US1192480A - Aeronautical safety device. - Google Patents

Description

s L VAN METER, Jn AERONAUTICM. SAFETY DEVICE. APPLICATION men gums. ma.

Patented July 25, 1916.

5 SNEETSSHEET l ammo S. L. VAN METER, In.

AERONAUTICAL SAFETY DEVICE. APPLICATION FILED AUG. 8. I913.

1 1 92,480. Patented July 25, 1916.

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idzfm. 3% 4 V s. L. VAN METER, 1B. AERONAUTICAI. SAFETY D EVICE. APPLICATION FILED Mil-1.8. l9l3. 1 1 92,480, Patented July 25, 1916.

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S. L. VAN METER, Jn. AERONAUTICAI. SAFETY owes.-

APPUCATl-ON FILED AUG. 3. IQI3. 1 1 92,480. Patented July 25, 1916.

5 SHEETS-SHEET 4.

S. L. VAN METER, In. AERONAUTICAL SAFETY DEVICE.

APPLICATION min nus, m3.

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AERONAUTIQAL SAFETY DEVICE.

Specification of Letters Patent.

Patented July 25, 1916.

Application filed August 8, 1918. Serial No. 788,729.

To all whom it may concern:

Be it known that I SOLOMON L. VAN METER, Jr., a citizen 0% the United States, residing at Lexington, Fayette county, and State of Kentucky, have invented and discovered certain new and useful Improvements in Aeronautical Safety Devices, of which the following is a specification.

My invention relates to parachute attachments for aeroplanes and its objects are to provide means which shall cally cast into the to the body of the aviator on the release of the actuating mechanism, to provide effective power means for eil'ecting the above action, to provide means for insuring the prompt opening of the parachute when thus thrown into the air, to provide means for lessening the shock imparted to the body of the aviator when the parachute has caught the air, to provide means for inclosing parachute when it is mounted upon the aeroplane in connection with means for holding such inclosing means in closed position and for immediately releasing the same when the discharged from the aeroplane, to provide means for holding the operator in his seat and means for guarding the aviator against contact with the aeroplane as e is separated therefrom by the separation of the parachute and the aeroplane and generally to improve the construction of a device of this clams With these ends in view, my invention is embodied in preferable form in the device hereinafter described and illustrated in the accompanying drawin In these drawings, in elevation of an acre lane showing my device applied thereto; F1g.,2 is a section on line 22 of Fig. 1; Fig. 3 is a section on line 3-3 of Fig. 1; Fig. 4 is a to plan view; Fig. 5 is a section, partly bro en away on line 5-5 of Fig. 6; Fig. 6 is a central section through the inclosing hood for the parachute; Fig. 7 is a detail of the inclosing hood; Fig. 8 is a detail section of the parachute expanding spring; plan view of part of the releasing means for the Fig. 10 is a rear view in elevation of the back of the seat and rope attaching member; Fig. 11 is an edge view of the part shown in Fig. 10; Fig. 12 is a perspective view of the attaching back plate and harness; Flg. 13 is a detail section on line 1313 of Fig. 10; Fig. .4. is a side view showing the parachutein act to automatiair a parachute attached the Flgure 1 is a side view perspective of part pult, 'is' adapted power mechanism;

active position; Fi .15, a front view in elememben for the aviator;

vation of the guar Fig. 16 is a detail of the frame and is a side view in e vertical section of a part ower mechanism; Fig. 17 evation, partly in section, of the upper rear end of the power mechanism; F1 18 is a detail view of the lower part of t e power mechanism; Fig. 191s a side view in elevation, showing the device just after the arachute has been cast oil from the aerop ane; Fig. 20 is a detail top plan view of part of the parachute expanding spring, after the expanded; Fig. 21 is a on line 21 -21 of Fig; plan of part of the aviator; Fig. 23 is a 23 23 of Fig. 22; Fig. 24 is a detail section on line 24 -24.- of Fig. 22; Fig. 25 is a side elevation, partly in section of a modified form of the power means illustrated in Fig. 1; Fig. 26 is a horizontal detail section on line 26-26 of Fig. 25; Fig. 27 a side view in elevation of another modi ed form of power means for casting the lparachute; Fig. 28 is an enlarged view part y in section of the device shown in Fig. 27; Fig. 29 is an enlarged detail view of the lower part of Fig.28 and Fig. 30 is a detail cross section on line 3030 of Fig. 28.

