GB808438A - Mechanism for controlling the direction of rotation of a rotatable element - Google Patents
Mechanism for controlling the direction of rotation of a rotatable elementInfo
- Publication number
- GB808438A GB808438A GB1455956A GB1455956A GB808438A GB 808438 A GB808438 A GB 808438A GB 1455956 A GB1455956 A GB 1455956A GB 1455956 A GB1455956 A GB 1455956A GB 808438 A GB808438 A GB 808438A
- Authority
- GB
- United Kingdom
- Prior art keywords
- cylinder
- collar
- pivots
- pivot
- cylinders
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/50—Steerable undercarriages; Shimmy-damping
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Steering-Linkage Mechanisms And Four-Wheel Steering (AREA)
Abstract
808,438. Vehicle power steering. CLEVELAND PNEUMATIC TOOL CO. May 10, 1956, No. 14559/56. Class 79(5) [Also in Group XXXIII] Mechanism for controlling the direction of rotation of a rotatable element, e.g. a steerable aircraft undercarriage leg comprises a support element for the rotatable element, first and second cylinder members and associated fluid actuated piston members, a mounting portion on each member extending generally in the same direction, each cylinder mounting portion being connected to one of said elements and each piston mounting portion to the other element, at least one cylinder pivot and its associated piston pivot being equally spaced from the axis of rotation of the rotatable element, and stabilizing means between the cylinder members to prevent uncontrolled rotation thereof. In Figs. 2 and 3 twin-aircraft ground wheels are mounted at the foot of an inner cylinder 11 forming a shock absorber with an outer cylinder 10. A collar 14 is rotatably mounted on the cylinder 10, and is connected to the cylinder 11 by a scissors linkage 16, so that the wheel may be steered by rotating collar 14. Two mounting portions 19 on cylinders 17, 18 are pivoted at 22 to lugs 21 on cylinder 10, and two mounting portions on the piston rods 26 are pivoted at 31, 32 to lugs 29 on the collar 14. The cylinders have fluid pressure ports 33 and 34. The collar is rotated by admitting fluid under pressure to the port 33 of one cylinder and the port 34 of the other. At some point in the steering range, pivot 32 will be aligned with its associated piston rod pivot 22, whereupon the cylinder 18 will be free to swing about these pivots. To prevent this a bar 36 is pivoted to the cylinders at 37, 38. Similarly, when pivot 31 is aligned with its associated piston rod pivot 22, the cylinder 18 and bar 36 prevents cylinder 17 from swinging. The pivots 37, 38 are equidistant from the associated pivots 22. In Fig. 9, the arrangement is such that when the wheel is in the neutral position, the associated cylinder and piston rod pivots of cylinder 119 coincide at 136, and those of cylinder 121 at 138 and both cylinders are free to swing. To prevent this, a bar 143 is pivoted to the cylinders at 144, 146, and is formed with a tooth 147 engaging a notch 148 formed in the collar. Each cylinder rotates relatively to the fixed cylinder 10 with half the angular velocity of the collar, and the tooth 147 and notch 148 are located half way between the axis of bar 143 and the axis of the collar, whereby the tooth and notch have the same velocity when the wheel is turned from the neutral position, and their successive positions are shown in chain dot lines in Fig. 9. Fig. 10 (not shown) shows a modification in which the two pivots associated with cylinder 119 are further from the axis 137 than those of cylinder 121, though the pivots of each associated pair are equidistant from axis 137. Co-operating abutments on the collar and fixed cylinder limit the range of steering.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1455956A GB808438A (en) | 1956-05-10 | 1956-05-10 | Mechanism for controlling the direction of rotation of a rotatable element |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1455956A GB808438A (en) | 1956-05-10 | 1956-05-10 | Mechanism for controlling the direction of rotation of a rotatable element |
Publications (1)
Publication Number | Publication Date |
---|---|
GB808438A true GB808438A (en) | 1959-02-04 |
Family
ID=10043418
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB1455956A Expired GB808438A (en) | 1956-05-10 | 1956-05-10 | Mechanism for controlling the direction of rotation of a rotatable element |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB808438A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2536500A (en) * | 2015-03-20 | 2016-09-21 | Airbus Operations Ltd | Steering Device for an aircraft |
-
1956
- 1956-05-10 GB GB1455956A patent/GB808438A/en not_active Expired
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2536500A (en) * | 2015-03-20 | 2016-09-21 | Airbus Operations Ltd | Steering Device for an aircraft |
US9988144B2 (en) | 2015-03-20 | 2018-06-05 | Airbus Operations Limited | Steering device for an aircraft |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US2508057A (en) | Apparatus for translating, actuating, and restraining forces to vehicle wheels | |
US4109747A (en) | Steering mechanism | |
GB1114987A (en) | Camber adjustment of vehicle wheels | |
ES470610A1 (en) | Suspension for independent vehicle wheels | |
US3696881A (en) | Vehicle steering system of the fluid power type and spring centered, spring modulated control cylinder therefor | |
GB1211177A (en) | Improvements in or relating to steering linkages | |
US4948069A (en) | Device for steering the nose wheel train of an aircraft landing gear | |
GB1222610A (en) | Steering mechanism | |
GB808438A (en) | Mechanism for controlling the direction of rotation of a rotatable element | |
GB861368A (en) | Improvements in or relating to steering devices for motor vehicles | |
US3994362A (en) | Hydraulically operated steer axle linkage | |
GB820228A (en) | Improvements in or relating to stacking trucks | |
GB983732A (en) | An articulated vehicle having hydraulic steering mechanism | |
GB798866A (en) | Improvements in or relating to steering mechanism | |
US2916294A (en) | Wide angle steering mechanism for industrial trucks | |
US2336567A (en) | Shimmy dampening apparatus for aircraft tail wheels | |
US2926032A (en) | Method of and means for changing the relative angle of rotary members | |
US2613888A (en) | Aircraft castorable or steerable landing element mountings | |
GB824611A (en) | Power steering | |
US4324305A (en) | Steering mechanism for excavators and the like | |
GB970542A (en) | Improvements in or relating to the steering of wheeled vehicles | |
US2884258A (en) | Steering correction device for vehicles | |
GB871358A (en) | Improvements in or relating to steerable trucks | |
US2747818A (en) | Nose landing gear with internally castered and steered wheel | |
US3057429A (en) | Vehicle steering system |