Development of remotely controlled shaped charge for lateral displacement of rocket stages after separatio

Blanchard, W. S., Jr.

English

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REPLY TO 
ATTM OF: e p  
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION 
WASHINGTON, D.C. 20546 
TO z USI/Scientific & Technical Information Division 
Attention: iss Winnie M e  Morgan 
GP/Qffice of Assistant General 
Counsel for Patent Matters 
SUBJECT: Announcement of NASA-Owned 
U,S, Patents in STAR 
In accordance with the procedures contained in the Code GP 
to Code US1 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 Mo,:: 
GayPe Parker 
Enclosure g 
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(NASA CR OR TMX OR AD NUMBER) 
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9 W. S. BLANCHARD, JR 
LATERAL DISPLACEMENT SYSTEM FOR SEPARATED ROCKET STAGES 
?iled Sept. 6, 1966 2 Sheets-Sheet 1 
INVENTOR 
x 
BY 
ATTORNEYS 
Y LANCHARB, JR 
LATERAL DISPLACEMENT SYSTEM FOR SEPARATED ROCKET STAGES 
Filed Sept. 6, 1966 2 Sheets-Sheet 2 
52 
48 
2 
INVENTOR 
ILLARD S. B L ~ ~ C ~ a ~ D ,  JR. 
BY 
ATTORNEYS 
3,384,Q16 
ERAL ~ ~ S ~ ~ A ~ E ~ E N ~  SYSTEM P 
illard S. ~ ~ a n c ~ a r ~ ,  Sr., Hampton, Va., assignor to the 
United States of America as represented by the Ad- 
ministrator of the National Aeronautics and Space 
Administration 
~~~~~~ STAGES 
Piled Sept. 6, 1966, Ser. No. 577,546 
7 CLims. (Cl. 102-49.5) 
AB9 
A system for laterally displacing connected rocket 
stages after separation by detonating a shaped charge 
mounted on the side of one of the stages to impart an in- 
stantaneous sideward force and optionally creating an 
opening in the stage side to permit residual outgassing, 
applying an additional lateral force. 
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 gov- 
ernmental purposes without the payment of any royal- 
ties thereon or therefor. 
This invention relates generally to a separation device 
for adjacent components of a rocket vehicle and more 
particularly to apparatus for prevention of collision be- 
tween the last propulsion stage and the payload of a rocket 
vehicle. 
Various methods and devices have been utilized pre- 
viously for preventing collision of the adjacent compo- 
nents of a rocket vehicle or missile. For example, retro- 
rockets, retrorockets plus tumble rockets, retrorockets plus 
despin rockets plus tumble rockets, spring devices and 
centrifugal despin devices in combination with tumble 
rockets or lateral displacement rockets. Although retro- 
rockets accomplish separation of the adjacent components 
they are much heavier and fail to displace the last propul- 
sion stage from the path of the payload. For a number 
of existing and proposed rocket vehicle configurations 
there is considerable danger that a collision would occur 
between the last propulsive stage and the payload be- 
cause of residual thrust from the propulsive stage, be- 
cause of diff erencs of longitudinal decelerations between 
the bodies resulting from aerodynamic drag forces, or, 
because of a combination of these factors. 
For a nonspinning body the primary disadvantage of 
retrorockets plus tumble rockets is the increased weight. 
For a spinning body there is an additional disadvantage in 
that a much more powerful tumble rocket is required and 
the possibility exists that, depending on predictability of 
the spin rate, the body still might assume a coning mode 
rather than a tumbling mode which would result in possi- 
ble collision. Obviously, the combination of retrorockets 
plus despin and tumble rockets is much heavier than either 
of the above two techniques with the added disadvantage 
that it cannot be accurately predicted that collision will be 
prevented because of significant errors induced by small 
uncertainties in the spin rate and the thrust-time charac- 
teristics of the retrorockets, despin rockets and tumble 
rockets. 