Referring to the drawings, 1 is an aeroplane which is here shown as of the bi-plane type, although it is obvious that the invention may be applied to aeroplanes of other types. Fixed on the rearwardly extendin frame 2 of the aeroplane is a framewor body 3 and pivotally supported on the central crossbar of tral bar of a substantially rectangular casting member 4 to the rear bar of which are secured several vertical ower-exerting springs 6, the lower ends 0 which are severtical detail section 20.; Fig. 22 is a detail ack of the seat of the cured to the rear crossarm' of the frame 3,

as shown in Fig. 2. The front cross arm edevice illustrated in Figs of the form of t 1 to 24 inclusive may .be denominated a catato bear against the underside of a parachute carrierconsisting preferabl of a hickory-bar 8. The rear end of this ar passes under the rear cross bar 5 of the catapult, whereby when the catapult is released, its sprin s 6 will cast the parachute carrielg upwar ly into the air. The extreme forward end of member Sis connected by means of a rope '9 or other flexible consame has been fullydetail section on line this frame work is the con-- necting member to the catch lever 10 which is pivoted at 11 on the frame 3. .The'front the carrier is released and the catapult is permitted to cast the same.

Pivotally mounted on the carrier 8 is a bracket 14 (see Fig. 6) which may be adjusted vertically by means of a set screw 15, extending through a carrier member. Resting on this bracket is a parachute inclosing hood which is preferably of metal and which comprises an upper solid domesha ed portion 16 perforated with air hole's an' a lower cylindrical portion consisting of slats 17 which by means of hinges 18 connecting them to the dome are adapted to swing outwardly to permit the free escape of the parachute therefrom. The object of the adjustable bracket is to permit the hood to be set out at an inclined angle to the carrier so that when the latter is discharged the hood will be thrown rearwardly or forwardly as desired whichever serves to more effectually clear the aeroplane. To hold the slats of the hood in position, the lower ends thereof are set within a flange 19 of an annular plate 20 and hooked levers 21 are adapted to enter perforations in this flange and in opposite slats for the purpose of hold ing the hood and the plate 20 locked together. These levers are pivoted on lugs 22 projecting from the under side of the plate 20. adapted to be held normally apart so as to keep. the u per ends in engagement with the hub and ange bridge piece 23, to said arms serves to draw the lower ends together and thus releases the upper ends from the flange and hood when the bridge 23 has been withdrawn from its engagement with the arms. A releasin cord 25 is connected to the bridge mem er and extends over a pulley 26 which is mounted on the parachute carrier 8. The cord extends down through an aperture in this carrier and is fixed at its lower end to a Suitable eye on the frame 3. When the carrier is thrown upwardly by the cata ult a tension will be exerted on this cor 25 which will pull the spacing bridge 23 away from engageby means ofa releasable ment with the arms of the hooked members thus permitting the release of the members from the hood.

Theplate 20 is perforated to permit the entrance of air thereto. This plate in con- 10 will be permitted to fly I The lower arms of the levers are while a spring 24 connected I (See Figs. 6 and 8).

pending the spring readily,

junction with the expanding hood constitutes the inclosing means for the parachute 27 which in Fig. 6 is shown as inclosed in the hood, the connecting ropes thereof being shown as atthe bottom 0 the hood and resting on the plate 20.

Adapted to be releasably attached to the parachute at its throat is a parachute expanding member consisting of an annular sprin or series of fiat springs laid together and esignated by the reference character 28. (See Figs. 5, 6, 8, 20and 21.) This spring member in expanded form is illus trated in Figs. 20 and 21. At intervals around the circumference are spring clips 29 which are adapted to loosely engage the circumferential cord 30 attached to the parachute 27 at approximately the throat of the parachute. This expanding spring is of less diameter than the parachute and is adapted to expand the throat of the parachute outwardly and upon the further distention of the parachute, owing to its catching the air, the cord and released from the spring clips, thus disengaging the parachute from the expanding spring.

