Patent US3904153A successfully refreshed from Google Patents.
US3904153A
Expired / Lapsed
US
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Steerable and retractable aircraft nose landing gear assembly
Assignee: Boeing Co
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Filing: 1974-02-25
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Granted: 1975-09-09
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Expires: 1994-02-25
Abstract
Abstract A steerable and retractable aircraft nose landing gear assembly including a cross link for rapidly connecting and disconnecting the nose wheels from the aircraft steering mechanism and a common locking arrangement for locking the wheels in retracted or extended positions is disclosed. The cross link arrangement connects a movable collar attached to the steering mechanism to a collar affixed to the wheels when the wheels are to be steered by the steering mechanism. Opening of the cross link separates the wheels from the steering mechanism and, thus, allows the aircraft to be freely moved by a towing vehicle without feedback to the steering mechanism occurring. The common locking mechanism comprises a bungee spring operated pair of off-center locking links running between the drag strut linkage and a flange affixed to the aircraft. The operation of an actuator rotates the links against the force created by the bungee spring to unlock the mechanism. When in either the extended or the retracted position, the off-center locking links prevent movement of the drag strut linkage in a manner such that the wheels are prevented from moving to the opposite position.
Inventors
- 👤 John Watts
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-08 23:05
CPC Classifications
B; B64; B64C; B64C25/00; B64C25/32; B64C25/50; B64C25/02; B64C25/08; B64C25/10; B64C25/18
Claims Analysis
Total Claims: 25
Claim 1
Independent Claim
225 words
An aircraft nose landing gear assembly comprising: shock absorbing means suitable for absorbing the shock applied to aircraft when its nose wheels come in contact with the ground upon landing; a cylindrical housing surrounding said shock absorbing means; a mounting mechanism for affixing said cylindrical housing to said aircraft; wheel support means for supporting aircraft nose wheels in a manner such that said nose wheels are free to move and control the direction of movement of said aircraft when said nose wheels are in contact with the ground, said wheel support means including a wheel collar mounted about one end of said cylindrical housing; aircraft steering means for controlling the movement of said wheel support means when attached thereto, said aircraft steering means including a steering collar mounted about said cylindrical housing adjacent to, but spaced from, said wheel collar; and manual attachment means for attaching said steering collar to, and detaching said steering collar from, said wheel collar, said manual attachement means comprising a link detachably connected between said steering collar and said wheel collar, said link being formed and connected in a manner such that when said steering collar is detached from said wheel collar, said wheel support means and the aircraft wheels it supports are free to rotate through any desired arc without causing any corresponding movement of said aircraft steering means.
Claim 2
Dependent Claim
225 words
An aircraft nose landing gear assembly comprising: shock absorbing means suitable for absorbing the shock applied to aircraft when its nose wheels come in contact with the ground upon landing; a cylindrical housing surrounding said shock absorbing means; a mounting mechanism for affixing said cylindrical housing to said aircraft; wheel support means for supporting aircraft nose wheels in a manner such that said nose wheels are free to move and control the direction of movement of said aircraft when said nose wheels are in contact with the ground, said wheel support means including a wheel collar mounted about one end of said cylindrical housing; aircraft steering means for controlling the movement of said wheel support means when attached thereto, said aircraft steering means including a steering collar mounted about said cylindrical housing adjacent to, but spaced from, said wheel collar; and manual attachment means for attaching said steering collar to, and detaching said steering collar from, said wheel collar, said manual attachement means comprising a link detachably connected between said steering collar and said wheel collar, said link being formed and connected in a manner such that when said steering collar is detached from said wheel collar, said wheel support means and the aircraft wheels it supports are free to rotate through any desired arc without causing any corresponding movement of said aircraft steering means.
Claim 3
Dependent Claim
47 words
An aircraft nose landing gear assembly as claimed in claim 1, wherein said cylindrical housing is rotatably attached to said aircraft; and, including a lockable retraction mechanism suitable for moving said cylindrical housing, said shock absorbing means and said wheel support means between extended and retracted positions.
