Controlled release device for use in launching rockets or missile

Burcham, T. W.

English

NASA Technical Reports Server

REFLY TO 
ATTM OF: Gp 
NATIONAL AERONAUTICS A N D  SPACE ADMINISTRATION 
WASHINGTON. D.C. 20546 
TO t USI/Scientific 6r Technical Information Division 
Attention: Miss Winnie M, Morgan 
GP/Office of Assistant General 
Counsel for Patent Matters 
SUBJECT: Announcement of NASA-Owned 
U,S, Patents in STAR 
~n accordance with the procedures contained in the Code GP 
to Code U S 1  memorandum on this subject, dated June 8, 1970, 
the attached NASA-owned U . S .  patent is being forwarded for 
abstracting and announcement in NASA STAR, 
The following information is provided: 
U,S. Patent NO, 
Corporate Source 
Supplementary 
Corporate Source 
NASA Patent Case No,: S-83338 
Enclosure: 
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Tiled April  29, 1966 
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T. W. BURCHA 
CONTROLLED RELEASE DEVICE 
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ec. 10, 196$ T. W. BURCHAM 
CONTROLLED RELEASE DEVICE 
Tile5 Apri? 29, 1966 
32 
2 Sheets-Sheet 2 
-54 
INVENTOR 
ate 
3,415,156 
as represented by the Ad- 
21 A e r ~ n 2 ~ ~ ~ s  and Space 
2 Claims. (ea. 89-1.806) 
~~ 
A controlled release device for use in launching rockets 
or missiles that utilizes the expedient of absorbing energy 
by deforming a ductile elongated pin as it moves through 
a die. 
The invention described herein was made by an em- 
ployee of the United States Government and may be man- 
ufactured and used by or for the Government for govern- 
mental purposcs without the payment of any royalties 
thereon or therefor. 
This invention relates to a controlled motion retarding 
device, and more particularly to a controlled release de- 
vice for use in launching rockets or missiles. 
Heretofore, in the launching of missiles, especially those 
of large size, normally before the missile is released from 
the launch pad, the engines of the missile develops a pre- 
determined amount of thrust. After the engines develop 
the desired amount of thrust, a hold down arm carried on 
the launch pad releases the missile. A sudden jar is im- 
parted to the missile when the hold down mechanism is re- 
leased due to the large thrust build-up. Such an instan- 
taneous release causes dynamic stresses to be imparted to 
the missile which could damage the missile. Instantaneous 
release could also damage the very delicate instruments 
carried by the missile for recording various parameters 
during the flight operation. 
It is desired that there be a gradual controlled release 
of the missile for the first few inches of travel of the mis- 
sile from the launch pad. Various apparatus have been 
analyzed for controlling the release of the missile, but due 
to the tremendous amount of thrust developed by large 
missiles they have not proven satisfactory. For example, 
hydraulic systems have been considered, but due to the 
size of a system, the plumbing and controls for such a 
system, and other parameters, they have not been adopted. 
It is desirable that a reliable, rugged and simple control 
release device be utilized which is capable of counteract- 
ing a predetermined amount of thrust developed by the en- 
gines permitting the missile to gradually lift off the launch 
pad. 
In accordance with the present invention, it has been 
found that the foregoing difficulties encountered in releas- 
ing a missile may be overcome by providing a novel con- 
trolled release mechanism for missiles. This controlled re- 
lease device consists of the following basic parts: (1) a 
die, ( 2 )  an elongated deformable element engaging the 
die for exerting resistance to relative movement therebe- 
tween resulting in progressive deformation of the element, 
(3)  the die and the element having connection between the 
missile and a launching pad for offering support for the 
missile and (4) the connection being such that as the mis- 
sile is initially separated from the support during launch- 
ing, the element is deformed by the die offering progres- 
sive controlled release of the vehicle. 
The subject invention contemplates a novel expedient 
of absorbing energy through deforming materials by the 
relative movement between a deformable element and a 
die. Previously, metal drawing has been on a relatively 
small scale wherein energy is exerted for the purpose of 
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deforming the metal into a different shape. The present in- 
vention utilizes drawing to produce energy for checking 
the movement of a vehicle. 
Accordingly, it is an object of the present invention to 
utilize the expedient of drawing metal to contro! the move- 
ment of a vehicle during a predetermined distance of 
travel. 
Another important object of the present invention is to 
control the release of a missile from a launching pad. 
Still another important object of the present invention 
is to provide a device which minimizes the dynamic 
stresses imparted to a missile during the initial release of 
a missile from a launching pad. 
A further important object of the present invention is 
to provide a device which controls the acceleration of a 
missile during launching. 
Still another object of the present invention is to pro- 