The sprin member 28 is adapted to be confined wit in the inclosing hood with the slats of suchhood exerting a tension upon thespring so that upon the release of the slats the spring will be permitted to expand circumferentially. To this end this spring is bent into the form of loops as shown in 5 and the inner ends of these loops are adapted to be inserted within and held by the walls of an annular groove 31 (see Figs. 5, 6 and 8), formed in a ring 32 which is adapted to lie loosely within the hood, being held therein by the pressure of the springs. The outer ends of the loops thus formed are adapted to be bent outwardly and held in such upright bent position by the pressure of the slats 17 of the hood when these slats are'docked in closed position. When the slats are released these loops will first spring downwardly from an upright positin to a horizontal position and then the expanding force of the spring will uncoil the loops exuntil it assumes the form shown in Figs. 20 and 19. The grooved ring 32 is preferably provided with a central mesh body 33. The connecting cords 34 of the parachute 27 are attached at their lower ends to a supporting rope 35. This rope is attached to the aviator through a shoe absorbing member which comirises a back plate 36 adapted to bear again and support the back of the aviator and provided with a suitable attaching harness 37. The rope 35 is adapted to enter and lie in a convolute groove formed on a plate by ridges 38 in a suitable body with- 39 see 13. The rope-is ada ted to be held in $556 grooves by means of frangible he supporting the belt which passes through the plate,

Fig. 11, or other connecting means 42 on the l this end the seat right a projection 45 extending into line with a pin 45' on the seat. A spring 47 tends to throw the rod 46 to the right, looking Fig. 10, so as to release said rod 46 whereby the back plate is steadied and held in upright position. A pivoted trigger 50 is mounted on the back of the plate 36 and the supporting rope 35 is adapted to be detachably or breakably tied to this trigger piece of twine 51. The trigger engages a notch in the rod 46 and thereby serves to hold the rod from disengagement with the ears on the seat against the pressure of the spring 47. 11 car 46' on the rod braces the trigger. When the parachute has been discharged and the supporting rope 35 is tautened, it will lift the and supporting rope 48.

To guide the aviator as he is separated from the aeroplane and to prevent him from coming in contact with the frame of the machine, a backwardly inclined wire guard frame 52 is provided (See Fig. 15 and Fig. 4). This guard frame is mounted buhind the seat of the aviator and slants u wardly and rearwardly so that should h e be. drawn backwardly from the aeroplane, he will be guarded against commg in com tact with the frame work of the machine to his rear.

In order to adjust the tension of the springs 6 which are adapted to throw the e rear cross rod of the frame 6 is made rotatably adjustable in its sockets of the springs are fastened to ropes which are coiled around the same. Both ends of this cross rod may be provided with ratchets 53, adapted to be engaged by The'operation of the device above described is as follows :-Upon the destruction force of the springs 6- will pull down the rear end of the catapult 4, forcibly throwing up the front end and thus casting the parachute carrier upwardly and rearwardly, y the carrier on the rope 25 will release the bridge permitting the spring 24 to raw the outer ends of the hooks 21 toward one another, thereby disconnecting the plate 20 from the hood, (1 unlocking the hood.

he hood rests loosely on the bracket 14 and w en the carrier is thrown into the air, will also be thrown from the bracket and carrier by the propulsive force of the carrier. The plate 20 is connected only to the hood and this connection is solely through the hooks 21, hence when the carrier is cast into the air, the plate 20 will The hinged slats of the hood when thus released from the plat 20 are forced outwardly by the downward movement of the loops of the spring member 28, thus opening the hood and facilitating its separation from the parachute inclosed thereby. The separation of the quicke spring.

of the parachute from the t e discharge aeroplane 18 shown 1n Fig. 19 in which it will appear that the expanding spring, the hood and the supporting ring are all immediately se arated from t e parachute upon the di arge of these parts from the aeroplane. As the supporting rope becomes taut, owing to the filling with air, it will release or raise the tri ger 50, permitting the separation of the ack from the seat in the manner heretofore described and the supporting rope will then gradually break the shock absorbingfwines 40 until the rope has unwound and rought up against its fastening means 42, Whereupon the aviator will be suspended as shown in Fig. 14.

