US3128574A - Aerial flight device - Google Patents

Description

April 1964 B. SUNRA-Y' 3,128,574

AERIAL FLIGHT DEVICE.

Filed March 29;, 1962';

v INVEMTORL ,B'ernard Jun-ray" United States Patent 3,128,574 AERIAL FLIGHT DEVICE Bernard Sunray, Box 254, Crystal River, Fla. Filed Mar. 29, 1962, 'Ser. No. 183,661 8 Claims. (Cl. 46-74) In my prior copending applications Serial Numbers 729,477, filed April 18, 1958; 764,888, filed October 2, 1958; and 9,210, filed February 17, 1960, now Patents Numbered 3,084,475, April 9, 1963; 3,- 085,363, April 16, 1963; and 3,084,476, April 9, 1963, respectively, I have disclosed aerial flight instruments of the multi-stage type wherein two or more discrete flight stages are separably connected for launching as a unit. The main flight stage has propelling means of suflicient power to initially propel all assembled stages. In flight, as the power of the main flight stage is expended, or drops to a certain value, the second or auxiliary stage is automatically expelled or separated from the main stage and given an initial thrust or impulse in the flight direction. The auxiliary stage may also be equipped with its own propelling means, operation of which is prevented as long as the stages are assembled but automatically placed in operation by separation of the stages. Three or more stages may be thus connected for launching as a unit and for successive separation in flight.

In my aforesaid prior application the propeller of the main stage and that of the auxiliary stage or stages, is permanently journaled upon the stage or fuselage. After the propelling energy of the stage has been exhausted, the propeller and its driving bands act to retard, rather than to assist flight.

It is the chief purpose of the present invention to obviate this drawback by providing a flight device or stage in which the propeller and its driving bands are separated from the stage or fuselage and drop away when the power of the bands has been largely expended.

Another object is to provide a flight device as aforesaid wherein the separation of the propeller and driving bands is effected automatically by and in response to substantial depletion of energy of the bands to thereby greatly decrease the air resistance of the stage and correspondingly increase its range and flight characteristics.

A further object is to provide a flight instrument as aforesaid, which may be of the singleor multistage type and, if of the multi-stage type the same mechanism eifects separation of the stages and separation of the propeller and driving bands from the stage presently driving the assemblage in flight.

Yet another object is to provide an aerial flight device of the character mentioned, wherein not only the propeller and its driving bands but also the propeller mounting and journaling means is automatically separated, thus still further reducing the weight and air resistance of the parts in flight and correspondingly improving range and flight characteristics of the stage.

Another object is to provide an aerial flight device of the type described which is both amusing and instructive and which, when used as a single stage, illustrates aerodynamics as a propelled instrument, and, subsequently, as a glider after the propeller and bands drop off.

Still another object is to provide an aerial flight device which, when used as a multi-stage instrument, illustrates the principle of separable multi-stage missiles and missile destroyers.

Other objects and advantages of the invention will become obvious to those skilled in the art after a study of the following detailed description in connection with the accompanying drawing.

In the drawing:

FIGURE 1 is an elevation showing the invention with its lower end inserted into a launcher and supporting a Patented Apr. 14, 1964 "ice second stage at its upper end, the launcher and second stage being partially shown in dotted lines;

FIGURE 2 is a detail view to an enlarged scale, partly in section in a plane identified by line 22, FIGURE 1, and showing the kick-off lever in cocked position;

FIGURE 3 is a view similar to FIGURE 2, taken at thereto and looking from left to right;

FIGURE 4 is a sectional detail taken in a plane identified by line 44, FIGURE 2;

FIGURE 5 is a detail perspective view to about the same scale as FIGURES 2, 3 and 4, showing the construction by which the propeller ismounted for rotation in and separation from the rearward sleeve of the strut or fuselage;

FIGURE 6 is a detail view showing a modified form wherein the sleeve itself is mounted for separation from the strut; and

FIGURE 7 is a detail perspective view of the construction shown on FIGURE 6.

Referring in detail to the drawing, 1 identifies a strut or frame, shown as a length of light metal or wood, such as balsa, square in cross section and having a transversely longitudinal slot, not shown, in which a wing or vane 2 is inserted. Preferably the wing is of light, thin veneer and is removably and replaceably held in position by a frictional fit within the slot. A second or stabilizer vane 2a may be removably secured to strut 1 in a like manner.

