US1362292A - Aeroplane - Google Patents

Aeroplane Download PDF

Info

Publication number
US1362292A
US1362292A US368005A US36800520A US1362292A US 1362292 A US1362292 A US 1362292A US 368005 A US368005 A US 368005A US 36800520 A US36800520 A US 36800520A US 1362292 A US1362292 A US 1362292A
Authority
US
United States
Prior art keywords
chassis
tails
machine
base
aeroplane
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
Application number
US368005A
Inventor
Gunderson Ole
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Individual filed Critical Individual
Priority to US368005A priority Critical patent/US1362292A/en
Application granted granted Critical
Publication of US1362292A publication Critical patent/US1362292A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C35/00Flying-boats; Seaplanes

Definitions

  • Ione feature of the invention is the arrangement of its supporting chassis.
  • Another feature is the special seaty for the driver.
  • Another feature is -the special anchor.
  • Figure 1 is a side elevation of the machine about to ascend.
  • Fig. 2 vis a plan view of the machine in iii ht, the planes being dotted only. he body of the machine is broadly designated by the letter B, P are the planes, T the tails controlled by a steering device or stick S, and E the motor or engine controlled by a lever L; and no novelty is claimed for the pa rts mentioned.
  • the vdriving mechanism in the present case consists of a relatively small propeller l having two blades and mounted on a shaft 2 which rotates in a bearing 3, and a relatively large two-bladed propeller 4 mounted on a sleeve 5 surrounding the shaft 2 'and in its own bearing 6,'this propeller having its blades pitched and therefore as a whole rotating'oppositely'to the other and in a pla-ne a little distance from it.
  • Power is communicated from the motor or engine E to the shaft and sleeve in any suitable manner,v
  • the seat being mounted on standards or supports 12 which hold it-rigid with the body no matter what position the latter-assumes.
  • the drlver will sit on the seatbottom 10, but when ascending or starting along ⁇ a practic ally vertical line he ⁇ will slide back and sit on the seatback 11 as indicated in Fig. 1, and the bottom should be rather narrow ⁇ so'Y that his legs can pass astride it at this time.
  • the harness for holding him in place will be constructed with a view to permitting him to shifthis position as thus suggested.
  • the launching and landing devices employed in connection with the machine vas thus described are specially constructed in order that the body B will stand almost vertical when the base of the chassis rests ⁇ on the ground.
  • .Said chassis is herein shown asv having a pair of front legs 20 leading ⁇ downward and rearward from the body Band diverging from each other, and a single rear leg 21 leading back from the body to a point beyond the tails, or at least to such point that it will hold the tails oft' the ground; and 22 designates truss rods for bracing the legs.
  • This chassis may have for its base any suitable supports Vvs uch as skids, shoes, pontoons, or wheels 23 and 24 as shown; but it is limportant that, whatever the form taken by the supports,'the base of the chassis shall stand nearly at right angles to the length of the body. Therefore when said base (the wheels as shown) rests on the ground the body B stands upright on forward a little from a strictly vertical line.
  • an anchor herein shown as composedy of a. rope 25 connected with some part of the chassis and hanging therefrom, and a spring clip 26'carr1ed by.
  • theV rope and adapted to be engaged lwith some fixed object such 'as the stump 27 herein illustrated, although of course any hea object such as la stone or perhaps an. atten ant vwould answer.
  • the purpose of thel anchor is to hold the machine upright on ⁇ its base ready to start, and thev spring clip will ⁇ slip off the object 27 (or be released by the', "attendant) when the start is made.
  • a launchlng and landing chassis carried by the body with its base substantially at right angles to the length of suchbody, and anchoring mechanism adapted to make frictional engagement with some fixed object.
  • the combination with a body and its tails and driving mechanism iXedly supported fromthe body adjacent the controls and including a narrowbottom and a back at-right angles' thereto;y of a launching'l chassis carried by the body for holding the latter substantially vertical with its tails 'above the surface, and anchoring mechanism includ'- ing a rope cbnnected with the body and a spring clip carried by the rope and l'adapted to engage a fixed object.

