A landing gear control lever system including a lever assembly, a locking assembly, and a switch assembly is disclosed herein. The locking assembly is connected to the lever assembly. The locking assembly has a rotary actuator and a Scotch yoke member operably connected to a portion of the rotary ac
A landing gear control lever system including a lever assembly, a locking assembly, and a switch assembly is disclosed herein. The locking assembly is connected to the lever assembly. The locking assembly has a rotary actuator and a Scotch yoke member operably connected to a portion of the rotary actuator such that rotation of the rotary actuator causes linear movement of the Scotch yoke member. The locking assembly can further include a locking arm operably coupled to the Scotch yoke member and moveable between locked and unlocked positions upon rotation of the rotary actuator.
대표청구항▼
1. A landing gear control system for use in an aircraft having landing gear, comprising: a lever assembly comprising— a control lever pivotable between a first position and a second position about a pivot point; anda locking element coupled to the control lever;a switch assembly operably connected t
1. A landing gear control system for use in an aircraft having landing gear, comprising: a lever assembly comprising— a control lever pivotable between a first position and a second position about a pivot point; anda locking element coupled to the control lever;a switch assembly operably connected to the lever assembly, wherein the switch assembly has at least one switch and is configured to control movement of the landing gear of the aircraft, wherein the switch is activated in response to movement of the control lever between the first and second positions;a locking assembly operably connected to the lever assembly, the locking assembly comprising— a rotary actuator;a Scotch yoke member with a shaft and a slot extending laterally from the shaft and operably connected to a portion of the rotary actuator such that rotation of the rotary actuator causes linear movement of the Scotch yoke member;a locking arm operably coupled to the Scotch yoke member and moveable between locked and unlocked positions upon rotation of the rotary actuator, wherein— the locking arm in the locked position engages the locking element of the lever assembly when the control lever is in the first position and prevents the control lever from moving to the second position, andthe locking arm in the unlocked position allows the control lever to move away from the first position. 2. The system of claim 1, further comprising a manual override member coupled to the locking arm and manually actuatable to move the locking arm from the locked position to the unlocked position independent of rotation of the rotary actuator to allow manual movement of the control lever between the first and second positions. 3. The system of claim 1 wherein the rotary actuator comprises a rotary solenoid. 4. The system of claim 1, further comprising a switch actuator pivotally connected to the control lever, wherein the switch actuator has an extendable portion that is configured to extend and retract upon rotation of the control lever. 5. The system of claim 4 wherein the switch actuator includes a hollow, tubular housing and the extendable portion is a spring-loaded plunger at least partially contained within the housing. 6. The system of claim 4, further comprising a cam plate mechanically coupled to the switch actuator, wherein the extendable portion of the switch actuator slides along a surface of the cam plate during movement of the control lever; between the first and second positions. 7. The system of claim 1 wherein: the locking assembly further includes a drive pin coupled to the rotary actuator;the Scotch yoke member further includes a shaft coupled to the locking arm and a slot portion extending laterally from the shaft; andwherein the slot portion of the Scotch yoke member slidably engages the drive pin. 8. The system of claim 1, further comprising a chassis, wherein the lever assembly, the switch assembly, and the locking assembly are mounted to the chassis. 9. The system of claim 1 wherein the locking assembly further includes a clevis operably coupled to the Scotch yoke member, and the locking arm. 10. The system of claim 1 wherein the locking arm includes a groove portion that contains the locking element of the lever assembly when the locking arm is in the locked position. 11. A landing gear control system coupleable to landing gear of a vehicle, comprising: a lever assembly having a landing gear control lever and a locking element connected to the landing gear control lever;a locking assembly coupled to the landing gear control lever, the locking assembly comprising: a rotary actuator with a drive member;a manual override button;a Scotch yoke member with a shaft and a slot extending laterally from the shaft and slideably connected to the drive member of the rotary actuator such that rotation of the rotary actuator causes linear movement of the Scotch yoke member;a locking arm operably coupled to the Scotch yoke member and moveable between locked and unlocked positions upon rotation of the rotary actuator; anda clevis operably coupled to the Scotch yoke member, the manual override button, and the locking arm; andwherein— the locking arm in the locked position engages the locking element of the lever assembly when the control lever is in the first position and prevents the control lever from moving to the second position, andthe locking arm in the unlocked position is disengaged from the locking element and allows the control lever to move away from the first position. 12. The locking assembly of claim 11, further comprising a manual override button coupled to the locking arm such that depression of the override button causes the locking arm to rotate and disengage the locking element of the lever assembly. 13. The locking assembly of claim 11 wherein the rotary actuator comprises a rotary solenoid. 14. The locking assembly of claim 11 wherein the locking arm includes a groove configured to engage the locking element of the lever assembly. 15. The locking assembly of claim 11 wherein the slot includes: a first portion that extends laterally to a first side of the shaft; anda second portion that extends laterally to a second side of the shaft that is opposite the first side. 16. A landing gear control system for use in an aircraft having a cockpit and landing gear, comprising: a chassis configured to be positioned within the cockpit of the aircraft, the chassis having an external portion and an internal portion;a lever assembly including— a control lever extending through a portion of the chassis and pivotable between a first control position and a second control position about a control lever pivot point attached to the internal portion of the chassis;a locking element coupled to the control lever and movable with the control lever between the first and second control positions;a switch assembly coupled to the chassis and operably connected to the lever assembly, the switch assembly having at least one switch and an electrical or optical connector coupled to the switch and extending through a portion of the chassis, wherein the switch controls movement of the landing gear of the aircraft, wherein the switch is activated in response to movement of the control lever between the first and second positions;a locking assembly operably coupled to the chassis and operably connected to the lever assembly, the locking assembly including— a rotary actuator;a Scotch yoke member operably connected to a portion of the rotary actuator such that rotation of the rotary actuator causes linear movement of the Scotch yoke member;a locking arm pivotable between a first locking position and a second locking position about a locking arm pivot point attached to the internal portion of the chassis, wherein the locking arm is operably coupled to the Scotch yoke member and moveable between locked and unlocked positions upon rotation of the rotary actuator, and wherein— the locking arm in the locked position engages the locking element of the lever assembly when the control lever is in the first position and prevents the control lever from moving to the second position, andthe locking arm in the unlocked position allows the control lever to move away from the first position. 17. A method of manufacturing a landing gear control system for use with landing gear of an aircraft, the method comprising: pivotally attaching a lever assembly to a chassis the lever assembly having a control lever pivotable between a first position and a second position about a pivot point, and a locking element coupled to the control lever and movable with the control lever between the first and second control positions;connecting the lever assembly to the chassis and coupling the lever assembly to a switch assembly, the switch assembly having at least one switch and being configured to control movement of the landing gear of an aircraft, wherein the switch is activated in response to movement of the control lever between the first and second positions; andconnecting a locking assembly to the chassis, the locking assembly including: a rotary actuator having a drive member;a Scotch yoke member with a shaft and a slot extending laterally from the shaft and slideably connected to the drive member of the rotary actuator such that rotation of the rotary actuator causes linear movement of the Scotch yoke member;a locking arm operably coupled to the Scotch yoke member and moveable between locked and unlocked positions upon rotation of the rotary actuator, wherein— the locking arm in the locked position engages the locking element of the lever assembly when the control lever is in the first position and prevents the control lever from moving to the second position, andthe locking arm in the unlocked position allows the control lever to move away from the first position.
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이 특허에 인용된 특허 (5)
Sparks Gary A., Bi-directional, dual acting, electric safety lock.
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