vide a device which is simple and economical which checks 
the movement of a vehicle. 
Another object of the present invention is to provide a 
device which checks the movement of a vehicle having a 
spindle that includes a conical section which is forced 
through a die exerting resistance to relative movement 
therebetween during deformation of said spindle. 
A particular advantage of using the device constructed 
in accordance with the invention is that the rate of move- 
ment of the vehicle to which it is attached is easily con- 
trolled by simple variations in the size of the pin or die 
utilized. Also, the device is simple to  manufacture and at- 
tach to a vehicle and is reliable and effective in its opera- 
tion. 
Other objects and advantages of this invention will be- 
come more apparent from a reading of the following de- 
tailed description and appended claims taken in conjunc- 
tion with the accompanying drawings wherein: 
FIGURE 1 is a schematic view of a space vehicle in 
launching position with a Gontrolled release device con- 
structed in accordance with the present invention illus- 
trated; 
FIGURE 2 is an enlarged front elevational view of the 
controlled release device iIlustrated in FIGURE I; 
FIGURE 3 is a n  enlarged side elevational view of the 
controlled release device constructed in accordance with 
the present invention; and 
FIGURE 4 is an enlarged cross-sectional elevational 
view taken on line 4-4 of FIGURE 3. 
Referring now in more detail to the drawing wherein 
like reference numerals designate identical or correspond- 
ing parts throughout the several views and with special 
attention to FIGURE 1, reference numeral 10 generally 
designates a space vehicle, shown as a multistage rocket, 
erected in a launch position. The multistage rocket 10, 
which is illustrated schematically, consists of an upper 
stage 12 and a lower booster stage 141. which separates 
from the upper stage at a predetermined point in the 
flight of the rocket. A space vehicle 16 is carried on the 
upper stage 1% and separates from the upper stage of the 
rocket when the rocket reaches a second predetermined 
point in the flight. 
The rocket is supported on a plurality of ciroumferen- 
tially spaced launching supports 18. Each of the launching 
supports 18 has a hold down mechanism including a hori- 
zontal hold down arm 20 which engages a bracket (not 
shown) carried on the skin 22 of the rocket. The hori- 
zontal hold down arm 20 is connected to a pivotal verti- 
cal support member 2 which is moved outwardly from 
the rocket to disengage the hold down arm 20 from the 
bracket prior to launching the rocket. The hold down 
mechanism does not form part of this invention, but is 
illustrated for environmental purposes. 
A controlled release device, generally designated by 
3,415,156 
reference numeral 24, is nnected between the lower 
perimeter of the skin 22 of the rocket 1@ and a bracket 28 
carried on the launching support 18. The bracket 28 in- 
cludes a pair of laterally spaced vertical side plates 30 
having their inner edges integral with a back plate 32 
which is secured to the launching support 18 by any 
bolts and/or welding. A horizon- 
gral with the upper edges of the 
spaced apertures 36 therein for 
receiving the controlled release devices 24. 
The controlled release device 26 includes a die 38 and 
an elongate'd deformable element, such as a metal pin 40. 
The die comprises a pair of side plates 42 having their 
lower ends integral with a circular base 44. The circulx 
base 44 has a conically shaped aperture 44 therein which 
tapers inwardly from the top of the base 44 and termi- 
nates in a cylindrical aperture 47. Each of the side plates 
42 has an aperture 48 adjacent its top for receiving a boit 
ich passes through an aperture 49 in a base portion 
pivot joint 52 carried on the skin 22 of the rocket 
The pivot joint 52 includes a pair of laterally spaced 
vertical flanges 54 each having an aperture 56 therein. 
When the controlled release device is utilized with a 
rocket the lower perimeter of the skin 22 of the Docket is 
connected by a pin 58 intermediate the spaced flanges 54. 
The pin 58 passes through the apertures 54 in the flanges 
54 and an aperture 60 in the skin 22. The pin has a head 
42 on one end and a nut 64 is threaded on the other end 
securing the pivot joint 50 to the rocket. The bolt 48a has 
ia similar head 66 on one end and threaded nut $8 on the 
other end. The side plates 42 are illustrated as having a 
vertical aperture 70 in their medial portion. 
The pin 40 is preferably constructed of any suitable 
ductile metal, including but not limited to ductile steel 
and the like, so that such will be progressively deformed 
by drawing as the rocket is launched from the launching 
supports 18. The pin 40 includes a shank portion 72 hav- 
ing threads 74 adjacent its lower end. The shank passes 
extends upwardly 
the die 38, and is 
integral witlh the smaller en cal frustum shaped 
portion 78. The larger end of conical frustum shaped por- 
rminates in an inwardly tapering elongated por- 
gle provided by the conical shaped aperture 46 
in the die 38 is the substantial complement of the angle 
provided by the conical frustrmn shaped portion 78 on 
the pin 40. The diameter of smaller end of the conical 