Claim 4
Dependent Claim
166 words
an upper drag strut having one end rotatably attached to said aircraft and the other end rotatably attached to said lower drag strut, said upper drag strut including a transverse arm located in the region where said upper and lower drag struts are rotatably attached to one another, said upper and lower drag struts formed and attached in a manner such that: a. when said cylindrical housing, said shock absorber means and said wheel support means are in said extended position, said upper and lower drag struts are in an extended position whereat their longitudinal axes are essentially coaxial; and, b. when said cylindrical housing, said shock absorber means and said wheel support means are in said retracted position, said upper and lower drag struts are in a retracted position whereat their longitudinal axes define an acute angle; and, C. a drag strut locking mechanism suitable for locking said drag strut assembly in either of its extended or retracted positions, said drag strut locking mechanism comprising:
Claim 5
Dependent Claim
166 words
an upper drag strut having one end rotatably attached to said aircraft and the other end rotatably attached to said lower drag strut, said upper drag strut including a transverse arm located in the region where said upper and lower drag struts are rotatably attached to one another, said upper and lower drag struts formed and attached in a manner such that: a. when said cylindrical housing, said shock absorber means and said wheel support means are in said extended position, said upper and lower drag struts are in an extended position whereat their longitudinal axes are essentially coaxial; and, b. when said cylindrical housing, said shock absorber means and said wheel support means are in said retracted position, said upper and lower drag struts are in a retracted position whereat their longitudinal axes define an acute angle; and, C. a drag strut locking mechanism suitable for locking said drag strut assembly in either of its extended or retracted positions, said drag strut locking mechanism comprising:
Claim 6
Dependent Claim
111 words
a second lock link rotatably attached to said aircraft and having one end rotatably attached to the other end of said first lock link, said first and second lock links forming an offset locking mechanism having a single lock position whereat said lock links are substantially coaxial with, but slightly offset from, one another, said offset angle pointing toward said upper drag strut, said single lock position beiNg achieved when said first and second drag struts are in either their extended or their retracted positions, said first and second lock links including fingers formed so as to impinge on one another when said lock links are in their single lock position;
Claim 7
Dependent Claim
111 words
a second lock link rotatably attached to said aircraft and having one end rotatably attached to the other end of said first lock link, said first and second lock links forming an offset locking mechanism having a single lock position whereat said lock links are substantially coaxial with, but slightly offset from, one another, said offset angle pointing toward said upper drag strut, said single lock position beiNg achieved when said first and second drag struts are in either their extended or their retracted positions, said first and second lock links including fingers formed so as to impinge on one another when said lock links are in their single lock position;
Claim 8
Dependent Claim
111 words
a second lock link rotatably attached to said aircraft and having one end rotatably attached to the other end of said first lock link, said first and second lock links forming an offset locking mechanism having a single lock position whereat said lock links are substantially coaxial to, but slightly offset from, one another, said offset angle pointing toward said upper drag strut, said single lock position being achieved when said first and second drag struts are in either of their extended or retracted positions, said first and second lock links including fingers formed so as to impinge on one another when said lock links are in their single lock position;
Claim 9
Dependent Claim
111 words
a second lock link rotatably attached to said aircraft and having one end rotatably attached to the other end of said first lock link, said first and second lock links forming an offset locking mechanism having a single lock position whereat said lock links are substantially coaxial to, but slightly offset from, one another, said offset angle pointing toward said upper drag strut, said single lock position being achieved when said first and second drag struts are in either of their extended or retracted positions, said first and second lock links including fingers formed so as to impinge on one another when said lock links are in their single lock position;
Claim 10
Dependent Claim
155 words
an upper drag strut having one end rotatably attached to said aircraft and the other end rotatably attached to said lower drag strut, said upper drag strut including a transverse arm located in the region where said upper and lower drag struts are rotatably attached to one another, said upper and lower drag struts formed and attached in a manner such that: (a) when said wheel support means is in said extended position said upper and lower drag struts are in an extended position whereat their longitudinal axes are essentially coaxial; and, (b) when said wheel support means is in said retracted position, said upper and lower drag struts are in a retracted position whereat their longitudinal axes define an acute angle with respect to one another; and, D. a drag strut locking mechanism suitable for locking said drag strut assembly in either of its extended or retracted positions, said drag strut locking mechanism comprising:
