US2636697A - Flare plane - Google Patents

Description

"A1551 8,1953 R. L. DENNY 2,636,6557 Q FLARE PLANE Filed June 9, 1951 2 mm 1 INVENTOR.

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R. L. DENNY FLARE PLANE April 28, 1953 2 SHEETS-SHEET 2 Filed June 9, 1951 INVENTOR. Z676 D'A/W nrraex/ei a 3 arm/0Z0 Patented Apr. 28, 1953 UNITED STATES PATENT OFFICE FLARE PLANE Reginald Leigh Denny, North Hollywood, Calif;

Application June 9, 1951, Serial No. 230,756

Claims. 1

The present invention relates to an improved arrangement and technique for producing controlled illumination using flares disposed in a novel manner in radio controlled aircraft.

It is desirable, under certain conditions, to produce a controlled illuminating source located at an optimum distance from the area which is to be illuminated. Thus, in certain instances it may be desirable to illuminate effectively desired portions of a battlefield so as to observe infiltration movements of the enemy, and in naval warfare to illuminate selected portions of harbor or sea for purposes of observing enemy craft such as, for example, submarines.

Heretofore for these general purposes different techniques have been proposed, and the one commonly employed involves the idea of dropping flares from aircraft or shooting the flares from guns located on the ground. In such cases the flare is most effective when located a certain distance above the ground, but of course, due to its flight, the flare occupies its most effective position for a rather limited period of time. For that reason it has heretofore been proposed to slow up the speed of descent of the flare, as for example, by use of parachutes.

With the aforementioned prior art techniques and arrangements in mind, it is an object of the present invention to provide an improved arrangement and technique whereby the aforementioned desirable results may be obtained most effectively.

A specific object of the present invention is to provide an improved arrangement and technique which includes the use of an aircraft having flares mounted thereon, with provisions for burning the flare during its complete burning life while 'on the aircraft.

Another specific object of the present is to provide an improved arrangement of this type mentioned in the preceding paragraph associated with means for controlling the flight of the aircraft and for dispensing the different flares into burnburned flares into a burning area.

Another specific object of the present invention is to provide an improved arrangement of this character which includes a plurality of hollow wing spars within whichflares are stored and from which such flares are dispensed to an area adjacent the outer tips of the wing structure, such wing tips serving as reflectors for the burning flares.

Another specific object of the present invention is to provide an improved arrangement of this character in which a plurality of individual flares may be burned simultaneously to thereby provide a greater illumination intensity per unit weight of flare material.

The features of the present invention which are believed to be novel are set forth with particularity in the appended claims. This invention itself, both as to its organization and manner of operation, together with further objects and advantages thereof, may be best understood by reference to the following description taken in connection with the accompanying drawings in which:

Figure 1 represents a radio controlled system embodying features of the present invention;

Figure 2 is a view taken substantially in the direction indicated by the line 22 in Figure 1;

Figure 3 is a top plan view of one of the wing structures of the aircraft shown in Figure 1, with portions of the structure fragmented to disclose-internal constructional ,features, it being noted that while the left wing is shown in Figure 3, the right wing is of identical construction as shown in this Figure 3;

Figure 4 is a sectional view taken substantially on the line 4-4 of Figure 3;

Figure 5 is a sectional view taken substantially on the line 5-5 of Figure 4;

Figures 6, 7 and 8 show in enlarged form a portion of the mechanism shown in Figure 4 but in different operating positions;

Figure 9 shows one of the flares in the position it assumes while burning;

Figure 10 is a perspective view showing in modified form an unburned flare;

Figure 11 shows another form which the flare may take;

Figure 12 is af erspective view showing one of the heat insul tifig elements used to separate the flares stor e g the aircraft wing;

Figure 13 is spective view showing one of the unburned ares used in the aircraft wing shown inthe previous figures Figure 14 is a perspective view showing the gas seal puncturing element used in the arrangement shown in Figure 3;

Figure 15 is a perspective View showing the rectangular cross sectional features of the wing spars shown in Figure for storing the individual flares;

Figure 16 is a. perspective view showing the underside of the flare shown in Figure 13.

Figure 17 shows the manner in which the may be controlledlby' a solenoid H The present invention contemplates the-use of a radio controlled plane as shown in Figure l, the radio controls for the plane being essentially con ventional and forming, per se, no part oi the present invention. The radio control system includes a ground based transmittenwith l l for radiating five difierenttypesoi signals for.

reception on the antenna system I! of the. plane it. A pair of such signals is used conventionally to control up and down. movement of the plane; a second pair of. controllsignals provides so-called left and right? flight. control; while; the: fifth 1 signal heretofore conventionally"transmitted" a so-called parachute chaii'fie'l is used to control the flares whichar'el storcdinethe" Wing si natures M, i5 oftli plane. I

The wing structures. M115 are essentially. of identical construction, and for that reason a detailed description of the wing. structure it sufflces'as a. description for the" other wing structitre l5.