frustum shaped portion 78 of pin 40 and the shank por- 
tion 72 is preferably slightly less than the cylindrical por- 
tion 47 of the die so as to penmit passage of the shank 
therethrough. The diameter of the larger end of the coni- 
cal frustum shaped portion 78 is larger than the cylindri- 
cal portion 47 and such depends on desired amount 
energy that is to be dissipated in pulling the pin 
through the die. The particular configuration of the pm 
in the application illustrated is important because the re- 
sulting resistance to movement of the vehiole progres- 
sively diminishes as the diameter of the pin becomes pro- 
gressively less. The angle land length of taper of the 
elongated portions also controls the amount of energy 
necessary to pull the pin 40 through the die 38. Thus, by 
varying (diameter of the pin 40 and the length and angle 
of the tapered portion of the pin the length of time for 
complete release of the rocket can be controlled. 
In operation, after the rocket BO has been erected on 
the launching supports 18, the hold down arms 20 we 
moved into position to secure the rocket onto the launch- 
ing supports 18. The pin 4 of the controlled release de- 
vice 24 is passed through die 38 until the conical frustum 
of the pin 40 engages the conical 
of the die. The shank 72 of the pin 
40 is passed through the aperture 3 of bracket 28. The 
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die is then secured to the pivot joint 50, which is attached 
to the skin 22 of the rocket ID, by means of the bolt 48a. 
The nut 74 is t!i:eaded on the shank 72 of the pin 40 
securing the pin in the bracket 28. After all of the con- 
trolled release devices 26 have been circumferentially 
spaced around the perimeter of the skin 22 of the rocket 
BO, the rocket 10 is in condition $or launohing. 
Prior to starting the engines of the rocket I@, during the 
count down period, readings are taken to insure that the 
equipment of the rocket is in proper operating condi- 
tion. If the readings indicate that the rocket's equipment 
is functioning properly, the engines are started. When the 
engines develop a predetermined amount of thrust, the 
hold down arms 20 disengage the rocket BO, and the rocket 
IO begins !ifting off the launching supports 18. Additional 
readings are taken between the time of starting of the 
engines and releasing of the hold down arms to insure 
that the engines are functioning properly. During the first 
few inches of lift-off, in the preferred embodiment illus- 
trated, the distance is six inches, the controlled release 
devices regulates the ascent oi  the rocket so as to mini- 
mize the usual jar which accompanies the launching op- 
eration when the hold down arms disengage the rocket I@. 
As the hold down arm 20 releases the rocket, the pin 40 
is deformed as it is drawn through the die 38. Since the 
die 38 is tapered, the resistance of the pin 48 becomes 
smaller as the rocket 10 rises, until after approximately 
six inches of rocket travel, the rocket will be complete!y 
free. Additional readings may be taken during the con- 
trolled release of the rocket 10. 
The length of time for complete release of the rocket 
can be modified by varying the length of the tapered pin 
40 and the amount of energy absorbed can be modified 
by varying the major diameter of the tapered pin. By 
previous test and calculation the energy that will be ab- 
sorbed by a controlled release device can be predicted. 
While a preferred embodiment of the invention has 
been described using specific terms, such description is for 
illustrative purposes only, and it is to be understood that 
changes and variations may be made without departing 
from the spirit or scope of the following claims. 
What is claimed is: 
I. A controlled release device for use in launching a 
propelled vehicle from a launching support comprising: 
a die with an aperture therein having a tapered portion; 
an elongated ductile deformable element engaging said 
die through said aperture for exerting resistance to rela- 
tive movement therebetween wherein said deformable ele- 
ment has a tapered portion which is a substantial com- 
plement of said tapered portion of said die, said tapered 
portion of the die and the deformable element being 
tapered inwardly opposite the direction of travel of said 
vehicle; and means for attaching said die to said vehicle 
and for attaching said deformable element to said launch- 
ing support whereby when said vehicle is separated from 
the support during launch, the deformable element is de- 
formed by drawing it through the aperture of said die to 
provide a progressively controlled release of the vehicle. 
2. A controlled release device according to claim 1 
wherein said deformable element has a second tapered por- 
tion tapered inwardly in the direction of travel of said 
vehicle for controlling the length of time for complete 
release of said vehicle. 
References Cited 
UNITED STATES PATENTS 
2,867,153 1/1959 Hirsch _ _ _ _ _ _ _ _ _ _ _ _ _  89-1.806 
3,224,336 12/1965 Eddins _ _ _ _ _ _ _ _ _ _ _ _  89-1.806 
2,602,538 7/1952 Bimba et al. _ _ _ _ _ _ _ _ _  72-274 
SAMUEL W. ENGLE, Primary Examiner. 
U.S. C1. X.R. 
89-1.8 19 


Controlled release device Patent

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