US2325630A

US2325630A - Glider launching device

Info

Publication number: US2325630A
Application number: US456908A
Authority: US
Inventors: James N Petty
Original assignee: Individual
Current assignee: Individual
Priority date: 1942-09-01
Filing date: 1942-09-01
Publication date: 1943-08-03
Anticipated expiration: 1960-08-03

Description

Aug. 3, 1943. J. N. PETTY GLIDER LAUNCHING DEVICE Filed Sept. 1, 1942 Patented Au 3, 1943 UNITED STATES if PATENT OFFICE e 2,325,630 l d GLIDER LAUNCHlNG DEVICE James N. Petty, Madcopa County, Ariz. Application September 1, 1942, Serial No. 456,908

4 Claims. (01. 244-73) This invention pertains to devices'for launching gliders, and has for itsobjects:

The provision of amechanism which can be built inor attached to a glider or sail plane of ordinary construction, equipped with landing wheels and when so attached may be used to launch the glider from runways adjacent flying fields or some other suitable terrain.

A further object of the device is to provide a jetpropulsion unit which may be easily and quickly, attached to a glider having landing wheels.

A third object is to provide means contained within the glider body whereby a jet propulsion unit may be attached to-the glider body and after launching the glider may be detached by mechfuselage and retained between these hooks on either sidethereof.

Construction of this force chamber has been described in my previous application heretofore filed,1 Serial No. 447,022... This chamber consists of. a steel vessel having .a rounded nose I1 and converging conically shaped sides l3 ending in a dischargejet nozzle i9 at the rear. Thefflow of compressed gases within the vessel is controlled by a valve intermediate the jet nozzle and the rear portion of the vessel.

It is to be understood that there are two hooks l4 and I5 made in pairs, left and right parts, re-

' spectively, and attached to each side of the beam anism operated from within the cockpit so that the jet propulsion unit is dropped to the ground thereby freeing the glider of its weight.

A further object is to provide a Jetpropulsion unit adapted for use with the apparatus above' described, which is so constructed that when discharged from a glider at an altitude of several hundred feet will drop to the ground in a ver- .tical position and so as not to damage any of its .mechanism, either with or without the use of a partially supporting parachute.

Other objects will appear hereinafter.

I attain the foregoing objects by means of the devices and construction illustrated in the accompanying drawing, in1which-- 2 Figure 1 is a side elevation of the device as installed in a glider; the portions of the glider body being shown in dotted outlines to illustrate the position of the device;

. Figure 2 is a transverse sectional view taken substantially on lines 2-2, Figure 1;

Figure 3 is a transverse sectional view taken l substantially on lines 3-3, Figure 1;

Figure 4 is a plan view. Similar numerals refer to similar parts in the several views. a

Reference number 2 indicates the forward end" of the fuselage of the glider; 3, the hood; 4, the. landing gear; 5, the seat, and 5 indicates the cockpit area. i l Along the lower centralportion of. the fuselage there is a longitudinally extending beam H) which may be termed the base beam of my device. Attached on either side of this by bearing supports H and i2 are hooks or claws i4 and 15. The lower portions of these hooks are shaped to conform to the outer contour of the jet propulsion force chamber l6 positioned below the i0. Their shaping and bearing supports are symmetrical relative to a plane drawn vertically through beam ill. The upper ends of these hooks l are provided with a pivot joint which connects them to hinged levers 26 and 21, joined and connected at the middle by a pin joint 28. The pin holding this joint is turned down from the end of a longitudinally extending bar 30 which may be termed theoperating bar. The hooks are so shaped and proportioned that when they are holding the pressure vessel l6, as shown in Figure 2, the levers 26 and.2'l are aligned so as to form a semi-cantlever link construction providing a definite stop which locks the hooks in closed position around the vessel.

The hooks are releasedby an upward move-- ment of the longitudinaloperating bar 30 which draws the upper ends togetherand separates the upward movement of thisoperating bar 30 is effected by a pair of links 32 and 33. Thelower linknbeing pivotally attached to the base beam in at 34 and the upper link to the middle of the cross beam 30 at 35. Links 32 and 33 are connected at the middle at 36 in such a manner that the draw bar 31 is pivotally sustained between them. A crank 40 is attached to the lower end of link 32 and this pivotally attached to a link 4|, which connectsto the lower end of an operating lever 42, at its forward end. This operating lever is 1 pivoted onthe beam' l D at43 and extends upward to a convenient position within the cockpit area 6. It is to be understood that links 32 and 33 V and links M are duplicated on each side of beam sists of a sheet metal foldfshown particularly.

in Figure 3. Support is afforded by a compara- Push rod 31 extends forward along the The downward position is indicated in solid lines in Figure l and the withdrawn or upper position is indicated by dotted outlines 55. When in the downward position the rear edges of the two folds areshaped to fit the nose contour of the forward end ll of the pressure vessel it. This forms a substantial brace against which the forward push of the discharg nozzle, communicated through the body of the "pressure vessel, Inay push and exert its forward force motion. An assistant spring 56 may be attached to the flanged portio which bears the pin 35.

