US2422662A - Glider - Google Patents

Description

- June 24, 1-947. D. s. FAHQRNEY 2,422,662

GLIDER Filed 001;. 7, 1943 lNVENTOR DEL/15E S. FAHEWEY Patented June 24, 1947 UNITED STATES PATENT OFFICE 2,422,a62 GLIDER' I Delmer S. Fahrney, United States Navy Application October '7, 1943, Serial No. 505,320

(01. 2443) (Granted under the act of March 3, 188 3, as

7 Claims.

amended April 30, 1928; 370 0. (757) lage being formed of any suitable light-weight material and of any desired configuration, the wing and control surfaces being of conventional design. The present application is a continuation in part of pending application Serial Number 407,140, filed August 16, 1941,.now matured into Patent 2,399,215.

It is an object of the present invention to provide the fuselage with compartments that house radio control equipment, television, servo-motors, batteries, relays, stabilizers, generators, auxiliary fuel tank, bomb, torpedo, flare and smoke screen material.

A still further object of the present invention is the provision of a tow cable and means for guiding the glider below the line of tow.

A still further object of the present invention is the provision of means responsive to any change in the angle of tow.

A still further object of the present invention is the provision for pilotless towing of a glider through use of stabilizers and servo mechanism to actuate the control surfaces of the glider automatically.

A still further object of the present invention is the provision of detachable means on the fuselage operable by release mechanism controlled from the towing airplane.

A still further object of the present invention is the provision of releasable means connecting the airplane and glider, also controlled from the towing airplane.

A still further object of the present invention is the provision of means controlled from the towing airplane for releasing material from some of the compartments in the fuselage of the glider.

A still further object of the present invention is the provision of means in some of the compartments of a glider responsive to directional apparatus for controlling the glider when released from a tow line.

Other objects and advantages of the present invention will be more apparent from the following description and claims.

Referring now to the accompanying drawings which are made a part hereof, and on which similar reference characters indicate similar parts throughout the several views.

Figure 1 is a side elevational view of a glider fuselage and detachable wing. The servo-motor, stabilizer, battery and bomb compartments being shown in dotted lines in the fuselage, a tow line and cables being shown fragmentarily and connected to conventionally illustrated release means-v s Figure'Z is a view similar to Figure 1, the wing being provided with adjustable diving flaps, the glider fuselage with a television or radio compartment shown in dotted lines and with a tow line and cables shown fragmentarily and connected to conventionally illustrated release means.

Figure 3 is a viewsimilar to Figure 1, the wing in the drawing being fixedly secured to'the fuselage, the fuselage provided with afuel compartment shown in dotted lines and a fuel supply conduit connected to a valve in said compartment, the tow-line, cables and fuel supply conduit beingshown fragmentarily and connected to release means shown conventionally.

Figure 4 is a View similar to Figure 3, the fuselage being providedwith a compartment and a hinged door, a bomb or torpedo in said compartment, the bomb or torpedo being shown in dotted lines, the tow line and cables being shown fragmentarily and connected to release means shown conventionally,

Figure 5 is a side elevational view of a glider fuselage, the fuselage provided with radio, television, relays, generators, servo-motors and bomb compartments shown in dotted lines,- a tow line connected to release means shown conventionally in the nose of the fuselage, afeeler and a guiding arm connected in the nose Ofthe fuselage, and means on the tow cable for holding the guiding arm, the-tow cable being shown fragmentarily and the fuselage broken.

Figure 6 is a side elevational view of a modified form of the present invention in which the gliderlssecured'to release means on the airplane, the fuselage of the glider being provided with compartmentsfor extra fuel supply shown in dotted'lines, and a fuel supply conduit connected to a valve in said compartment as shown, with means for opening the valve and meansfor releasing the conduit being shown conventionally as in Fig. 3.

Figure 7-isa plan view of atype-of hinge for connecting a plate and a wing to the fuselage and illustrating the connecting pin and solenoid.

Referring-now to the drawings, the fuselage or body 8 of the glider maybemade of any suitable light-weight material, such as metal, plastic or the like, thefuselage being formed in any desired configuration. As illustrated in the drawings, the fuselage '8 is provided with a plurality of compartments, the numeral 9 representing the electric or. hydraulic servo and stabilizer compartment, the battery compartment and H the compartment for high explosives.