Spring devices utilized for separation of the last pro- 
pulsion stage from the payload do not deflect the propul- 
sion stage from the flightpath and, therefore, permit the 
possibility of a collision resulting from residual thrust 
and/or differences in longitudinal decelerations attributed 
to aerodynamic drag forces. Centrifugal despin devices in 
combination with tumble rockets or lateral displacement 
rockets are complex, expensive and considerably heavier 
than the techniques of the instant invention. 
In order to overcome the disadvantages of the prior art, 
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the instant invention contemplates the use of a shaped 
charge responsive to a remote signal for establishing a lat- 
eral force to remove the last booster stage or propulsive 
unit from the flightpath of the payload. 
It is an object of the instant invention to provide a safe, 
reliable way of preventing collision between the last pro- 
pulsive stage and the payload of a rocket vehicle. 
Another object of this invention is to provide a safe, re- 
liable way of preventing collision between consecutive pro- 
pulsion stages of rocket vehicles in instances where the 
delay time between stage separation and later propulsion 
stage ignition is sufficiently long to allow collision between 
these propulsive stages. 
Another object of this invention is to provide a light- 
weight, inexpensive, highly reliable technique for the pre- 
vention of collision between the payloads and last pro- 
pulsion stages of spinning or nonspinning launch vehicles. 
A further object of the instant invention is to provide 
a technique for preventing collision between the payload 
and last propulsive stage of a launch vehicle wherein a 
shaped charge is detonated to provide an opening in the 
side of the last propulsive stage and thus initiate lateral 
movement thereof from the flightpath of the payload. 
Still another object of this invention is to provide an 
activator for activating an ignitor €or a shaped charge 
that provides lateral thrust to  remove the last propulsive 
stage from the flightpath of the payload. 
A still further object of the instant invention is to pro- 
vide a collision negating technique wherein the payload 
and last propulsive stage of a rocket vehicle are separated 
and a device is activated to provide timely ignition of a 
shaped charge that detonates and laterally displaces the 
last propulsive stage from the flightpath of the payload. 
Generally, the foregoing and other objects are accom- 
plished by providing an activating device which utilizes a 
timing device for accurately providing power to  an initia- 
tor or detonator which causes a shaped charge to detonate. 
Detonation of the shaped charge provides a force lat- 
eral to the flightpath of the propulsive stage as well as an 
opening in the side of the rocket whereby any residual 
pressure within the rocket casing is utilized for assisting 
in the lateral displacement of the propulsive stage of the 
rocket vehicle. A more complete appreciation of the in- 
vention and many of the attendant advantages thereof will 
be readily apparent as the same becomes better under- 
stood by reference to the following description when con- 
sidered in connection with the accompanying drawings 
wherein: 
FIG. 1 is a diagrammatic view of the events occurring 
during launch of a typical multi-stage rocket vehicle; 
FIG. 2 is an isometric view of a rocket casing incor- 
porating a diagrammatic display of the device of the in- 
stant invention; 
FIG. 3 is a cross-sectional view of a portion of the de- 
vice utilized in the instant invention; and 
FIG. 4 is an isometric view similar to that of FIG. 2 
showing the rocket casing after activation of the instant 
invention. 
Referring now to the drawings and more particularly 
to FIG. 1 wherein rocket vehicle 10 is shown in an as- 
sembled configuration and as 'comprising first stage pro- 
pulsive unit 12, second stage propulsive unit 14, third or 
last propulsive unit 16 and payload 18. For clarity, no 
aerodynamic shroud is shown for propulsive unit 16 
since such shrouds are normally ejected prior to last 
stage separation and have no bearing on the instant in- 
vention. Arrows 22 indicate the general direction of the 
flightpath of vehicle 10 and indicate the general directich 
taken (by the various vehicle components at sequential 
times during the launch of vehicle 10. 
