| 摘要 |
<p>952,333. Controlling composite aircraft. ENGLISH ELECTRIC CO. Ltd. April 5, 1961 [April 12, 1960], No. 13030/60. Headings B7G and B7W. [Also in Division H4] Relates to a system for landing a conventional aeroplane 1 with the aid of a piloted flying platform 2 capable of vertical take-off and landing and of horizontal flight at a speed exceeding the normal stalling speed of the aeroplane 1 in which the platform 2 is flown upwards towards the aeroplane 1 from a position below and astern thereof to a position in which contact is made with the wheels of the aeroplane 1, sufficient force is applied thereto to take the full weight of the aeroplane, an automatically or manually controlled lock-on gear secures the aeroplane to the platform and the platform carrying the aeroplane is then landed vertically. According to the present invention an optical or near optical radiation source A is mounted underneath the aeroplane 1, two transversely spaced directional sensing heads B1 and B2, Figs. 1 and 2, on the platform 2 are directed at the source A and means are provided for deriving from the longitudinal component # 1 , Fig. 1, and the lateral components # 1 , # 2 of the sighting angles of the heads B 1 and B 2 the pitch, roll and thrust demand signals required to fly the platform 2 to the aeroplane 1, the pitch and roll demand signals # and # being applied to an automatic pilot and the incremental forward thrust demand signal #T being applied to a flight director display. As described with respect to Figs. 4, 5 and 6 (not shown), the demand signals are computed in accordance with the equations where A, B ... G are constants, the pitch and roll ratio d#/dt and d#/dt are measured by rate gyros and a is the forward acceleration. Each sensing head may comprise an auxiliary reflector near the focus of a main parabolic reflector and a radiation sensitive cell at the centre of the main reflector, Fig. 3 (not shown).</p> |