Description

Q.GUNDERS0N.
AEHOPLANE.
vAPPLICATION FILED MAR. 23. i920.
Patented De@.14,1920.
OZe @a/mnsm l UNITED STATES PATENT OFFICE.
OLE eUNDEnsoN, or scHENEcTA'DY, NEW Yoan.
AEROPLAN E.
Application led March 23, 1920. Serial N0. 368,005.
A V'more especially to launching and landing devices; and the object of the same is primarily to construct a flying machine which is deslgned and intended to rise along a substantially vertical line under the impulses of its own propellers. 'l
In carrylng out this object, Ione feature of the invention is the arrangement of its supporting chassis.
Another feature is the special seaty for the driver.
Another feature is -the special anchor.
Details of the invention as applied to any ordinary biplane are set forth below` and shown in the drawings wherein:
Figure 1 is a side elevation of the machine about to ascend.
Fig. 2 vis a plan view of the machine in iii ht, the planes being dotted only. he body of the machine is broadly designated by the letter B, P are the planes, T the tails controlled by a steering device or stick S, and E the motor or engine controlled by a lever L; and no novelty is claimed for the pa rts mentioned.
The vdriving mechanism .in the present case consists of a relatively small propeller l having two blades and mounted on a shaft 2 which rotates in a bearing 3, and a relatively large two-bladed propeller 4 mounted on a sleeve 5 surrounding the shaft 2 'and in its own bearing 6,'this propeller having its blades pitched and therefore as a whole rotating'oppositely'to the other and in a pla-ne a little distance from it. Power is communicated from the motor or engine E to the shaft and sleeve in any suitable manner,v
as for instance by the bevel gearing broadly indicated at 7 in Fig. 1.v
The drawings show the elements L and S for controlling the engine and for steering, and these elements will stand within reach f of an operator mounted' on vhis seat. The latter -in this case lis specially constructed,
vthe ground h aving a bottom 10 and a back 11 at about rlght angles to it, and both being rather narrow as shown in Fig. 2, the seat being mounted on standards or supports 12 which hold it-rigid with the body no matter what position the latter-assumes. Ordinarily the drlver will sit on the seatbottom 10, but when ascending or starting along` a practic ally vertical line he `will slide back and sit on the seatback 11 as indicated in Fig. 1, and the bottom should be rather narrow` so'Y that his legs can pass astride it at this time. The harness for holding him in place will be constructed with a view to permitting him to shifthis position as thus suggested. l
The launching and landing devices employed in connection with the machine vas thus described are specially constructed in order that the body B will stand almost vertical when the base of the chassis rests `on the ground. .Said chassis is herein shown asv having a pair of front legs 20 leading `downward and rearward from the body Band diverging from each other, and a single rear leg 21 leading back from the body to a point beyond the tails, or at least to such point that it will hold the tails oft' the ground; and 22 designates truss rods for bracing the legs. This chassis may have for its base any suitable supports Vvs uch as skids, shoes, pontoons, or wheels 23 and 24 as shown; but it is limportant that, whatever the form taken by the supports,'the base of the chassis shall stand nearly at right angles to the length of the body. Therefore when said base (the wheels as shown) rests on the ground the body B stands upright on forward a little from a strictly vertical line. In connection with this structure I preferably make use of an anchor, herein shown as composedy of a. rope 25 connected with some part of the chassis and hanging therefrom, and a spring clip 26'carr1ed by. theV rope and adapted to be engaged lwith some fixed object such 'as the stump 27 herein illustrated, although of course any hea object such as la stone or perhaps an. atten ant vwould answer. The purpose of thel anchor is to hold the machine upright on `its base ready to start, and thev spring clip will` slip off the object 27 (or be released by the', "attendant) when the start is made.
In launching a machine as thus constructed, it is stood on the base of its chassis as seen Fig. 1 and anchored `ifan anchorv and by preference inclined olf the object 27, the retarding eect of the anchor no longer prevails, and the aeroplane rises along a substantially vertical line up which it is pulled by the combined action of the two propellers. When the desired altitude has been attained, the operator through his controls puts the machineon an even keel and continues his fli'ght as usual.
When a landing is to be made, the machine is steered to a point near the surface and then its nose turned upward, the speed of the propellers is retarded and the momentum of the machine soon ceases, and then by proper control the operator can permit the machine to settle tail-first 'until he' lands on the base'of the chassis with the nose of the machine in the air and again in the position occupied at starting. In other words, launching' is eectedy by use of a. chassis which holds the machine' with its nose upward,'and employment of themotor and propellers; and landing is efected by a tail drive, while descent is retarded and controlled by the same propellers. It is obvious that the wheels 23 and 24 might be replaced by other forms of shoes, and even pontoons could be used at the base of the chassis so that the machine could rise from and ali ht upon the water.
hat is claimed as new is:
1. In anaeroplane, a launchlng and landing chassis carried by the body with its base substantially at right angles to the length of suchbody, and anchoring mechanism adapted to make frictional engagement with some fixed object.
2. The combination with an aeroplane including a-body and tails; of a chassis including a rear leg projecting from the bodyv beyond `the tails, fixed front legs", and supports o n said legs producing ay base for the chassis standing in a plane substantially at' right angles to the length of the body.
3. The combination with. an aeroplane including a body and tails;'of a chassisincluding a rear leg projecting from the body beyondthe tails, front legs projecting obliquely downward .and rearward from the front of the body and diverging fromV each the controls, and a seat Leeaaea cludingabody andtailsmfa launchin chassis including legs projecting obliquely rom the front of the body, and beyondthe tails from the rear of the body, and wheels on said legs in a plane substantially at right angles to the length of the body, and anchoring mechanismincluding a spring clip suspended from said chassis and adapted to make frictional engagement with some fixed ob- 'ect., J 5. In an aeroplane, the combination with a bodyfand its tails and driving mechanism, the controls, and a seat ixedly supported from the body adjacent the controls and including a narrow bottom and aback at right angles. thereto; of a launching chassis carried by the body and with its base in a plane across the rear of the tails substantially at right angles to the length of the bOdy;
6. In an aeroplane, the combination with a body and its tails and driving mechanism, iXedly supported fromthe body adjacent the controls and including a narrowbottom and a back at-right angles' thereto;y of a launching'l chassis carried by the body for holding the latter substantially vertical with its tails 'above the surface, and anchoring mechanism includ'- ing a rope cbnnected with the body and a spring clip carried by the rope and l'adapted to engage a fixed object.
7l. he combination with an' aeroplane including a lbody and. tails; of a chassisincluding a rear leg rojecting from the body beyond the tails, ront legs projecting obliquely rearward from the frontof the -body and diverging from each other, braces for the legs holding their-lower ends in a plane substantially at right angles tothe length of the body, and anchoring mechanism including a rope y'connected with the braces andv means on said rope adapted to makefric,
tional engagement with some fixed object.
In testimony whereof I aiiix mysignature in the presence of two witnesses.
US368005A 1920-03-23 1920-03-23 Aeroplane Expired - Lifetime US1362292A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US368005A US1362292A (en) 1920-03-23 1920-03-23 Aeroplane

