GB400292A - Improvements in means for launching aircraft - Google Patents
Improvements in means for launching aircraftInfo
- Publication number
- GB400292A GB400292A GB1201332A GB1201332A GB400292A GB 400292 A GB400292 A GB 400292A GB 1201332 A GB1201332 A GB 1201332A GB 1201332 A GB1201332 A GB 1201332A GB 400292 A GB400292 A GB 400292A
- Authority
- GB
- United Kingdom
- Prior art keywords
- component
- upper component
- aircraft
- lift
- axle
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
- 239000002131 composite material Substances 0.000 abstract 3
- 239000006096 absorbing agent Substances 0.000 abstract 1
- 230000004048 modification Effects 0.000 abstract 1
- 238000012986 modification Methods 0.000 abstract 1
- 230000000452 restraining effect Effects 0.000 abstract 1
- 238000005096 rolling process Methods 0.000 abstract 1
- 238000000926 separation method Methods 0.000 abstract 1
- 230000035939 shock Effects 0.000 abstract 1
- 230000002459 sustained effect Effects 0.000 abstract 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D5/00—Aircraft transported by aircraft, e.g. for release or reberthing during flight
Landscapes
- Engineering & Computer Science (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
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.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1201332A GB400292A (en) | 1932-04-26 | 1932-04-26 | Improvements in means for launching aircraft |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1201332A GB400292A (en) | 1932-04-26 | 1932-04-26 | Improvements in means for launching aircraft |
Publications (1)
Publication Number | Publication Date |
---|---|
GB400292A true GB400292A (en) | 1933-10-26 |
Family
ID=9996834
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB1201332A Expired GB400292A (en) | 1932-04-26 | 1932-04-26 | Improvements in means for launching aircraft |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB400292A (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN106915450A (en) * | 2017-03-10 | 2017-07-04 | 佛山市神风航空科技有限公司 | The landing modes and its device of a kind of aircraft |
US10611498B2 (en) | 2017-08-24 | 2020-04-07 | Aurora Flight Sciences Corporation | Rail recovery system for aircraft |
CN111452975A (en) * | 2020-04-13 | 2020-07-28 | 宋有洲 | Multifunctional aircraft |
-
1932
- 1932-04-26 GB GB1201332A patent/GB400292A/en not_active Expired
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN106915450A (en) * | 2017-03-10 | 2017-07-04 | 佛山市神风航空科技有限公司 | The landing modes and its device of a kind of aircraft |
US10611498B2 (en) | 2017-08-24 | 2020-04-07 | Aurora Flight Sciences Corporation | Rail recovery system for aircraft |
CN111452975A (en) * | 2020-04-13 | 2020-07-28 | 宋有洲 | Multifunctional aircraft |
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