The wing structure (4 is diiigll'd' not only for its ndrmal' useful purpose or providing lift and control for flight of the aircraft, but is designed, in accordance with. the present invention, for storing a piurality or flares it which are burned in successionin' snaresl'fi proximity. to' th'e wing tips.

not: this purpose the. wirigl M, asisho'w'n' ures. 3 and 5', includes three hollow spasif", it,

v spars ll, it, so that the intensity" of illumination developed upon burning of the'fiar'e in the center tube'orspar i8 is' greater than" that produced by the flares w th the tubes? or spars I l, t ll.

Itwill be observed, as seen from Figures" and 136'; that each one or flares 5 includes a r-use I G A- and a-mech anica pacing; element it??? which is longerthan the fuse 1 6A so as-tu provide some protection-for the". fuse orkdetonator: l SA-ewh'em the fuses are stored in {10511316112918 shown in Figure. 3.

Preferably, the? flares l6 areeiected. innsu'ccession under the influence of high pressure'gasfrom a cor-responding one of the pressure tank-s fut, 2'2, 23 (Figure 3) upon. operation either-mechanism shown in Figure; 4, such mechanism normally serving to; maintain the string of; flares" it in stored position but upon actuation ot the solehold. 24, allowing the escape oi only one ilare, i. e., the outermost flare lb toa burning position shown in- Figure 9.

With reference tol igure, the string ofifl'ares' 4 23 is automatically made available for purposes of ejecting the flares when and as the string of flares it is originally stored in the corresponding tube or spar ll, l8, l3.

For this purpose each of the tanks 2i, and 2B is connected through suitable conduits MA, 22A, 23A to a closure member 2E3, 22B, 233, each of such closure members having a frangible surface which may be punctured by the conical This member 28* is slidable in the corresponding tube or spar ll, l8, l9 and carries an annular gasket 28 which cooperates with the internal wall of such tubes or spars to provide a pressuretight seal preventing the escape of gas. It is clear that" when a: sufficient number of flares 58 are loaded, the member 28 carrying the spike 2'1 punctures thefrangible wall in the closure member-.tl-B to automatically allow the escape of gas under pressure from the corresponding tank 2%, 22,233.;15 the case may be, such pressure acting to normally eject th'e flares outwardly;- but the mechanism; as mentioned previousiy with reference to Figure t prevents suchiej'ectment.

More specifically, with reference to Figure 4, the" dog 2E3" engages the shoulder" iiiC (Figures 4 and 16) to prevent dispensing Or eiectinent of the flare it from its normally stored. position shown in Figure 4; to its'burning position shown in" Figure 9. Upon downward movement of the plate by means described later; the' (10%"2513 is nolonger effective; however, subsequently; when the" plate moves upwardly toitsnormalpcsition theothe'r dog engages thesa'rne shoulder lBA so as to maintain such flare it in its burning position. The mechanism for actuating the plate is now describedin detail}.

As alluded to previously, the plate; 2 5 is operated in accordance with signals" transmitted over the conventional so-ca'lled parachute?" channel, such signal being continuously transmittedand the control apparatus being actuated. upon interruption ofisuchsi'gnal; Thus, thesolenoidfifl in: Figure 4 is: shown itsino'rmally energized position wherein its armature. ZilAis maintained in a retracted position. against the. actionof. the coilcompression spring Sill Upondee'nergi'zation of thes'olenoid 2 t, i. 6:, upon interruption of! the received contr'cl signaL. the actuated; parts assums in succession the positions shownin Figthese; 8 and 7. It. is observed. that the armature 2 23A is pin connected to one end. of a link Iil which has its other end pin. connected to a bell crank 32. The. bell. crank 32'. is pivoted; on the axle 33' with a free end. thereof adapted to engage" and move the pivotedlspring. biased dog 36', such dog 35 being pivotally mounted. on the horizontal'l'y'rnoving plate 3?. The dog- 36 ignormally. maintained inits. position shown in Fig ure 4 by the coil tension spring 353, having one'of its erid's' connected. to the pawl 36 and the other one or its ends connected to the plate 3L The plate 31' is normally biased to the right in Figure 4 by, the coil tension spring 40, having one of its ends attached to the stationary wing portion ll and the other one of itsiendsattached to the" plate 3?. A earn mechanism interconnects the horizontally movame plate 3': with. the Verticallynlovabl'e plat'ez'fi', so that upon horizontal movement of the plate 37' the plate 25 moves vertically. For'p'ur'po'ses of a'clii'eviiigthisresul't the plate 37 is interconnected With the plate 2.5

through pins 42, t3, and the plate. 25 is con strained to move vertically by the pins 44', 45 cooperating with the walls of the corresponding lost "motion slots 48, '41 in the plate Thus, it is clear, upon deenergization of solenoid 24, the outermost flare I6 is allowed to move to its burning position and be arrested in such burning po- 1 sition shown in Figure 9.