In Figure l, the fuselage 8 i provided with a wing I2 that is detachably secured to the body in the following manner. On the fuselage 8 are mounted plate members l4 that are bolted or otherwise secured to the fuselage, the members being provided with spaced knuckles [5. On the wing l2 are mounted plate members l6 that are bolted or otherwise secured to the wing, the members being provided with knuckle I! that. engage the knuckles I5. The plates are detachably connected by a pin I 8 that passes through the sets of knuckles. One end of the pin I8 is connected to means releasably secured between the wing and the fuselage and adapted: to uncouple the plates and, in the. present showing I have illustrated one form of uncoupling. means in the form of a. solenoid [9 for operating the pin l8. Solenoids bein of well-known types and well known in the art, I have not shown them in detail. I would, at this point. have it distinctly understood that although I have shown a solenoid, I do not wish to limit myself to same, a other types of release means may be employed. A tow line connects the glider to an airplane (not shown), one end of the tow line being provided with a clevis 2! operatively secured to a plate support 22' that carries knuckles '23 and a solenoid t9; Secured to the fuselage 8 in any suitable manner is a plate 20 having a knuckle 25- that engages knuckles 2 3, the plates being heldin detachable engagement by pin" 'l-B, one end of the pin being connected tosolenoid 1-9: ries a plurality of electric cables 26 that connect solenoids ii!) to a source of' electrical energy in an airplane ('hot'shown).

In Figure 2 of' the drawings, the wing I 2 is shown as being fixedly secured to the body 8 and it is provided with adjustable diving flaps 2-! and 28 which can beset automatically on release of glider. In the nose of the fuselage 8 in compartment 9, is housed an electric or hydraulic servo and stabilizer, in compartment Iii batteries, and in compartment 30 television or radio equipment, all of the equipment being well known in the art, it is not shown in detail. The fuselage is provided with the tow line release mechanism illustrated inF-igure 1. I

Figure-3, in the nose of the fuselage 8 in compartment 9 is an electric orhydraulic servo and stabilizer and in compartment W- a battery; Within the fuselage 8 is 2: incl compartment 3| having an outlet valve 32 equipped with a coupling nipple 33 that engages the end of a fuel hose 34, the fuel hose being carried by the tow line. 20a The fuselage 8 carrie a plate 35 that may be detachably secured to the fuselage, the plate carrying a pair of solenoids 36 and 31'. Connected to the solenoids 3'6 and 31* are electric cables 26 that are carried by the tow line 20'. Pin- 38 of solenoid 38 engages the valve 32 while pin 39 of solenoid 3! engages the coupling nipple 33. The towline release mechanisrn" is the same as illustrated in Figure 1.

In Figure 4 of the drawings, the compartment M7 is adapted to house a bomb or, as illustrated, torpedo M shown in dotted lines. The compartmen-t m is provided with a trap door 42 that is provided with a catch lug 43. The plate support 22" in this view is somewhat longer and allows for the mounting of an additional solenoidhaving an engaging pin 45. The pin engages the catch lug 43- and holds the trap door The tow line 29 car- 42 in locked position. Although I have shown in Figure 4 an aerial torpedo 4| in compartment 40, I would have it distinctly understood that this compartment may be utilized for housing flare or smoke screen material- In Figure 5, I have shown the solenoid I!) mounted in the nose of the: fuselage 8-. The tow line 20 is provided with a ring Bil fora purpose to be later described. This tow line is connected by means of a clevis or other link means 2! to a contact means held by a pin actuated by the solenoid it in a manner similar to the connections previously defined. Within the fuselage 8 there is provided an electrical relay box 6! and mount-- ed in the box 8! in any suitable manner for movement and contact therein is one end 62 of a feelcr arm 63, the opposite end portion 64 being held in engagement with a ring 68. The electrical relay box Si is connected by suitable electric conduits to the compartment 9 that houses a stabilizer mechanism and gyros. the glider is towed the relay in the box at is set to operate the stabilizer mechanism to move the: glider control sur faces in response toany deviation in the angle of the feeler arm 6'3 from that for which it. is set, to bring the glider back into a relative position with respect to the airplane to return the feeler arm again to its normal angular position. The solenoid t9, the stabilizers and gyros are con-- nected to the radio compartment 25' by suitable conduits (not shown) so that when the glider is released by operation of the solenoid til it simultancously turns on gyro stabilization and radio, television and other equipment as may be desired. Electrical energy for operating the var ious devices may be supplied by a iamdriven generator or a gasoline-engine generator housed in compartment 35. Within the fuselage 8: are mounted small electric motors to that are connected to compartment 5% by suitable electrical conduits (not shown). Television or-target. seekin-g mechanism is housed in compartment 3c and it is connected by suitable conduits: 'not shown) to the radio compartment 2% The battery to serves to supply current to some of the devices through conduits (not shown) that connect the battery with some of the compartments.

