GB612799A - Aircraft controlling system - Google Patents

Abstract

612,799. Controlling aircraft; retractable landing-gear. MORANE-SAULNIER SOC. ANON. June 4, 1946, No. 16979. Convention date, March 7. [Class 4] In a control system for aircraft a single casing 24 contains the parts controlling the landing flaps 5 of the wing 2, shown in plan, Fig. 2, and also the parts controlling the retractable three-wheel landing-gear (of which only the rear wheels 4 are shown), the above two controls being operated through a common single member such as the horizontal shaft 25 shown in Fig. 3. In the construction shown, the control of the flaps is free for operation only while the landing-gear is in its lowered condition. The shaft 25, which can be rotated by a crank turned by the pilot and acting through sprocketwheels and a chain 9, has freely mounted on it two worms 33 and 26, which can be alternatively coupled by lugs such as 27, 29 to a sliding sleeve 30 splined to shaft 25 so as to rotate therewith. In the position shown in Fig. 3, the worm 33 coupled to sleeve 30 can be driven from shaft 25 to turn worm-sheels 34, 40, to act one through arms 15 upon the two undercarriage wheels 4 to lower them and the other through an arm 17 to lower the third wheel; a pivoted lever 38 with an arm 39 locking sleeve 30 from sliding is turned down to withdraw arm 39 during the ending of the rotation of wheel 40, so that sleeve 30 can then be moved by means of a wire 7 connected to a pilot's control-lever, acting on lever 22 having an arm 32 to move sleeve 30 into connection with worm 26, which can then be rotated by further turning of shaft 25 to drive wormwheel 36 and lower wing flaps 5 through arms 12 and levers 11. A spring 23 exerts through arm 32 of lever 22 a force tending to move sleeve 30 towards the position shown.