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1. 发明专利

CA591988A AIRCRAFT LANDING GEAR LOCK MECHANISM 未知
公开(公告)号：CA591988A
公开(公告)日：1960-02-02
申请号：CA591988D
申请人： CLEVELAND PNEUMATIC TOOL CO
发明人： WESTCOTT WILLIAM B JR

2. 发明专利

DE1055374B 未知
公开(公告)号：DE1055374B
公开(公告)日：1959-04-16
申请号：DEC0013349
申请日：1956-07-12
申请人： CLEVELAND PNEUMATIC TOOL CO
发明人： HOGAN WALTER HENRY
IPC分类号： B64C25/50

3. 发明专利

DE1045811B 未知
公开(公告)号：DE1045811B
公开(公告)日：1958-12-04
申请号：DEC0013393
申请日：1956-07-20
申请人： CLEVELAND PNEUMATIC TOOL CO
发明人： WESTCOTT WILLIAM BOOTH
IPC分类号： B64C25/14

4. 发明专利

CA566710A STEERING MECHANISM PARTICULARLY FOR AIRCRAFT 未知
公开(公告)号：CA566710A
公开(公告)日：1958-11-25
申请号：CA566710D
申请人： CLEVELAND PNEUMATIC TOOL CO
发明人： HOGAN WALTER H

5. 发明专利

FR1159732A 未知
公开(公告)号：FR1159732A
公开(公告)日：1958-07-01
申请号：FR1159732D
申请日：1956-08-23
申请人： CLEVELAND PNEUMATIC TOOL CO
IPC分类号： B64C25/14

6. 发明专利

FR1154251A 未知
公开(公告)号：FR1154251A
公开(公告)日：1958-04-04
申请号：FR1154251D
申请日：1956-06-21
申请人： CLEVELAND PNEUMATIC TOOL CO
IPC分类号： C23C18/31 , C25D5/38

7. 发明专利

GB714709A Improvements in or relating to gear shift controlling apparatus 未知
公开(公告)号：GB714709A
公开(公告)日：1954-09-01
申请号：GB2537051
申请日：1951-10-30
申请人： CLEVELAND PNEUMATIC TOOL CO
IPC分类号： B63H21/22 , F16H61/32 , G05D3/12
摘要： 714,709. Reverse-gear control. CLEVELAND PNEUMATIC TOOL CO. Oct. 30, 1951 [Oct. 30, 1950], No. 25370/51. Class 80 (2) [Also in Groups XXXVII and XXXVIII] The gear changing mechanism of a boat engine is moved to "forward," " neutral or "reverse" under the control of a selector switch 34. Movement of the switch to any position F, N, R, energizes a motor brake release magnet 40 in series with either the " forward " or " reverse " windings of a motor 16 dependent on the direction of movement of the switch. The motor is thereby driven, in the appropriate sense, to rock the gear shift lever 14 to a corresponding position, through gearing 20 and a screw and nut 18, 22, e.g. as disclosed in Specification 569,245. The motor circuit is made through one of the brushes 66, 68, 70 on the arm 64 which reciprocates with the travelling nut 22 and the appropriate fixed contact plate 58 or 60. If the " forward " or " reverse " brush is operative the motor runs until the operative brush passes off the end of the associated contact plate. If the neutral" brush is operative the motor runs until the brush reaches the gap 72. In each case the motor circuit is broken and braked to a standstill by de-energization of the brake release magnet 40 when the gear shift lever 14 has reached the corresponding position. The motor 16, the brake mechanism 40, 48 and the switching means 66, 68, 70, 58, 60 are all mounted on the gear casing 20 which is pivoted at 30 to the framework.