In Fig. 25 is shown the modification of the means of casting the parachute into the air. In this form of the device a frame 57 mounted on the aeroplane is provided and a movable frame or catapult member 58 is mounted on this fixed frame with .its rear end pivoted thereon and its front end movable. -The front rod of this front frame extends under the parachute carrier member 59. The rear end'of the member 59 extends under the rear end of the frame 57. The front arm of the movable frame 58 bears upon the upper end of a piston rod 60 carried by a piston 61 movable in a cylinder 62. This cylinder is connected by means of a pipe 63 to a vessel 64 adapted to contain compressed air or other gas under pressure. A cock 65. controls this pipe 63 and a releasing rope 66 is connected to this cock and a apted to open the same to permit the rush of the as under pressure to the cylinder. By this construction it will be seen that by the admission of a charge of gas under pressure to the cylinder that the iston thereof will be forced upwardly t us forcibly driving upward the front end of the frame 58 and thereby casting the parachute carrier 59 and the parachute upwardly and rearwardly.

In Figs. 27 to 30 inclusive, there is shown another modified form-of the power means for casting the parachute. In this arrangement an expanding hood 67 of substantially the same construction as that shown in the device first described is employed and the parachute is contained therein. The bottom plate 68 with which this hood engages and which corresponds to plate 20 of the device of Fig. 1 is fixed to a piston member 69, consisting of a long solid cylinder which fits within a hollow cylinder 70 and is adalpted to rest upon or near a charge of pow er or other explosive 71, in the bottom of the cylinder 70. A primer 72 is adapted to fire this charge of explosive and this primer is ignited by a percussion hammer 3 which is controlled by a trigger 74, connected to a pull cord 75 the aviator. In this arrangement when the aviator pulls the cord 75 the explosive charge of the parachute within convenient reach of.

within the cylinder 70 will be tiploded, thus discharging the iston cylinder 69 and the hood carried there y.

Having thus described my invention what I claim is 2-- 1. In an aeronautical safety device, in

combination with a parachute and an inclosing member therefor to confine the parachute and hold it' folded, releasable means to lock the inclosing means, a supporting member for the inclosing means detachably mounted on the aeroplane and power means operable to exert force upon the supporting member for casting the same from the aeroplane upon actuation thereof, substantially as described. y

2. In an aeronautical safety device, in combination with a parachute, inclosing means therefor, carrying means for said inclosing means, a lever for casting said carrying means from the aeroplane, said lever supporting said carrying means at one end thereof away from the aeroplane, power means attached to and adapted to operate said lever and means controlled by the aviator for releasin said power means, substantially as descri ed.

3. In an aeronautical safety device, in combination with a parachute, an inclosing hood therefor having a continuous portion at one end thereof adapted to receive the upper end of the parachute,said hood having outwardly and circumferentially expanding portions at the other end thereof operable to suddenly release the parachute, spring means bearing against the free extremities of said portions to positively expand the same, means for holding said portions closed and means for releasin holding means, substantially as descri ed.

4. In an aeronautical safety device, in combination with a. parachute an inclosing hood therefor comprisin a body portion forming one end of the 00d and pivoted slats forming the side of the hood, means to hold said slats closed and means to release said holding means, substantially as described. V 5. In an aeronautical safety device, in combination with a parachute, a parachute expanding spring, means to confine said parachute and sprin within a limited space, means to release said confining means and automatically detachable connections between said parachute and expanding spring, substantially as described. Y

6. In an aeronautical safety device, in combination with a parachute, an expanding spring of less diameter than the parachute clips .on said spring adapted to detachably engage the lower border of said parachute, means within which said parasaid chute and spring are confined, said means means to release said confining means, substantially as described.

an aeronautical safety device,,in combination with a parachute, a slatted hood for containing said parachute, means engaging the ends of said slats, hooked arms operable to hold said slats and means together, means to exert pressure on said arms to hold them in operative position and means to release them from the slats, substantially as described. 7

8. In an aeronautical safety device, in combination with a parachute,su porting means for said parachute mounte on the aeroplane, means for automatically casting said parachute from the aeroplane and a guard member placed to the rear of the aviator to guard him in his separation from the aeroplane, substantially as described.

9. In an aeronautical safety device, in

combination with a Earachute, a seathand a attac ed to member for releasing said back from-tho seat as the connecting member becomes taut when the parachute is cast free from the aeroplane.

In witness whereof, my hand and seal at Lexington, Fayette county, Kentucky, June, A. D; nineteen hundred and thirteen.

80L0ll0R nan VAN mama Ja. [a a3 Witnesses:

3o I have hereunto set-

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