As best shown in FIG. 2 rocket casing 24 of propulsive 
unit 16 includes forward section 26 and after or nozzle 
3,384,016 
3 
section 28. It is to be understood that propulsive unit The initial separation which must take place between 
16 adapter hardware, such for example as springs and the payload 18 and last propulsive stage 16 immediately 
associated structure, is not shown for simplicity and to prior to initiation of the shaped charge can be achieved 
avoid confusion in view of the fact that it has little or by any means such for example as springs, retrorockets, 
no effect on the instant inveniion. Center of gravity 32 5 hydraulic pistons or other well known devices. It is also 
of expended propulsive unit 16 is located on centerline to  be recognized that the delay time between separation 
30 as determined by well known computations. and charge ignition is disclosed as one quarter-of-a-sec- 
Negator assembly 48 is shown to include activator 42 ond which is satisfactory €or two vehicle configurations 
which would comprise a timing device and a power studied; however, other periods may prove to be more 
source well within the state of the art for insuring the suitable for other configurations. 
proper timing for activating initiator or igniter 46. Ig- The signal used to initiate the separation and the 
niter 46 is of well known construction and is attached shaped charge can come from any one of a number of 
to a commercially available flexible linear shaped charge sources. A logical source is a pressure switch which reads 
48, shown to be of circular configuration, and causes the chamber pressure within the propulsion stage. Such a 
ignition or detonation of shaped charge 48. The mount- 15 switch would complete the required circuit when the 
ing of the charge on one side of the stage asymmetrical chamber pressure of the propulsion stage dropped to a 
to the flightpath, together with its shape, combine to pro- preselected value. If necessary a delay could be pro- 
duce a resultant explosive force vector 50, upon detona- vided between the switch closure and the separation 
tion. Force vector 50 generally is on a line passing maneuver. Well (known delay devices are suitable for this 
through the center of shaped charge 48 and crossing cen- 20 function, as well as for the time interval between sepa- 
terline 30 of casing 24. The point at which vector 50 ration and shaped charge detonation. 
should cross centerline 30 is at the location of center of The tests conducted have shown that the instant in- 
gravity 32 to provide the most efficient force for lateral ventive technique is sound and that adequate lateral sepa- 
displacement of last propulsive stage 16 from the flight- ration velocities can be obtained for typical configura- 
path of payload 18. As more clearly shown in FIG. 3, 25 tions both in an atmosphere as well as in the vacuum of 
shaped charge 48 is mounted on rocket casing 24 by ad- outer space. These tests have further verified that the lat- 
hesive 52. However, it is to be understood that shaped eral velocity attained is not significantly affected by spin 
charge 48 can be held in place against the required rate and also have shown that the results are satisfactory 
stand-offs of the proper height to exert the maximum with or without outgassing pressures within the propul- 
force on motor case 24 by small springs, an epoxy base 30 sion stage. 
cement, or, as shown, by a flexible bonding agent. Thus, it is seen that this invention provides a light- 
FIG. 4 shows motor casing 24 in which shaped charge weight, inexpensive, highly reliable technique for the pre- 
48 has been detonated to provide opening 54 that would vention of collision between the payload and last pro- 
permit release of any residual gases retained within the pulsion stage of spinning or nonspinning launch vehicles 
casing and arrow 22 which coincides with force vector 35 or between consecutive propulsion stages of such ve- 
50 and indicates the direction of movement of motor hicles. 
case 24 and any attendant appendages which would be Obviously many modifications and variations of this 
included in the structure of last propulsive stage 16. subject invention are possible in light of the above teach- 
Accordingly, it is seen that this invention consists of ings. It is therefore to be understood that within the 
mounting a commercially available flexible linear shaped 40 scope of the appended claims the invention may be prac- 
charge on the side of the last propulsive stage motor ticed otherwise than as specifically described. 