The forward end of strut 1 is rounded to fit snugly within the rearward end 4 of a sleeve generally indicated at 3, which, as best shown upon FIGURES 2 and 3, is a onepiece turned item having an enlarged forward cylindrical end 5. This forward end has a first, relatively narrow, longitudinally extending slot 6 and, substantially diametrically opposite slot 6, a bayonet slot 7 including a relatively wide longitudinally-extending section 7a and a section 7b extending circumferentially to the left as the parts are viewed upon FIGURE 3, from the lower side edge of section 7a. Both slots open through the forward edge of the sleeve.

A kick-01f lever 8 of light wire is bent as best shown at FIGURE 2, to form an eye 8a at its right end to receive and hold one or more driving bands 9 of rubber or other resilient material. The lever has a smooth fit within slot 6 and is formed with a double bend, one of which, 8b, fits over the rearward end of this slot and another of which, 80, projects upwardly to make contact, when desired, with the rearward end of the strut of a second stage 10, as clearly shown upon FIGURE 2. The other end of lever 8, that is the left end as seen in FIGURE 2, is essentially straight and has a length sufficient to enable it to be manipulated by one finger, externally of the sleeve. The lever is thus mounted for limited universal movement about a first axis extending longitudinally of the sleeve and strut, and a second axis normal to the first axis and to the longitudinal dimension of the lever. Both axes pass through what is essentially the point of contact of bend 8b with the end of slot 6. Thus, referring to FIGURE 2, the first axis is vertical and in the plane thereof through the aforesaid point. The second axis is normal to the plane of the figure through the identified point.

Referring to FIGURE 4, it is seen that the lever may be pivoted about the aforesaid first axis, from a first position shown in solid lines, wherein its straight end is within the section 7b of slot 7, counterclockwise to a second po sition shown in dotted lines, wherein the lever is free to pivot about the aforesaid second axis, clockwise to a third or kick-off position. Movement of the lever to third position may eject a second stage 10 forwardly out of the sleeve. In this position the straight end of lever 8 projects at an angle, forwardly with respect to the longitudinal axis of the sleeve.

At its rearward end, strut 1 is rounded to fit a propeller-bearing sleeve 11 having an integral lug 12 projecting radially from one side thereof. In assembly, this lug is longitudinally aligned with slot 6 in forward sleeve 3. The lug has a longitudinal slot 13 therein, sized to receive with a smooth fit, a propeller shaft 14. As shown, the forward end of the shaft is bent to form an eye Ma, while its rearward end is bent at right angles, as at 14b, FIGURE 5, to fit within a notch 16a in the end of the hub of the propeller 15. See FIGURE 1. A pair of thrust elements 16 and 17, FIGURE 5, may comprise beads of ceramic or light metal and are mounted upon the shank or straight central part of the shaft This part has suflicient length so that when shaft 14 is mounted within slot 13 as depicted upon FIGURE 5, the beads are upon opposite sides of the lug and head 17 acts as a thrust bearing to resist twist-tension in the driving bands and to permit rotation of the propeller with a minimum of friction. When assembled as shown, propeller may rotate freely without interference from sleeve 11 or strut 1.

The parts are so constructed and arranged that when the propeller is twisted reversely to the direction required for fli ht in the forward direction, the resulting reaction of driving bands 9 upon lever 8 tends to rotate the lever to the full-line position shown upon FiGURE 4, that is, the position wherein its straight end is urged within the circumferential portion '71) of bayonet slot 7. The construction is also such that when the propeller and bands are in place as in FIGURE 1, but not twisted, there is a residual tension in the bands tending to pivot lever 3 clockwise about its aforesaid second axis. The forward edge of circumferential slot portion 712 may be slightly helical so that the residual tension mentioned effects a component reaction between the lever and forward edge, tending to pivot the lever counterclockwise as viewed upon FIGURE 4, out of slot portion 7b and into portion 7a where it is free to pivot to the kick-off position. Of course, when the driving bands are twisted for flight, the reaction of the twist therein upon lever 8 is sufficient to hold its straight end within portion 711 until substantially all of the twist energy therein has been expended in rotating the propeller. However, the bend 8b is sufficient to hold the lever against being pulled out of the sleeve by tension in the driving bands even when the lever is pivoted to the aforesaid kick-off position. This feature is important because it enables the invention to be used as a single stage propeller-glider or as a multistage instrument whose forward stage or stages are separated in flight from the first or main stage shown. Thus the present invention may be incorporated into the multistage flight devices disclosed in my aforesaid applications.