In Figure 6, I have illustrateda modified form ofmylnven-tion in which the glideris cl'etachab-Iy mounted on an airplane. The fuselage is pro vided with a plurality of compartments previous 1 described and, therefore, no further descripti-on is deemed necessary. Tothe wings t2" are secured struts 45 having a knuckle E1 that engages knuckles Q8. Mounted on the fuselage 59 is a solenoid 50 having apin '5! that engages the knuckles 4'? and 48. On the vertical stabilizer 52 there is mounted a plate 53 that is provided with knuckles so that are engaged by knuckle 55 carried by the fuselage 8. The plate 53 also carries a solenoid 5'6 having a pin 51 that engages the knuckles 55 and 5-5. An electric conduit 53 connects the solenoids with a source of electrical energy within the fuselage E9 A fuel tank (ii is connected, by means. similar to those shown in Fig, 3, to the fuel reservoirs in the airplaneiuselag-e at for refuell-ingthem from tank 3 9.

In the use of the glider illustrated Figure l, the glider is towed to a target at which point the pilot of the airplane towing the glider presses a button or switch making contact with a source of electrical energy, the electrical energ passing through the conduits 2 5 to the solenoids It, thus energizing the solenoids, withdrawing the pins from the knuckles, thus releasing the wing, the

tow line and the electrical cables. Upon release of the wing, electrical cables and tow line, the

fuselage carrying the bomb falls free onto the "towing airplane the tow cable and electrical cables are released from the fuselage. The equipment 30 (television or radio detectors) directs the released glider bomb to its objective, the radio, servo-motors, stabilizers and television being supplied with current from the battery source. The control pilot in the tow plane through the radio equipment actuating appropriate relays, actuates servo mechanism in the glider bomber directing it towardthe target as indicated by radio or television equipment until the glider bomber strikes its objective.

In the use of the glider illustrated in Figure 3, the glider serves as an auxiliary fuel tank. The fuel is released from the tank 3| by the energization of the solenoid 3B withdrawing the pin 38, the gasoline passing from the tank or compartment 3| through the fuel hose 34 to the fuel tank in the towing airplane. When the compartment 34 is empty the glider can be released or towed back to base station. To release, the pilot presses a switch connecting the source of electrical energy with the solenoids l9 and 31 thus releasing from the glider the tow line 20, the electric conduits 26 and the fuel hose 34, the glider will glide to a landing on field or water through the medium of the operation of glider controls by servo mechanism and stabilizers.

In the use of the glider illustrated in Figure 4, the compartment 40 being loaded with a bomb or torpedo, the glider towed to an objective at which point the pilot of the towing airplane throws a switch, the electric current passing through the cable .26 energizes the solenoid withdrawing the pin from the trap door catch lug 43, the door opening and releasing the bomb or torpedo simultaneously with the energization of solenoid 44. The glider can then be returned to base and released by energization of solenoid IS. The glider is freed from the tow line 20 and the electric cables 26 and glides to a landing through actuation of control surfaces by servo and stabilizers energized by a battery.

In the use of the glider illustrated in Figure 5, the automatic tow operates in the following manner. The glider is towed below the towing airplane, the feeler arm is held in engagement with, and at an angle to the tow line by ring 60. During the towing of the glider any change in the angle of tow of the glider, either to the right, left, up or down is immediately transferred to the relay El that transfers the change to the small motors 66, that changes the follow-up ratio on the gyro-stabilizers, the stabilizers causing the glider to assume proper tow position. Electrical energy is supplied by the wind-driven generator or gasoline-motor generator 65. The solenoid l9 and the gyro-stabilizers being connected to the radio compartment, radio control directed signals will release the tow line, the glider being stabilized for level flight. At this point the television or target seeking device is automatically turned on and the glider will then react to radio signals or answer automatically, directions given by the target seeking apparatus.