Valve 28 on pressure vessel I 6 is controlled from the cockpit by means of a removable key 60 which fits into the stem of the valve and is carried on a shaft 6| extending into the fuselage and supported on a bearing sleeve or beam H). The chain 62 transmits motion through sprockets 63 from crank 64 manipulated by the operator. It will be noticed that the construction of the key 60 fitting into valve 20 is such that downward motion of the pressure vessel l6 will release it from the valve stem without any frictional engagement or binding. On either side of the pressure vessel there are lugs 66 just to the rear of the forward hooks [5.

In operation the pressure vessel is filled with compressed air or other gases, to as many pounds per square inch as its structure will permit. The pressure vessel may also include a propulsive jet formed by burning and expansion of gases. The pressure vessel is then attached to the under side of the fuselage by means of the hooks l4 and I5 and pressed forward against the nose piece 50. Lug 66 prevents any rearward motion while assembling.

It is to be understood that this is to be used on gliders with some type of running gear. The operator being ready to take off opens valve 20 by manipulating crank 64. Release of gases from pressure vessel through nozzle 19, creates force, giving a forward thrust parallel to the axis vessel which pushes the ship forward until flight is attained. After the pressure of the gases in the force chamber l6 has been expanded the operator releases the forcechamber by a forward motion of lever 42. This motion raises the operating bar 30 which, in turn,- opens hooks l4 and I5 and releases the pressure vessel, which drops vertically in a horizontal position for a short distance. The nose then, being heavier than the rear, heads downward and this motion, nose first,

lines 55. The glider is then free of the weight of the pressure vessel and is manipulated in the usual manner. The pressure vessel lands on the nose portion which is well protected and strongly constructed. It is recovered, filled and used again.

To those familiar with the art various changes and modifications may suggest themselves, all of which may, however, well remain within the spirit of the invention, therefore, I wish to be limited only by the following claims.

I claim:

l. A glider launching device comprising a pressure vessel having a rearwardly extending jet nozzle, and a pressure-control valve, pivotally supported hooks positioned within the glider body adapted to engage the sides of said pressure vessel, a nose piece extending downward from the underside of the glider body adapted to engage the forward end of said pressure vessel, and mechanism operative within the glider body adapted to control said pressure release valve, and mechanism positioned within the glider body adapted to release said hooks from said pressure vessel, 7

2. Launching mechanism for gliders provided with running wheels, including, in combination, a pressure vessel having a rearwardly extending jet nozzle and a pressure control valve, a plurality of pairs of tong hooks pivotally attached within the glider body and extending downwardly therefrom adapted to hook onto and engage portion of the sides of said pressure vessel, a nose piece hingedly attached to said glider body adapted to extend downwardly to engage the forward end of said pressure vessel, links connecting the upper ends of said hooks whereby they may be locked in closed position supporting said pressure vessel. or moved from said locked position to effect a release from said engaging position, lever mechanism control by an operative handle within said glider body adapted to move said links to a releasing position and concurrently move said nose piece from the downwardly extending engaging position to a position within the glider body, together with control mechanism extending into said glider body adapted to control the pressure release valve on said pressure vessel fromwithin the cockpit area of said glider.

3. Launching mechanism for gliders having a body including a cockpit and provided with running gear, including, in combination, a pressure vessel having a jet nozzle, a plurality of hinged tong hooks and a pressure nose piece, adapted to releasably hold said vessel in operative position under said glider body, together with interconnecting links attached to said hooks and lever mechanism operative from the glider cockpit, for releasing said hooks simultaneously and withdrawing said nose piece.

4. Launching mechanism for gliders having a body including a cockpit and provided with running gear including, in combination, a pressure vessel having a propulsive jet nozzle, a pressure release valve, a plurality of hinged hooks adapted tosecure said vessel beneath said glider body, a nose piece adapted to maintain it in longitudinal position, link and lever mechanism including an operative handle within said cockpit adapted to operate said hooks'to release said vessel and withdraw said nose piece into said glider, and mechanism including a handle within said cockpit for operating said pressure release valve on said vessel when in operative position beneath said glider body and disconnect when said vessel is released.

JAMES N. PETTY.