In using the device as a single-stage instrument, propeller shaft 14 is slipped into its slot 13 in lug 12 as illustrated at FIGURE 5. Lever S is inserted into the slots of the forward sleeve 3 as shown upon FIGURES 2 and 3, and there held with the finger of one hand while the propeller is twisted in the direction reverse to that required for forward flight. As soon as substantial twist in driving bands 9 has been effected, the reaction thereof on lever 3 will be sufficient to hold it within the section 7b of slot 7 so that, if desired, the lever may then be released. At FIGURE 1, I have shown in dotted lines at 18 a launcher which includes a spring 19 and which may be identical with the launcher shown at FIGURE 7 of my aforesaid Patent No. 3,084,476. If such a launcher is to be used, propeller sleeve 11 is inserted into the socket thereof so that propeller 15 is held against rotation. The device may then be launched by release of spring 19, as by a pull on a cord attached thereto in a manner described in said application. Alternatively, the device may be simply held in the hand with strut 1 aimed in the selected direction of flight, usually vertically, and the propeller manually released.

As soon as the propeller starts to spin, the instrument is thrust upwardly and when twist-tension in the driving bands has been substantially expended so that it no longer urges the end of lever 8 into section 7b of slot 7, the residual tension in the bands causes the lever to pivot about its longitudinal axis, from the position shown in solid lines upon FIGURE 4, to the dotted line position there shown. The lever then pivots about its transverse axis with great speed, so that the momentum carries it completely out of slots 6 and 7 and entirely free of the sleeve. The sudden release of residual tension in bands 9 effects a reaction between the head 16 and the outwardly and rearwardly sloping forward surface of lug 1'2, which causes shaft 14 to snap out of slot 13. Thus the entire assembly consisting of lever d, bands 9, shaft 1 3, propeller IE5, etc., drops away, leaving the winged strut to continue its flight as a glider. Since the separation of the propeller assemblage greatly reduces the drag or air resistance, the over-all flight range and altitude are increased.

FIGURES 6 and 7 show a modified form in which the propeller sleeve also is released from the strut. In this construction, strut in has its rearward end charnfered or beveled as at 29. Fropeller sleeve 21 has an integral lug 22 in which there is a longitudinal bore 23 to receive the propeller shaft with a smooth bearing fit. The sleeve also has a smooth fit on and about the cylindrical end of strut 1a. The forward portion of the sleeve is cut away as indicated at 24, along intersecting planes one of which is substantially coincident with the axis of the sleeve, normal to the radial plane of lug 22, and the other of which is normal to the axis of the sleeve.

Referring to FIGURE 6, the sleeve is held against counterclockwise pivoting and effectively resists tension in driving bands 9'. However, due to chamfer 2% the sleeve may pivot clockwise relatively to the strut about an axis normal to the plane of the figure. The operation is essentially like that previously described except that the sudden release of residual tension in the driving bands causes the sleeve to pivot clockwise as aforesaid and to drop off with the propeller assembly. This further reduces the weight and drag of the strut assembly and correspondingly improves flight characteristics.

Since, in the modification of FEGURES 6 and 7, the bands, propeller, shaft, and thrust bearngs may be the same as in FIGURES 1 through 5, these items have been identified by the same reference numerals.

Where the invention is to be used as a multi-stage device, a second or forward stage as generally identified at it), FEGURE 1, and having a Wing 26, is formed so that the rearward end of its strut 27 has a smooth sliding fit within the open forward end of sleeve 3. When in proper assembled relation the rearward end of strut 27 abuts or is contiguous to a point on bend 8c of lever 8. Thus when the lever is released from the bayonet slot 7 and pivots about its transverse axis as previously described, it acts to suddenly thrust the second stage forwardly and upwardly to continue its flight independently of the first stage comprising strut ll. This second stage may include driving bands and a propeller which is released for rotation only after separation from the first stage, as fully described in my aforesaid applications.

I have thus provided an aerial flight device which, when constructed as a toy, affords both amusement and instruction. Due to the droy-away of the propeller assembly, the flight range and altitude are materially increased with consequent added interest and attractiveness.

While I have described the form of the invention presently preferred by me, alterations, modifications and substitutions of equivalents will occur to those skilled in the art after a study of the foregoing specification. Thus the description should be taken in an illustrative rather than a limiting sense; and it is my desire and intention to reserve all modifications and variations within the scope of the subjoined claims.

What I claim and desire to secure by Letters Patent is:

1. In an aerial fi-ight device, a winged strut r laving a longitudinal flight axis, a lever mounted on the forward end of said strut, a propeller journaled on the rearward end of said strut for rotation on an axis parallel with said flight axis, resilient driving band means connected etweensaid lever and said propeller to rotate said propeller by twist therein, and means mounting said lever and propeller to said strut for release therefrom in response to substantial depletion of twist in said band means.

