US3374739A - Payload recovery system - Google Patents

Description

March 26, 1968 R. 1.. RODGER PAYLOAD RECOVERY SYSTEM 2 Sheets-Shem 1 Filed March 16, 1966 o W m Tn m. V mmfim March 26, 1968 R. RODGER PAYLOAD RECOVERY SYSTEM 2 Sheets-Sheet 2 Filed March 16, 1966 INVENTOR QOBEQT L. RODS R a A a.

3,374,739 Patented Mar. 26, 1968 fiFice United States Patet 3,374,739 PAYLOAD RECOVERY SYSTEM Robert L. Rodger, Hackettstown, N.J., assignor to the United Statesof. America as represented by the Secretary of the Army Filed Mar. 16, 1966,.Ser. No. 536,587 4Cla ims. (Cl. 102-56) ABSTRACT OF THE DISCLOSURE The invention described herein may be manufactured and used by or for the Government for governmental purposes without the payment to me of any royalty thereon.

The invention relates to a projectile recovery system and more particularly to' a projectile recovery system utilizing a ballute device.

Since the advent of artillery, a nee-d to recover launched vehicles in a suitable manner has existed. The major consideration in recovering launched vehicles or projectiles has been to provide a means of recovery in a manner that allowsrelatively low deceleration loads upon impact. A

In the past, recovery was accomplished by one of three methods:

(1)"Have the vehicle launched in a parallel plane so that impact occurs in a soft medium, water or on a rocket sled.

(2) Have the vehicle, in the .case of an artillery. projectile impact base, launched from a vertical launching into a soft medium.

(3) Utilize a parachute to retard fall rate.

These aforementioned methods have proved unsatisfactory for the following reasons:

(1) Depending upon a soft impact generates too high a g level.

(2) Catching the vehicle on a rocket sled is too expensive.

3) Utilizing a parachute encompasses too many types of failure, i.e., shroud line entanglement, parachute collapsing, etc.

The novel drag device is devoid of the aforementioned deficiencies. It is attached to and launched with the vehicle. Once it is inflated, the possibility of collapsing is remote due to the utilization of only one line riser as compared to twelve or more with a parachute used as a flexible membrane.

It is therefore an object of the present invention to provide a projectile recovery system which allows relatively low deceleration loads upon impact.

Another object is the provision of a projectile recovery system which is attached to and launched with the projectile.

Still another object is to provide a projectile recovery system utilizing a ballute drag device and only one line riser.

A further object is the provision of a projectile recovery system utilizing a ballute packaged inside the projectile.

The above objects as well as others together with the benefits and advantages of the invention will be apparent upon reference to the detailed description set forth below, particularly when taken in conjunction wit-h the drawings annexed hereto:

FIG. 1 shows a partial sectional view of the present invention.

FIG. 2 illustrates an operational three stage view of the present invention.

As seen in FIG. 1, the payload recovery system 10 includes a projectile body assembly 12 and a recovery assembly 14. The recovery assembly 14 comprises a hollow cylinder 16 and a propelling yoke 18. The cylinder 16 is retained on the propelling yoke 18 by a series of pins 20.

A ballute drag device 22 is located inside of cylinder 16 and propelling yoke 18 and is attached by a single line riser 24 to a thrust bearing 25. A ballute is defined as a drag device which acts similar to both a balloon and a parachute.

A member 26 is positioned to cover a pair of adjacent bearings 28. A holder bearing 30 is positioned through the center of said bearings 28 having male screw threads 32 for securing to the female screw threads 34 of plate 36. A pair of dowel pins 38 extend from said holder hearing 30 into said plate 36 for further security. Secured to said cover member 26 by cup-point set screws 40 is a swivel plate 42. Four shear pins 44 (only two are shown) are secured to said plate 36', apart around the circumference of said plate 36. Secured inside said propelling yoke 18 on opposite sides of the bearings 28 are a pair of pistons 46, each piston having an O ring 48 located in groove 50 and a spring 52. The springs 52 are utilized to give an additional boost to said yoke 18 after initiation of said yoke 18 away from said payload. The pistons 46 are restricted during their thrust stroke by screws 51.

At the front of the propelling yoke 18 of the recovery assembly 14 is a fuze 54, which can be for example a mechanical time fuze, resistance-capacitance type, an electronic type, barometric type, etc. Located at the rear of the fuze 54 is a propellent case 56 having an initiating device 58, i.e. primer, detonation, etc., and propellent 60, therein. The activated fuze 54 releases the initiating device 58 at a predetermined time. This device 58 ignites the propellent 60.

