Patent GB-400292-A (GB)
Title: Improvements in means for launching aircraft
IPC: B64D5/00
Filed: 1932-04-26
Abstract: 400,292. Aircraft carrying other aircraft. MAYO, R. H., 39, St. James's Street, London. April 26, 1932, No. 12013. [Class 4.] A composite aircraft comprises two component aircraft each capable of independent sustained flight mounted one on top of the other and initially connected together by rigid but releasable locking means in such a manner as to enable the composite aircraft to take off, fly and land with the wings of both components contributing in an efficient manner towards the total lift required for such flight, and having means for increasing the angle of incidence or otherwise increasing the lift co-efficient of the wings of the upper component relatively to the lower component during flight of the composite aircraft as such and while the two components are still attached together. Fig. 1 shows an upper component 12 mounted on a lower component 13 by means comprising co-axial axles 14 projecting from opposite sides of the floats of the upper component which are received in co-axial sockets 15 mounted above the wings of the lower component, locking pins 16, Fig. 6, initially preventing disengagement. This arrangement may be reversed the sockets being then carried by the upper component. The slot in the socket is sloped to ensure upward and forward disengagement but this may be varied in different cases. An adjustable rear support 17 is pivoted at 18 to component 13 and connected to component 12 at the tail end. When detached from the upper component member 17 turns about its pivot and is received in socket 20 as shown in Fig. 11. After release of member 17 the tail of the upper component is lowered by operation of the elevator to increase the lift co-efficient of the main planes, whereby the craft will fly clear as soon as pins 16 are withdrawn. Means to prevent lateral movement of the axles may be fitted and one eontinuous axle may be used. In the case of a land machine, Fig. 11, an axle 14 connected by struts to the body may be used or the wheel axle itself in which case means are provided for locking shock absorbers and the like in their extended position. Fig. 11 shews an automatic release mechanism operated by lowering of the tail of the upper component, this comprises a hook 21 fixed to the axle 14 and co-operating with a stop 22. More than one such releasing means may be fitted e.g. two lateral sockets and axles comprising automatically freed hooks set to release just prior to that of a central mounting, the lateral securing means serving to prevent rolling. Various modifications of this device are described. In one form the locking hook and restraining projection may take the form of a rack and pinion which engage together the pinion being provided with braking means. All external mounting parts may be retractable. Locking means of the type shewn in Fig. 6 may be releasable only by a combined or consecutive operation of controls located in both components. Alternatively they may be released automatically by lowering of the tail or by the operation of means for increasing the incidence or lift of the upper wings which do not involve change of attitude of the upper component. Fig. 7 shews one form of automatic means for preventing withdrawal of axle 14 should the upper component have insufficient excess of lift. A trip device may be fitted operable on movement of the upper component out of its socket which device may close the throttle of the lower component, switch off the ignition, or operate a lift spoiling device to ensure ready separation of the two components. Guards may be fitted to prevent undue longitudinal tilting of the upper component after release. The upper component may comprise two aircraft one carried by the other.