Preferably, after the flares are stored and before burning, the outermost open ends of such tubes or spars ll, I8, 13 are closed by frangible, burnable material for protection against weather and other elements. At the same time the solenoid 24 is actuated, i. e., deenergized, the flare igniting means (Figure 3), which is pref- 'erab1y a spark plug, is energized for purposes of producing burning of the fuse or detonator lEiA. Thus, initially the flare is lit while in the retracted position shown in Figure 4, and the re sulting burning flare in its movement outwardly to its position shown in Figure 9 causes the barrier 48 to disappear, i. e., be burned or broken Another feature of the wing structures shown herein resides in the provision of a reflector for the burning flare. This reflector, having the general reference numeral 52, comprises the wing tips and is preferably of light reflecting material which likewise is capable of withstanding high temperatures. Preferably, the wing tips 52 are stainless steel.

Also preferably, to prevent heating of the flares which remain still unburned, small layers of heat insulating material 53 (Figures 3 and 12) are disposed between adjacent flares.

While the drawings show the flares and corresponding tubes or spars of square or rectangular cross section, the flares and corresponding spars may take the general shapes as indicated by the modified flares shown in Figures 10 and 11, Figure 10 showing a cylindrical flare 56 and Figure 11 showing a relatively flat flare 51, each having a corresponding detonator 56A, 51A and corresponding spacer 56B, 57B.

While the drawings show the use of gas pres- ,sure to urge the flares outwardly and to e ect the same, it is clearly within th province of the present invention to provide other means for this purpose and, for example, springs either of the tension or compression type may be used for this purpose, i. e., of urging, moving and ejecting the flares.

Preferably, the aircraft shown in Figure 1 includes gyro stabilizers, thereby avoiding the use of ailerons. However, it is desired that the speed of the aircraft be relatively high so that it may be maneuvered into position quickly, but it is likewise desired to slow the flight of the aircraft while the flare is burning. For this purpose automatic means are provided for lowering the flaps 59 of the aircraft while the flare is burning. For that purpose a flap moving mechanism may be coupled to the solenoid armature MA as shown in Figure 17. This automatic control of the flap, however, is optional although desired. The flap actuating mechanism is such that so long as a flare assumes a burning position shown in Figure 9, the flaps remain in a lowered position. To achieve this condition a microsw1tch controlling such flap moving mechanism may be disposed for engagement with a flare in its burning position. Thus, the flap moving mechanism may cause the speed of the plane to be reduced from 90 miles per hour to a speed of, for example, 50 miles per hour.

In operation of the arrangement the flares are first loaded in the hollow spars, a sufficient number being loaded so that the frangible diaphragm of the closure member ZIB, 22B, 233, as the case may be,:.is broken to'allow the escape of gas under pressure from the corresponding tank 2|,

22, 23. Upon such loading, the plate 25 (Figure 4) is cammed downwardly but the dog 253 thereon prevents outward movement of the flares even when gas under pressure is liberated. Thus, in the-loaded condition, the flares assume the position shown in Figures 3 and 4, and the openings to such'flares or tubes may be closed by frangible burnable closure member 48. The plane is then placed in flight by conventional means and directed to an optimum distance above the area which is desired to be illuminated. When the aircraft is in the desired position the control signal transmitted from the transmitter it (Figure 1) is momentarily interrupted to cause de-energization of the solenoid 2d and energization of the spark plug 5%, to in turn cause ignition of the flare. Upon deenergization of the solenoid 24 the flare moves from its normal retracted position shown in Figure 4 to its burning position shown in Figure 9, breaking and/or burning the frangible closure member 458 in its movement. In its burning position in Figure 9 the stainless steel wing tip-52, serving as a reflector, directs a concentrated beam of light downwardly. After the flare has burned, the burning time of each flare being for example 2 minutes, the control signal from the transmitter I0 is again momentarily interrupted, causing ejectment of the expended flare and ignition and movement of the adjacent flare into burning position. In the meantime, the aircraft is flying at a reduced speed of, for example, 50 miles per hour, since at this time the flare is in burning position, causing actuation of the flap moving mechanism to in turn cause the to be lowered.