case. The charge is so positioned that the energy released What is claimed as new and desired to be secured by 
upon detonation of shaped charge 48 causes an opening Letters Patent of United States is: 
in the motor case the size and shape of the shaped charge 1. A system for displacing two connected stages of a 
pattern and, aocordingly, the released energy i s  ConCen- 45 rocket from alinement along the flightpath of the rocket 
trated along veotor 50 which passes through center of 
gravity 32 of last propulsive stage 16. The charge could separation means for separating said connected stages 
be initiated approximately one quarter of a second after from each other; 
payload 18 has been separated from propulsion stage 16 an explosive charge means producing an explosive 
by some device, not shown, such for example as springs. 50 force upon detonation; 
The energy released by the detonation, because of the means producing an explosive resultant force on one 
extremely fast burning rate of shaped charge 48, is con- of said stages along a vector lying at an angle to said 
centrated along the single radial vector 50, even at high flightpath by the explosive force produced by the 
spin rates of casing 24. detonation of said charge; and 
activator means operative to detonate said explosive 
for various portions of the instant invention, for example charge upon separation of said stages, whereby said 
the pattern of shaped charge 48 which is shown as cir- one stage is laterally displaced from the flightpath 
cular can be of any configuration. In fact, it may be de- after separation of the said stages. 
sirable to utilize a length and strength for shaped charge 2. The system of claim P wherein said means produc- 
48 in a configuration such that no opening is made in the 60 ing an explosive resultant force includes means shaping 
casing and only the forces resulting from the detonation said explosive charge to direct the explosive force pro- 
would displace the propulsive unit laterally. However, in duced upon detonation and further includes means arrang- 
the illustrated embodiment the cross-sectional area of ing said charge upon said one of the stages asymmetrically 
opening 54 has been proven effective when approxi- with respect to said flightpath. 
mately ten times as great as the cross-sectional area of the 65 3. The system of claim 1 wherein said means pro- 
throat of the propulsive stage nozzle 28 and it is obvious ducing an explosive resultant force further includes means 
that a plurality of shaped charges might be utilized if dining said vector so as to pass substantially through the 
necessary or desirable for most efficient and economical center of gravity of said one of said stages. 
operation. Tests conducted on the in'stant invention uti- 4. In combination with two connected stages of a 
lized shaped charges of 40 and 80 grains per foot. How- 70 rocket disposed in a flightpath at least one of which has a 
ever, the material is commercially available in charges 
from 5 grains per foot to more than 200 grains per foot means for separating said connected stages; 
and, accordingly, it is probable that for some applications explosive charge means mounted on said one of said 
charges smaller or larger than those utilized in the tests stages having a casing to  produce an explosive force 
will be more suitable. 
comprising: 
It is to be understood that there are many alternatives 55 
casing containing gas under pressure: 
75 upon detonation; 
3,384,016 
means for producing rupture of said casing in response 
to said explosive force; and 
activator means to produce detonation of said explosive 
charge means upon separation of said stages, where- 
by the resulting outgassing exerts a displacing force 5 
on said stage. 
5. The combination of claim 4 wherein said means 
producing rupture of said casing includes means directing 
said explosive force at said casing. 
6. The combination of claim 5 further including means 
directing said force directed at said casing along a vector 
lying at an angle to said flightpath. 
7. The combination of claim 6 wherein said vector 
passes through the center of gravity of said one of said 
stages. 
UNITED STATES PATENTS 
3,108,5414 10/1963 Fletcher _ _ _ _ _ _ _ _ _ _ _  102-49.5 
3,180,264 4/1965 Webb _ _ _ _ _ _ _ _ _ _ _ _ _ _  102-24 
3,185,090 5/1965 Weber _ _ _ _ _ _ _ _ _ _ _ _  1 0 2 4 9 . 5  
3,311,324 3/1966 Holt et al. _ _ _ _ _ _ _ _ _ _ _  102-24 
FOREIGN PATENTS 
655,921 8/1951 Great Britain. 
BENJAMIN A. BORCHELT, Primary Examiner. 
SAMUEL FEINBERG, Examiner. 
V. R. PENDEGRASS, Assistant Examiner. 


Lateral displacement system for separated rocket stages Patent

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