US1551983A - Hydroaeroplane - Google Patents

Description

Sept 1, 1925 1,551,983

C. DORNIER HYDROAEROPLANE Filed Jan, 24. 1925 INVENTOH C'Zaudius Darnier By M ATTORNEY Patented Sept. 1, 1925 UNI-TED STAT PATENT OFFICE.

OF ONE-HALF TO THE FIRM DORNIER-METALLBAUTEN, GESELLSQHAFT MIT.

BESCHRZNKTER HAFTUNG, OF FRIEDBIGHSHAFEN-O'N-THE-BODENSEE, GERMANY.

HYDROAEROPLANE.

Application filed January 24, 1925. Serial No. 4,383.

To all whom it may concern:

Be it known that I CLAUDIUS DORNIER, a citizen of Germany, residin'g'at Friedrichshafen-on-the-Bodensee, Germany, have invented certain new and useful Improvements in 'Hydroaeroplanes, of which the following is a specification.

The present invention relates to a method of staying floats on aircraft.

For thep'urpose of attaching floats to air craft, the usual practice is to construct a framework of struts underneath the actual body of the flying machine, one end of the system of struts being secured to the underside of the body, while the other end-serves for the attachment to the floats. The usual methpd of stifl'ening the framework against transverse and axial thrusts 1s by means of diagonal ties and other wire bracings.

This method of attaching floats to aircraft is attended by numerous disadvantages.-

The' large number of struts and bracings contribute substantially to increasing the un favorable air resistance, Since this arrangement consists of many members, each .of which is essential in itself, the reliabilityin operation is greatly restricted from the outset, especially when it is remembered that very excessive stresses are set up in the individual struts of the framework during bad landings. Consequently, breakage of the float framework are still normal phenomena in the running of float machines. The aforesaid method of construction is also defective in other respects. In the first place, assembling necessitates special appliances and particularly. skilled workmen, so that, infman'y instances the attaching of the floats is a matter of great difliculty.

By contrast, the subject of this invention provides a method of staying the floats which does away with all complicated framework and ensures a very simple and advantageous method of manufacture and very favourable conditions for the attachment of The invention is characterized, substan-' tiall in that at least one pair of rigid unbenging fins or stump wings, to the lower members of which the floats are secured, is arranged on each side of the body of the aircraft The cross-sectional form of the struts is preferably similar to the profile of a propeller, so that not only is the unfavourable wind resistance very low, but at the same time a lifting effect is produced. In

on the water, are taken up by another pair of stump wings arranged at a suitable distance from the first pair. This second pair may also be replaced by other methods of staying. v I

In accordance with the smaller stresses, this second pair of wings may be of considerably lighter construction, and therefore have more the character of an auxiliary structure. Hence this method of staying can be' replaced by any other suitable form, such as simple stay rods which, in certain circumstances can be swung up against the body of the machine, when in the air and the floats are no longer in action, in order to-reduce the air resistance still further. The said auxiliary wings can,'l1o-wever, also be replaced by a continuous auxiliary or connecting member of the bridge type on which the front part of the body of the machine rests.

In developing the invention further, the fixed auxiliary stump wings can be. connected with the floats by hinges, the floats themselves being sprung in relation to the stum -like main wings.

This method of securing or arranging floats on aircraft, by means of such wlngs produces an extremely firmv and simple construction particularly favourable to the stability of the aircraft and rendering the use of stays and braces superfluous. Moreover, the spaces underneath the body of the machine and between the floats can be advantageously utilized for equipment purposes since as already mentioned,;no constructio'nance with the invention is excellently adapted for torpedo work.

Several embodiments are illustrated in the drawing.

Fig. 1 shows a front elevation of an aircraft constructed with floats in accordance with the invention.

Fig. 2 isa side elevation of Fig. 1.

In this embodiment the staying devices used consist for example of main and auxiliary stumps.

Fig. 3 shows a plan of an aircraft forming a further embodiment of the subject of the invention and in this case in addition to the main stump wings, the auxiliary fins being omitted, only a support adapted to swing laterally is provided which is shown in the swung-out position in the drawing. Fig. 4 is a side elevation of Fig. 3, the jib-like supports being shown folded against the body ofthe machine.

In Figs. 1 and 2, a indicates the body of the aircraft, alongside which the main fins or stump wings I) and auxiliary stump wings cfor example in stump formare arranged. The floats cl are secured in the described manner on to the under side of these stumps.

In Figs. 3 and 4 supports or stump wings f provided a auxiliary supports are shown.

These supporting means for example are so mounted that they can if necessary be swung into recesses g.

I claim v 1. Float supporting structure for aircraft comprising a stump wing arranged laterally at one end on eachv side of the body ofthe aircraft and adapted to produce a lifting effect when the aircraft is in flight; and a float secured at the other end of each stump wing and adapted to support the entire weight of the aircraft when on the water. I

2. Float stays for aircraft comprising a pair of rigid stump wings each laterally arranged on one side of the body of the aircraft and to each of which a float is,secured;

and a pair of auxiliary stump wings each arranged on one side of the. body" of the aircraftv which are adapted to counteract the turning moments of the first-named wings. p

3. Float stays for aircraft comprising a pair of rigid stump wings each laterally arranged'on one side of the body of the aircraft and to each of which a float is secured; each wing having a curved on as; section in order to produce a lifting effect when the aircraft is in flight; and a pair of auxiliary stump wings each arranged on one side of the body of the aircraft which are adapted to counteract the turning moments of the first-named stump wings, each of said auxiliary stump wings having a curved cross section in order to produce a lifting eflect when the aircraft is in flight.

4. Float stays for aircraft comprising a pair of rigid stump wings each laterally arranged on one side of the body of the aircraft and to each of which a float is secured; and a pair of auxiliary stump wings each arranged on one side of the body of the aircraft which are adapted to counteract the turning moments of the first-named wings, said auxiliary wings being adapted to be moved to reduce the air resistance when the aircraft is in flight.

5. Float stays for aircraft comprising-a pair of rigid stump wingseach laterally arranged on one side of the body ofthe aircraft and to each of which a float is secured; and a pair of hinged auxiliary stump wings each arranged on one side of the body of the aircraft which are adapted to counteract the turning moments of the first-named stump wings, said auxiliary stump wings due to the hinged connection to the body of the aircraft being adapted to be moved to reduce the air resistance when the aircraft is in flight.

In testimony whereof I aflix my signature.

CLAUDIUS DORNIER.

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