2. An aerial flight device corn-prising a strut having a longitudinal flight axis, and including first and second sleeve means mounted to the forward and rearward ends of said strut, respectively, a lever mounted on said first sleeve means, a propeller journaled for rotation on said second sleeve means, resilient band driving means connected between said lever and propeller, and means mounting said lever and propeller to said sleeve means for separation therefrom in response to substantial depletion of driving energy and residual tension in said driving band means in flight.

3. A flight device as in claim 2, said second sleeve means being mounted to said strut for release therefrom wtih said propeller.

4. In an aerial flight device, an elongated fuselage, a propeller, means releasably mounting said propeller for rotation at one end of said fuselage, a lever, means releasably mounting said lever at the other end of said fuselage, resilient band driving means connecting said propeller and lever and having residual tension when said driving means is untvvisted, said mounting means being constructed and arranged to separate from said fuselage in flight, by and in response to said residual tension.

5. An aerial flight device comprising, a winged frame having a longitudinal flight axis, a sleeve mounted tosaid frarne at the forward end thereof, coaxial of said axis, there being first and second diametrically-opposite, longitudinally-extending slots in said sleeve and opening through the forward edge thereof, said second slot including a oircum'ferenti-ally-disposed portion opening into the rearward end of the longitudinal portion thereof, a lever including a bend extending over the base of said first slot and mounting said lever for limited universal pivoting about said base, said lever also including a portion engaging in and slidable along said second slot, a propeller, hearing means releasably journaling said propeller at the rearward end of said frame for rotation on an axis parallel with said longitudinal axis, and resilient band driving means connected between said propeller and the end of said lever external of said sleeve and adjacent said first slot thereof.

6. An aerial flight device as in claim 5, said bearing means comprising a lug fixed with said frame and having a longitudinal open slot and a propeller shaft rotatably andremovably positioned in said slot, said propeller being mounted on said shaft for rotation as a unit therewith.

7. An aerial iliglrt device as in claim 5, said bearing means comprising a second sleeve mounted to said frame for separation therefrom in response to pivoting of said second sleeve about an axis transverse to said frame, a propeller shaft journaled in said second sleeve for rotation on a longitudinal axis, said propeller being connected with said shaft for rotation as a unit therewith, said second sleeve separating from said frame by pivoting about said transverse axis in response to sudden release of tension in said resilient band driving means.

8. In an aerial flight instrument, an elongated winged frame having a longitudinal flight axis, a first forwardlyopen sleeve fixed with the forward end of said frame and having a longitudinally extending first slot in its wall and opening through the forward edge thereof, a lever fulorurned between its ends on the rearward edge of said first slot and extending diametrically across said sleeve, a second sleeve detaohably mounted on the rearward end of said frame and having a second slot parallel with and opening radially outward of said longitudinal axis, a propeller shaft j'ournaled for rotation in said second slot, a propeller mounted on said shaft for rotation as a unit therewith, resilient driving band means connecting said shaft and one end of said lever and exerting residual tension therebetween when untwisted, and means carried by said first sleeve and releasably engaging and holding the other end of said lever, said last-named means being constructed and arranged to hold said lever against pivoting, by and in response to twist in said driving band means in the direction necessary to rotate said propeller in the flight direction, and to release said lever for detachment from said first sleeve, through said first slot, in response to said residual tension and after substantial depletion of twist in said driving band means.

References Cited in the file of this patent FOREIGN PATENTS 826,425 France Jan. 4, 1938

Claims (1)

1. IN AN AERIAL FLIGHT DEVICE, A WINGED STRUT HAVING A LONGITUDINAL FLIGHT AXIS, A LEVER MOUNTED ON THE FORWARD END OF SAID STRUT, A PROPELLER JOURNALED ON THE REARWARD END OF SAID STRUT FOR ROTATION ON AN AXIS PARALLEL WITH SAID FLIGHT AXIS, RESILIENT DRIVING BAND MEANS CONNECTED BETWEEN SAID LEVER AND SAID PROPELLER TO ROTATE SAID PROPELLER BY TWIST THEREIN, AND MEANS MOUNTING SAID LEVER AND PROPELLER TO SAID STRUT FOR RELEASE THEREFROM IN RESPONSE TO SUBSTANTIAL DEPLETION OF TWIST IN SAID BAND MEANS.

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