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US368005A US1362292A (en) 1920-03-23 1920-03-23 Aeroplane

Publications (1)

Publication Number Publication Date
US1362292A true US1362292A (en) 1920-12-14

Family

ID=23449488

Family Applications (1)

Application Number Title Priority Date Filing Date
US368005A Expired - Lifetime US1362292A (en) 1920-03-23 1920-03-23 Aeroplane

Country Status (1)

Country Link
US (1) US1362292A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2837302A (en) * 1953-11-27 1958-06-03 Anthony L M Pirrone Flying machine
US5056737A (en) * 1989-04-05 1991-10-15 Gec-Marconi Limited Vtol aircraft with movable undercarriage
US5560568A (en) * 1993-01-22 1996-10-01 Freewing Aerial Robotics Corporation Recovery system and method for capturing and securing an air vehicle to landing platform
US9731816B2 (en) * 2014-12-08 2017-08-15 The Boeing Company Multi-position landing gear

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2837302A (en) * 1953-11-27 1958-06-03 Anthony L M Pirrone Flying machine
US5056737A (en) * 1989-04-05 1991-10-15 Gec-Marconi Limited Vtol aircraft with movable undercarriage
US5560568A (en) * 1993-01-22 1996-10-01 Freewing Aerial Robotics Corporation Recovery system and method for capturing and securing an air vehicle to landing platform
US9731816B2 (en) * 2014-12-08 2017-08-15 The Boeing Company Multi-position landing gear

Similar Documents

Publication Publication Date Title
US20160176514A1 (en) Rotary wing drone
US3103327A (en) Helicopter control system
US1672163A (en) Aircraft
US2640549A (en) Jet-driven sustaining propeller for aircraft
US1362292A (en) Aeroplane
US1825363A (en) Water plane
US2403456A (en) Aircraft hold-down device
US1568765A (en) Helicopter
US1880520A (en) Airplane
US1669758A (en) Helicopter
US1652554A (en) Aircraft
US1308997A (en) Aeroplane
US2681775A (en) Convertible airplane having autorotatable sustaining elements
US1688186A (en) Air vehicle
US1793368A (en) Toy helicopter aeroplane
US2976935A (en) Jet drive rotary wing system
US1166488A (en) Aeroplane.
US1708249A (en) Airplane
GB1405938A (en) Toy
US1996750A (en) Autorotative wing aircraft
US1019988A (en) Flying-machine.
US1573228A (en) Helicopter
US1771724A (en) Land and water aeroplane
US1721935A (en) Aircraft
US1345970A (en) Airplane