Patent GB-1142611-A (GB)
Title: Improvements relating to fluid dynamic control members for vehicles
IPC: B64D27/02
Filed: 1965-02-16
Abstract: 1,142,611. Controlling aircraft. S. R. TYLER. 14 Feb., 1966 [16 Feb., 1965], No. 6661/65. Headings B7G and B7W. [Also in Divisions F2 and G3] Control forces are generated on an aircraft empennage (either at the tail or the nose) or on a similar structure on a sledge or other land vehicle, or air cushion vehicle, or hydrofoil craft by blowing through spanwise extending slots near the trailing edge. Lift variations that cancel each other can be applied, the resulting induced drag producing a braking effect. The invention is also applicable to marine craft such as submersibles. In one embodiment (Figs. 2 and 3, not shown), the tail is of cruciform configuration, and each member is of circular section and has two blowing slots (20-24) on each side of the trailing edge. In a second embodiment (Figs. 5 and 6, not shown) the tail is in the form of an inverted T, and each member is elliptical with one slot (31, 32) on each side of the trailing edge. Roll, pitch and yaw control forces are produced by appropriate differential blowing, and the braking effect is produced by generating, on different members or different parts of members, lift forces which cancel out but give rise to induced drag (Figs. 4D and 7D, not shown). For this purpose, in the second embodiment, the three arms of the T are divided into inner and outer sections. This induced drag may be controlled automatically to maintain a desired speed, e.g. during a landing approach. There may be, as shown, an additional slot 152, for use only during braking. The aircraft is propelled by an airscrew, ducted fan, or gas turbine engine (such as a by-pass engine), and the control surfaces when at the tail may be mounted in the slipstream or engine efflux, and the air for blowing is provided by air bleed from the bypass duct, or by compressors driven by auxiliary engines. Where ducted fans are used, the engine driving them may be interconnected through free wheels. The air supply to the slots is controlled by valves actuated by a pilot's control column and by the brake control through two mechanical discriminators (44, 55, Figs. 8A, 8B, not shown) each of which converts movement of a yoke (65 or 66) about three axes of a ball joint (68, Fig. 11, not shown) into movements of three valves (41, 42, 43) each of which controls the flows to an opposed pair of slots. Yaw control is effected by twisting the control column (80, Figs. 9 and 10, not shown) which is mounted at its lower end on a ball joint (80) and has a ring (92) through which trim adjustments can be made. Where an additional slot 152 is provided for use only during braking a valve 150 is provided which is only operated by the brake control rod 149. In this embodiment, the flow to the opposed slots 144, 146 is controlled by a fluid amplifier which in the neutral position allows air to discharge through a rearwardly directed slot 145. Movable control surfaces.-The control surfaces may be pivotally mounted for variations in sweep (Fig. 13, not shown), and the pivot axes may be inclined to vary the incidence as the surfaces pivot. In another embodiment (Fig. 12, not shown) the trailing edge, between a pair of slots, is formed by a pivotable cylinder (120) or part-cylinder from which a retractable fin (124) may extend. This is for use at high flight speeds where the blowing control is less effective, and the angular position of the cylinder and the relative flow rates through the slots are varied in unison.