The acceleration force activates a release mechanism (not shown) in the fuze 54. The acceleration function 15 where a=acceleration Gs P=Chamber pressure in pounds per inches 2 A|=Bore area in inches 2 W=Weight of projectile in pounds In operation, the drag device 22 is packaged as part of the projectile body 12 to be recovered. The payload recovery system 10 is launched (see FIG. 2) by a launcher 62, during the launching environment a fuzin-g mechanism 54 is activated which allows the recovery system 10 to reach a predetermined height at which time the fuzing mechanism initiates a propellent 60. The propellent 60 burns and generates gas which causes separation of the cylinder 16 which surrounds the drag device 22 by generating enough pressure to break the shear pins 44 there by allowing the springs 54 to lift the yoke 18 away from the payload. The drag device 22 which is retained to the projectile body 12 through a thrust type bearing 28 is then subject to dynamic pressure. The dynamic pressure inflates the drag device 22. The spin of the projectile (as shownrrby the arrows in FIG. 2) is segregated from the drag device 22 by the aforementioned thrusttype bearing. After the drag device 22 is inflated, the high drag force of the drag device 22 retards the projectile velocity and orientates the projectile 12 with respect to the ground causing relatively light impact of the projectile 12 with the ground. The drag force generated by the ballute drag device 22 forces the projectile 12 to assume an orientation in the direction of gravity and also restricts the free fall of the projectile 12.

The system can also be launched without a timing system. Under this condition the cylinder 16 containing the drag device 22 is separteed by the drag force.

When the drag force on the cylinder 16 is large enough to cause a diflierence in acceleration between the projectile body 12 and the cylinder 16, the cylinder 16 is forced from the body 12 through the action of springs 52 allowing the drag device 22 to be inflated with ram air.

In inflating the drag device 22, the surrounding dynamic pressure is forced into the side inlets 64. Upon inflation, the projectile body 12 begins its fall, (FIG. 2), when the single line riser is fully extended the balluate drag device allows the descent of the projectile body 12 allowing for a minimum G load landing or a mid-air pick up by an airborne vehicle.

Obviously many modifications and variations of the present invention are possible in light of the above teachings. -It is therefore to be understood, that within the scope of the appended claims, the invention may be practiced otherwise than as specifically described.

I claim:

1. A payload recovery system comprising,

a hollow cylindrical body,

-a payload attached at the rearward end of said body,

a balluatedevice located within said body,

a thrust bearing securing said ballute device to said payload and including,

a pair of adjacent barings,

a cover member attached to said bearings,

a holder bearing extending through the center of said bearings, and having male screw threads,

a plate adjacent said holder bearing, having female screw threads for receiving said male screw threads of said holder bearing, and

means attached tothe forward end of said body, for separating said body from said payload at a predetermined time after activation including, a fuse, a propellant case located at the rearward end of said .fuse, containing initiating means and a propellant therein, a pair of dowel pins extending from said holder bearing into said plate,

a plurality of shear .pins secured to said plate,

a swivel plate secured to said cover member by a plurality of cup point set screws,

a propelling yoke located inside said hollow cylindrical body,

a plurality of pins maintaining said body on said yoke,

a plurality of pistons secured inside said yoke and located on opposite sides of said bearing, and

an O ring and a spring provided adjacent and in contact with one end of said piston.

2. A system of the type described in claim 1, wherein ballute device is connected to said cover by a single line user.

3. A system of the type described in claim 2, including a plurality of air inlets located on said ballute device in such a manner as said ballute will be inflated by ram air.

4. A system of the type described in claim 3, wherein said pistons have grooves thereon,

said 0 rings being located in said grooves, and

said spring means are located at the end port-ion of each piston.

References Cited UNITED STATES PATENTS 1,309,982 7/ 1919 Darling .a 10235.6 1,624,837 4/ 1927 Holmes 308- 1,978,641 10/1934 Martin 10235.6 2,342,096 2/ 1944 Zimmerman 102-35.6 2,616,369 111/1952 Brown 102-4X 2,828,690 4/ 1-958 Freri 10235 3,038,407 6/1962 Robertson et a1. 102-35.4 X 3,168,266 2/:1965 Yost 244-138 W. KUJAWA, Assistant Examiner.

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