US1689807A - Hydroplane - Google Patents
Hydroplane Download PDFInfo
- Publication number
- US1689807A US1689807A US151058A US15105826A US1689807A US 1689807 A US1689807 A US 1689807A US 151058 A US151058 A US 151058A US 15105826 A US15105826 A US 15105826A US 1689807 A US1689807 A US 1689807A
- Authority
- US
- United States
- Prior art keywords
- supplementary
- runners
- pontoons
- aeroplane
- attached
- 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 - Lifetime
Links
- 238000010276 construction Methods 0.000 description 3
- 239000002828 fuel tank Substances 0.000 description 1
- 210000003141 lower extremity Anatomy 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C35/00—Flying-boats; Seaplanes
Definitions
- This invention relates toimprovements in aeroplanes and in particular. to adjustable devices so as to render the aeroplane more useful. 7 a
- the object of the invention is to provide a means of permitting the aeroplane to land on waterg-snow, ice or the like.
- Fig. 1 shows a side elevational view of an aeroplane equipped with my improved device.
- Fig. 2 shows a front elevational view thereof.
- y y I Fig. 3 shows a top plan view thereof.
- Fig. 4 shows an enlarged longitudinal detail sectional view of my improveddevice.
- Fig. 5 shows an enlarged transverse sec-' tional view taken on the line 55 of Fig. 4.
- Fig. 6 shows a further development of my improved device.
- the fuselage 10 the body 11, the motor 12,
- the controls 15, the fuel tank 16 are the general elements of an acreplane, such as commonly used for flying. It
- the struts 16 extend downwardly from the body 11 and are hinged, as at 18, to the pontoons 19, which extend longitudinally to the body 11.
- the pontoons 19 are formed or shaped so'as to provide a V shaped section, terminatingin a pointed element 20.
- the above described construction being such as will permit the pontoons 19 to be 'displaced'from the body 11, so as to provide a better means of landing on the said pontoons. Itbeing.understoodthat the struts 16, may be hinged to the lugs 21, for the purpose as here stated;
- a means of extending the supplerotatively mounted in suitable supports attached to the pontoon 22 The bevel pinions 30 and 31 are attached to the shafts 28 and 29, respectively and mesh with the bevel pinions 32 and 33., respectively, attached to the worm wheels 34 and 35, respectively.
- the worm wheels 34 and 35 are rotatively mount-- ed in the pontoon 19 and mesh with Worm racks 36 and 37, slidablymounted in the run 1101' 22.
- the supplementary runner 22 is of convex construction andv extends the entire length of the runner 20.
- runners attached to pontoons, and a means of extending the said supplementary runners.
- An aeroplane comprising pontoons, supplementary runners attached to the said pontoons and a means of'extending the said supplementary runners.
- An aeroplane comprising pontoons, supplementary runners mounted in the said pontoons, and a means of extending the said supplemenary runners.
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Tents Or Canopies (AREA)
Description
Oct. 30, 1928 1,689,807
c. H. TRAVER HYDRO-PLANE Original Fil ed Nov. 27, 1926 2 sheets-sheet 1 IN VENT OR T BY C df/ HjFaver ATTORNEY Get. 30, 1928.
C. H. TRAVER HYDROPLANE Original Filed Nov. 27, 1926 2 Sheets-Sheet INVENTOR Car/ H. Tmver' A TTORNEY Patented Oct. 30, 1928.
UNITED STATES PATENT OFFICE.
CARL TRAVER, OF BINGHAMTON, NEW YORK.
' nxnnornnnn.
Application filed November 27, 1926, Serial No. 151,058. Renewed April 18, 1928.v
This invention relates toimprovements in aeroplanes and in particular. to adjustable devices so as to render the aeroplane more useful. 7 a
The object of the invention is to provide a means of permitting the aeroplane to land on waterg-snow, ice or the like. I p
In the accompanying drawings:
Fig. 1 shows a side elevational view of an aeroplane equipped with my improved device.
Fig. 2 shows a front elevational view thereof. y y I Fig. 3 shows a top plan view thereof.
Fig. 4 shows an enlarged longitudinal detail sectional view of my improveddevice.
Fig. 5 shows an enlarged transverse sec-' tional view taken on the line 55 of Fig. 4.
Fig. 6 shows a further development of my improved device. t
The fuselage 10, the body 11, the motor 12,
operatively connected to the propeller 13, the
being understood that I do not necessarily limit the use of'my invention to monoplanes such as here illustrated, but to biplanes and all types and classes of aeroplanes such as are manufactured and used for all purposes.
Referring in particular to Fig. 6 of the accompanying drawings in which the undercarriage comprises a plurality of struts 16,
hinged, as at 17, to the body 11. The struts 16, extend downwardly from the body 11 and are hinged, as at 18, to the pontoons 19, which extend longitudinally to the body 11. The pontoons 19 are formed or shaped so'as to provide a V shaped section, terminatingin a pointed element 20. The above described construction being such as will permit the pontoons 19 to be 'displaced'from the body 11, so as to provide a better means of landing on the said pontoons. Itbeing.understoodthat the struts 16, may be hinged to the lugs 21, for the purpose as here stated;
Referring in particular to Figs; 4 and 5 of the accompanying drawings in which I have provided a means of extending the supplerotatively mounted in suitable supports attached to the pontoon 22. The bevel pinions 30 and 31 are attached to the shafts 28 and 29, respectively and mesh with the bevel pinions 32 and 33., respectively, attached to the worm wheels 34 and 35, respectively. The worm wheels 34 and 35 are rotatively mount-- ed in the pontoon 19 and mesh with Worm racks 36 and 37, slidablymounted in the run 1101' 22. The supplementary runner 22 is of convex construction andv extends the entire length of the runner 20. {The worm racks 36 and 37 are attached at'their lower extremities to the supplementary runners 22. The above described construction being such as will permi tthe hand wheel 23, when turned or rotated, to lower or extend the supplementary I runner 22, for the purpose as hereinbefore set forth. v Having thus described my invention, what I claim asnew'and desire to protect by Let ters Patent of theUnited States is as follows: i
1. In an aeroplane, runners attached to pontoons, and a means of extending the said supplementary runners.
2. An aeroplane comprising pontoons, supplementary runners attached to the said pontoons and a means of'extending the said supplementary runners.
An aeroplane comprising pontoons, supplementary runners mounted in the said pontoons, and a means of extending the said supplemenary runners.
- 4. In an aeroplane, a means of extending runners attached to pontoons, a hand-wheel operatively connected to the said supplementively connected to supplementary runners,
asa means of extending the said supplementary runners, said supplementary runners mounted in pontoons.
supplementary runners, said supplementary In testimony whereof I have affixed my signature.
CARL H. TBAVEE:
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US151058A US1689807A (en) | 1926-11-27 | 1926-11-27 | Hydroplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US151058A US1689807A (en) | 1926-11-27 | 1926-11-27 | Hydroplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US1689807A true US1689807A (en) | 1928-10-30 |
Family
ID=22537159
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US151058A Expired - Lifetime US1689807A (en) | 1926-11-27 | 1926-11-27 | Hydroplane |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US1689807A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2544794A (en) * | 1950-03-14 | 1951-03-13 | Bell Aircraft Corp | Helicopter amphibious landing gear |
-
1926
- 1926-11-27 US US151058A patent/US1689807A/en not_active Expired - Lifetime
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2544794A (en) * | 1950-03-14 | 1951-03-13 | Bell Aircraft Corp | Helicopter amphibious landing gear |
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