The modification 0f myinvention illustrated in Figure 6, the glider being detachably secured to the airplane is carried to thedesired objective at which point energization of the solenoids 50 and '56, the pins 5| and 51 are withdrawn from the knuckles, releasing the glider. This glider is primarily designed to carry additional fuel in its fuselage to increase materially the range of the airplane supporting it, the gliders wing being of ample proportions to lift the additional weight.

Other modifications and changes in the proportions and arrangement of the parts constituting the invention may be made by those skilled in the art Without departing from the nature and scop of the invention, as defined in the appended claims.

The invention described herein may be manufactured and/or used by or for the Government of the United States of America for governmental purposes without the payment of any royalties therein or therefor.

What I claim is:

1. In combination wtih an airplane a glider having a fuselage and wing, release means connecting said wing to said fuselage, a tow line connecting said fuselage to said airplane, one end of said tow line having release engaging means, release means carried by said fuselage and adapted to receive said tow line release engaging means, means carried by said tow line connecting said release means for said wing and tow line release engaging means with means in said airplane, and means in said glider for directing said glider after release of said wing and tow line.

2. In combination with an airplane a glider, means connecting said glider to said airplane, contact means carried by said glider in contact with said connecting means, means carried by said connecting means for holding said contact means in contact with said connecting means, and means on said connecting means responsive to remote control signals for releasing said connecting means and automatically stabilizing said glider for level flight.

3. In combination with an airplane a glider, means connecting said glider to said airplane, contact means carried by said glider in contact with said connecting means, means carried by said connecting means for holding said contact means in contact with said connecting means, means in said glider responsive to any angular change of said connecting means with respect to said glider, surface control means in said glider for correcting said angular change of said connecting means operated by said responsive means, and means in said glider responsive to remote control signals for releasing said connecting means.

4. In combination with an airplane a glider, means connecting said glider to said airplane, contact means carried by said glider in contact with said connecting means, means carried by said connecting means for holding said contact means in contact with said connecting means, means in said glider responsive to any angular change of said connecting means with respect to said glider, surface control means in said glider for maneuvering the glider back to a position to correct said angular change of said connecting means operated by said responsive means, and means in said glider responsive to remote control signals for releasing said connecting means and automatically stabilizing said glider for level flight.

5. In combination with an airplane a glider,

nneans connecting :said :glider -to said =-airplane, "Contact imeans'fearried*bydsaidZglider in contact with said connecting 'means, :means ca-rried by "said connecting means -'for holding :said contact smean's in "contact -[Wit-h Said connecting :IDGEKIS, -1neans in s-aid -"g'lider responsive to any angula'r achange of said connecting means with respect to *saidglider,surface eontrol means in .said glider fonfiorrecting said angular change-of saidconnectingmeansoperatedby said responsive means.

means in is'aid glider responsive to remote control signals "for "releasing @SfiidflCOIlIlBCblIlE means and automatically stabilizing :said .glider for level flight,-and directional object "seeking means re- =sponsive to said =remote control :me'a-ns.

6. In combination with an aircraft, a glider, a connection from said aircraft ireleasably attached =to :said glider, automatic flight control means in said glider for operation when said ;-:glicler is detached, said connection including -a releasable coupling to said glider, means on said connection operated by control meansin said-air- :craft for releasing said coupling and connection 'from said glider and -f or simultaneously turning on :said automatic :flight control means in said gllder.

-7. Incombination-with an aircraft, *awglider, --a connection:from saidaircraft:releasably attached to said. :glider, automatic flight control mean-s v in :said glider =for operation when :said glider is detached, :said connection inclnding a releasable coupling to saidlgliderfmeans on said connection operated by "control'means in aircraft for releasing said coupling and connection from --said glider and for simultaneously turning on said automatic flight controlmeans in saidg1ider,= operating'devices carried bysa-id-glider having centrolineans for-their operation,-andadditional releasalolemeans .forming apartof said coupling for operating :said :control means, additional means in said aircraft for controlling-'said-operating means in said coupling.

-DELM-ER' S. REFERENCES CITED The following references are of :record in the file of this patent:

UNITED STATES PATENTS Number Name Date 15207;492 Buck Dec. 5, E1916 1,779,855 =R0'che Oct. 28, L930 1-,418Q7'33 Fokker 0 June 6, i192 13690578 Hammond Nov. :6, 1928 "1281 81798 Hammond "Aug; "1 1, 11931 FOREIGN PATENTS Number Country Date 7981-80 :France Mar. '2, 19-36 739,730 France -Nov. -3, 1932

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