8. 发明专利

CA405639A SHOCK ABSORBER 未知
公开(公告)号：CA405639A
公开(公告)日：1942-06-23
申请号：CA405639D
申请人： CLEVELAND PNEUMATIC TOOL CO
发明人： CLEVELAND EPHRAIM WATKINS

9. 发明专利

GB542593A Improvements in or relating to shock absorbing devices 未知
公开(公告)号：GB542593A
公开(公告)日：1942-01-19
申请号：GB688640
申请日：1940-04-16
申请人： CLEVELAND PNEUMATIC TOOL CO
IPC分类号： F16F9/48
摘要： 542,593. Shock absorbers. STEVENS, A. H. (Cleveland Pneumatic Tool Co.). April 16 1940, No. 6886. [Class 108 (iii)] A dash-pot employing both air pressure and fluid friction checking means comprises two telescoping cylinders 10, 13, the inner 13 of which is spaced from the wall of the outer 10 so as to form an annular space 17. The cylinder 13 passes through packings 21, 22 in a head 18 held in place by a screwed cap 20 and furnished with fluid tight ring 24. The bottom of the cylinder 13 carries a piston 30 having ports 34 closed by an upper and a lower ring valve 37, 43, springs 36, 42 in some of the ports 34 bearing against the rings 37, 43 and tending to keep them away from the piston 30. Small ports 45 in the ring 43, and smaller ports 39 in the ring 37 prevent complete closure to fluid passage, and these ports are further connected together when the rings are up against the piston by grooves 46, 40 running round the piston. A port 47, closable by the ring 37, and a smaller port 48 connect the interior 59 of the cylinder 13 to the space 17. The centre of the piston 30 is fitted with an annulus 50 furnished with ports 52 closable by a sliding ring 53. Through the opening 51 of the annulus 50 extends a metering pin 55 fixed on the bottom connecting butt 11. The pin 55 has a parallel top portion 56 which merges into a conical portion 57 and finally becomes a larger parallel bottom portion 58, of the same diameter as the opening 51. Oil &c. is introduced through a top orifice 28, and after actuation to fill all the lower chambers with the fluid an air valve 29 is screwed in place and air under pressure pumped into the upper part of the cylinder 13. Small forces applied between the butts 11 and 14 result in fairly free passage of the oil through the ports 34, 47, 48 and the opening 51. A severe compressive force, however, will result primarily in increased compression of the air and then in the ring 43 being brought up against the piston 30, and the ports 52 being closed by the ring 53, the opening 51 being subsequently gradually closed by the progressively larger diameter of the pin 55 as the piston descends, till finally it is closed altogether by the portion 58, leaving then only the ports 45 as open passages. A severe expansive force closes the ports 34 and 47 by bringing the ring 37 down on the piston, leaving only the ports 39 and 48 between the space 17 and the remaining spaces 59, 60.

10. 发明专利

GB527490A Improvements in or relating to landing wheel mountings for aircraft 未知
公开(公告)号：GB527490A
公开(公告)日：1940-10-10
申请号：GB398039
申请日：1939-02-07
申请人： CLEVELAND PNEUMATIC TOOL CO
IPC分类号： B64C25/50
摘要： 527,490. Aircraft landing gear. CLEVELAND PNEUMATIC TOOL CO. Feb. 7, 1939, No. 3980. Convention date, March 31, 1938. [Class 4] [Also in Group XXXII] In an aircraft landing-gear, a ground-engaging member, particularly a nose or tail wheel, is so mounted as to be capable of swivelling about a plurality of axes sloping upwardly in a fore to aft direction. In the form shown in Fig. 2, 10 and 13 represent the telescoping cylinders of a shock-absorbing strut, containing a metering pin housing 22 with a central orifice 24 co-operating with a metering pin 25. A bush 17 keyed to the cylinder 10 has a cam surface 45 adapted to co-operate with a similar cam surface 18 on a sleeve 14 secured to the inner cylinder 13 in order to limit the extension of the shock-absorber and prevent relative rotation of the cylinders in the extended condition. Oil and compressed air may be introduced through a filler tube 27. The lower end portion of the cylinder 13 is formed with an integral boss 29 on one side thereof, within which is rotatably mounted the spindle 31 of the wheel knuckle 32. A self-centring device comprises two cam-rings 35 and 36, the former secured to the boss and the latter slidably keyed to the spindle and pressed by the spring 39. In a modification, Fig. 3, the wheel knuckle 132 is rotatable within a housing 46 which is rotatable on a shaft 47 carried by one end 48 of a brace 49, which, together with the shock-absorber 51 is pivotally secured to the aircraft. In a further modification, a housing similar to the housing 46 of Fig. 3 is rotatably mounted on the end of the lower cylinder of a shock-absorber similar to that shown in Fig. 2. Specification 527,897, referred to, is concerned with the aligning cams.

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