Claim 11
Dependent Claim
155 words
an upper drag strut having one end rotatably attached to said aircraft and the other end rotatably attached to said lower drag strut, said upper drag strut including a transverse arm located in the region where said upper and lower drag struts are rotatably attached to one another, said upper and lower drag struts formed and attached in a manner such that: (a) when said wheel support means is in said extended position said upper and lower drag struts are in an extended position whereat their longitudinal axes are essentially coaxial; and, (b) when said wheel support means is in said retracted position, said upper and lower drag struts are in a retracted position whereat their longitudinal axes define an acute angle with respect to one another; and, D. a drag strut locking mechanism suitable for locking said drag strut assembly in either of its extended or retracted positions, said drag strut locking mechanism comprising:
Claim 12
Dependent Claim
35 words
a bungee spring extending between said upper drag strut and said first lock link so as to create a force tending to move said first and second lock links into their single lock position; and,
Claim 13
Dependent Claim
35 words
a bungee spring extending between said upper drag strut and said first lock link so as to create a force tending to move said first and second lock links into their single lock position; and,
Claim 14
Dependent Claim
35 words
a bungee spring extending between said upper drag strut and said first lock link so as to create a force tending to move said first and second lock links into their single lock position; and,
Claim 15
Dependent Claim
35 words
a bungee spring extending between said upper drag strut and said first lock link so as to create a force tending to move said first and second lock links into their single lock position; and,
Claim 16
Dependent Claim
68 words
An aircraft nose landing gear assembly as claimed in claim 2, wherein said lockable retraction mechanism comprises: A. a first actuator extending between said cylindrical housing and a fixed position in said aircraft in a manner such that actuation of said first actuator moves said cylindrical housing, said shock absorber means and said wheel support means between said extended and retracted positions; B. a drag strut assembly comprising:
Claim 17
Dependent Claim
33 words
a second actuator connected to said second lock link for creating a force counter to said bungee spring force to move said first and second lock links out of their single lock position.
Claim 18
Dependent Claim
33 words
a second actuator connected to said second lock link for creating a force counter to said bungee spring force to move said first and second lock links out of their single lock position.
Claim 19
Dependent Claim
35 words
a second actuator connected between said second lock link and said aircraft creating a force counter to said bungee spring force to move said first and second lock links out of their single lock position.
Claim 20
Dependent Claim
35 words
a second actuator connected between said second lock link and said aircraft creating a force counter to said bungee spring force to move said first and second lock links out of their single lock position.
Claim 21
Dependent Claim
23 words
An aircraft nose landing gear assembly as claimed in claim 3 including a universal joint connecting said upper and lower drag struts together.
Claim 22
Dependent Claim
73 words
An aircraft nose landing gear assembly comprising: A. wheel support means rotatably attached to an aircraft for supporting the nose wheels of said aircraft; B. a first actuator extending between said wheel support means and a fixed position in said aircraft in a manner such that actuation of said first actuator moves said wheel support means and the nose wheel supported thereby between extended and retracted positions; C. a drag strut assembly comprising:
Claim 23
Dependent Claim
73 words
An aircraft nose landing gear assembly comprising: A. wheel support means rotatably attached to an aircraft for supporting the nose wheels of said aircraft; B. a first actuator extending between said wheel support means and a fixed position in said aircraft in a manner such that actuation of said first actuator moves said wheel support means and the nose wheel supported thereby between extended and retracted positions; C. a drag strut assembly comprising:
Claim 24
Dependent Claim
23 words
An aircraft nose landing gear assembly as claimed in claim 5 including a universal joint connecting said upper and lower drag struts together.
Claim 25
Dependent Claim
33 words
An aircraft nose landing gear assembly as claimed in claim 6 wherein said second lock link includes an arm extending outwardly, said second actuator connected to said arm of said second lock link.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1978-09-08 | 1979-03-10 | 1979-09-09 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1982-09-08 | 1983-03-10 | 1983-09-09 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1986-09-08 | 1987-03-10 | 1987-09-09 | $7700.00 | Window Closed / Lapsed |