In general, the burning time of each flare is determined by the length of the flare, while the intensity of illumination, i. e., the candle power developed, is determined by the cross-sectional area of the flare. These two variables, i. e., the length and cross section, may assume different proportions and, as shown in the drawings. the flare is in the central tube i8 develops a greater amount of candle power than the flares in the outside tubes I1 and I9.

While the particular embodiments of the present invention have been shown and described, it will be obvious to those skilled in the art that changes and modifications may be made without departing from this invention in its broader asspects and, therefore, the aim in the appended claims is to cover all such changes and modifications as fall within the true spirit and scope of this invention.

I claim:

1. In an arrangement of the character described, an aircraft having a wing structure, said wing structure including a plurality of parallel extending open-ended hollow spars, the open ends of said hollow spars being adjacent and beneath the tip of said wing structure, at least one flare in each of said spars, and said tip serving as a reflector for the flare while burning.

2. In an arrangement of the character described, an aircraft having a wing structure, said wing structure including a plurality of parallel extending open-ended hollow tubes, the open ends of said hollow tubes being adjacent and beneath the tip of said wing structure, at least one flare in each of said tubes, said tip providing means which serve as a reflector for the flare while burning, means normally urging said flare outwardly toward said tip, and controllable latching acetate? means: preventing: movement: Ofzf said. flare-s by said urgingvmeans;

3;. In an arrangement of the character. de.- scribed; an. aircraft" having: a;v Wing? structure said wingi structure: including am open-ended: hollow tube, the open. endlofc saidthollow'tubte. beingadj acent and beneath the: tip; of; said wing" structure, atl'east. or-eflarefim said; tuba. andLsaid; tip. providingqmeans which: serve as: arerlect'or for" the: flare while: burning;

4. In an arrangement.- oi the: character: described, an aircraft; having a: Wing; structure, said wing structure including a: plurality of: parallel extending open-ended; hollow' spars, said wing structure: including. a. tip; of; light: reflecting; ma.- terial disposed adjacent and-above the. open. ends of saidzspars; string of. flares. in. each of." said spars means: normally urgingsaid. string. of: flares outwardly towards the: open ends; of said spars, controllable locking means: for dispensing said; flares in succession to a burning, position adjacent the open ends of said spars.

In an arrangement of. the; character die;- scribed. an; aircraft having a wing structure, said Wingstructure including a plurality of paraliel extending open-ended. hollowtubes, said. wing structure including 2;.tl p0f' light reflecting material disposed adjacent-and above the. open ends of said; tubes, a string of flares in eachv of said tubes, means-normally urging said-string of outwardly towards the.- open' ends of said: tubes, and. mean-s for dispensing said.- flares in successionto a. burning. position adjacent: the open ends. of saidtubes.

6.- In. an? arrangement of the; character described, an aircraft having a. Wing structure, said Wing structure including at least one parallel extending, open-ended. hollow tube, said Wing structure including a tip'of, light reflecting material disposed adjacent and. above the open ends otsaidtube; a, string of flares in said. tube, and

means for dispensing; saidflares in succession to a; burning. position. adjacent.- the open end. of said tube.

I. The; arrangement. in. claim.v 6: in; which: said dispensing: means: includes: radios controlled means 8.. The arrangement; in; claim; 6? in. which said aircraft includes at least. one. speed: reducin member norm-ally; maintained; in; inoperative condition, and; means; rendering Saijdc speed. re,- d'ucingmember eifective upon actuation; 0t: said dispensingmeans.

9; In an arrangement! of the character described,, a: radio controlled: aircraft. incorporatin means; for: controlling; the: flight thereof: firom'. a ground position-,, said. aircraft. having a wing structurewhich includes. at. least. 0116:013fil1r611d8d hollow. tube. extending,longitudinally ofisaidiawin structure, said wing structure; including a tip of light reflecting material, disposed: adjacent; and above the'open endorsaiditubeba stringer flares in: said tube. radio controlled; means for dis;- pensing' said: flares: in succession to a. burnin position: adjacent the open end of said; tube... and radio controlled; means for igniting said flares prior; to movement. to said. burnin position.

10);. The. arrangement set forth,- in claim 9.- in which said aircraft includes. at, least. one; speed reducing member normally" maintained in. in:- operative condition, and. means rendering said speed reducing; member eiiective: upon; actuation of; said; dispensing means;

REGINALD LEIGH DENNY;

References. Cited in. the. file. Of this patent UNITED STATES PA'IENTS Number Name Date 1,304,314 Hill May 20,1919 2,019,652 Brookleypflv Nov. 5., 1935 2,381,332 Boldt: Aug; 7, 1945 FOREIGN PATENTS Number Country Date;

328,847 Italy- Aug; 22, 1935 445,813 France Sept. 13, 1912 865,600 France Mar. 3, 1941

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