device connected to said second portion of said arm and configured to pivot with respect to said arm in response to the direction of travel of the aerospace vehicle upon the landing surface. ### Claim 9 (depends on 1) The aerospace vehicle braking system of claim 1, further comprising: a braking device connected to said second portion of said arm and configured to pivot with respect to said arm in response to the direction of travel of the aerospace vehicle upon the landing surface; and said braking device having an upturned leading surface with respect to the direction of travel of the aerospace vehicle upon the landing surface. ### Claim 10 (depends on 1) The aerospace vehicle braking system of claim 1, further comprising: landing gear connected to said aerospace vehicle; and at least one debris deflector component connected to said arm that generally deflects away from said landing gear debris which may arise upon said engagement portion engaging the landing surface with a force sufficient to significantly decelerate the aerospace vehicle. ### Claim 12 (depends on 1) The aerospace vehicle braking system of claim 1, further comprising: landing gear connected to said aerospace vehicle; tires connected to said landing gear; and at least one debris deflector component connected to said arm that generally deflects away from said tires debris which may arise upon said engagement portion engaging the landing surface with a force sufficient to significantly decelerate the aerospace vehicle. ### Claim 12 (depends on 1) The aerospace vehicle braking system of claim 1, further comprising: said engagement portion of said arm including at least one downwardly extending claw-shaped portion that engages the landing surface upon said arm being in said position. ### Claim 13 (depends on 1) The aerospace vehicle braking system of claim 1, further comprising: said engagement portion of said arm including at least three spaced-apart downwardly extending claw-shaped portions that each engage the landing surface upon said arm being in said position. ### Claim 14 (depends on 1) The aerospace vehicle braking system of claim 1, further comprising: at least one sensor that monitors the force exerted by said engagement portion against the landing surface. ### Claim 15 (depends on 1) The aerospace vehicle braking system of claim 1, further comprising: an actuator connected to said arm to selectively move said arm between said first position and said second position. ### Claim 16 (depends on 1) The aerospace vehicle braking system of claim 1, further comprising: at least one sensor that monitors the force exerted by said engagement portion against the landing surface; an actuator connected to said arm to selectively move said arm between said first position and said second position; and at least one controller connected to said sensor and to said actuator that allows for the force exerted by said engagement portion against the landing surface to be selectively controlled. ### Claim 17 (depends on 1) The aerospace vehicle braking system of claim 1, further comprising: at least one sensor that monitors the force exerted by said engagement portion against the landing surface; an actuator connected to said arm to selectively move said arm between said first position and said second position; and at least one controller connected to said sensor and to said actuator that automatically applies in a predetermined manner the force to be exerted by said engagement portion against the landing surface. ### Claim 18 A landing gear system for an aerospace vehicle, the landing gear comprising: a force bearing portion connected to the aerospace vehicle that at least partially supports the aerospace vehicle; an arm having a first portion connected to said force bearing portion and a second portion generally distal to said first portion; said second portion of said arm including an engagement portion configured to forcefully engage the landing surface; said arm being movable between a first position wherein said engagement portion is substantially disengaged from the landing surface and a second position wherein said engagement portion engages the landing surface with a force sufficient to significantly decelerate the aerospace vehicle; and an actuator connected to said arm to selectively move said arm between said first position and said second position. ### Claim 19 (depends on 18) The landing gear system of claim 18, further comprising: a first component connected to said second portion of said arm and configured to pivot about a first axis with respect to said arm; a second component connected to said first component and configured to pivot with respect to said first component about a second axis generally perpendicular to said first axis in response to the direction of travel of the aerospace vehicle upon the landing surface; and at least one engagement member extending downwardly from said second component that engages the landing surface upon said arm being in said position. ### Claim 20 (depends on 18) The landing gear system of claim 18, further comprising: a braking device connected to said second portion of said arm and configured to pivot with respect to said arm in response to the direction of travel of the aerospace vehicle upon the landing surface; and at least one engagement member extending downwardly from said second component that engages the landing surface upon said arm being in said position. ### Claim 21 (depends on 18) The landing gear system of claim 18, further comprising: a braking device connected to said second portion of said arm and configured to pivot with respect to said arm in response to the direction of travel of the aerospace vehicle upon the landing surface. ### Claim 22 (depends on 18) The landing gear system of claim 18, further comprising: at least one debris deflector device that generally deflects away from said landing gear debris which may arise upon said engagement portion engaging the landing surface with a force sufficient to significantly decelerate the aerospace vehicle. ### Claim 23 An aerospace vehicle that lands on a landing surface, the aerospace vehicle comprising: a fuselage; an airfoil connected to said fuselage; at least one power source connected to at least one of said fuselage and said airfoil; a landing gear configuration connected to the fuselage that provides support of the aerospace vehicle on the landing surface; an arm having a first portion connected to the landing gear and a second portion generally distal to said first portion; said second portion of said arm including an engagement portion configured to forcefully engage the landing surface; said arm being movable between a first position wherein said engagement portion is substantially disengaged from the landing surface and a second position wherein said engagement portion engages the landing surface with a force sufficient to significantly decelerate the aerospace vehicle; and an actuator connected to said arm to selectively move said arm between said first position and said second position. ### Claim 24 A method of decelerating an aerospace vehicle on a landing surface, the method comprising: possessing an arm having a first portion connected to the aerospace vehicle and a second portion generally distal to said first portion, said second portion of said arm including an engagement portion configured to engage the landing surface; moving said arm being between a first position wherein said engagement portion is substantially disengaged from the landing surface to a second position wherein said engagement portion engages the landing surface; and applying a force against the landing surface with said engagement portion sufficient to significantly decelerate the aerospace vehicle. ### Claim 25 (depends on 24) The method of claim 24, wherein said applying of said force against the landing surface with said engagement portion sufficient to significantly decelerate the aerospace vehicle aerospace vehicle is accomplished using a powered actuator. ### Claim 26 (depends on 24) The method of claim 24, wherein said applying of said force against the landing surface with said engagement portion sufficient to significantly decelerate the aerospace vehicle aerospace vehicle further comprises monitoring the force exerted by said engagement portion against the landing surface using at least one monitor. ### Claim 27 (depends on 24) The method of claim 24, wherein said applying of said force against the landing surface with said engagement portion sufficient to significantly decelerate the aerospace vehicle aerospace vehicle further comprises: monitoring the force exerted by said engagement portion against the landing surface using at least one monitor; and using said monitor to selectively control the force exerted by said engagement portion against the landing surface. ### Claim 28 (depends on 24) The method of claim 24, wherein said applying of said force against the landing surface with said engagement portion sufficient to significantly decelerate the aerospace vehicle aerospace vehicle further comprises: monitoring the force exerted by said engagement portion against the landing surface using at least one monitor and at least one controller; and using said monitor and said controller to automatically apply in a predetermined manner the force exerted by said engagement portion against the landing surface.