The decision to make the Centaur Vehicle a Space Transportation System (STS) payload meant that new ground support equipment provisions at Launch Pads Pads 39A and 39B were required. These new equipment provisions were needed to service the Centaur vehicle while it was installed in the Orbiter's payload bay prior to launch. This paper describes the design of a new rolling beam umbilical syste (RBUS) being added to the pad fixed service structure (FSS) in order to provide the primary functions of liquid hydrogen (LH2) fill, drain, and vent. The carrier plate itself is a Government-furnished equipment item and of necessity became a T-O disconnect. This permits quick offloading in the event of an abort prior to lift-off. In addition to the rolling beam structure, mechanisms, and fluid lines, it was necessary to design and build a carrier plate simulator to support early development testing of the mast at the Launch Equipment Test Facility at Kennedy Space Center. The RBUS is designed to be compatible with the rotating service structure (RSS) to the extent that the umbilical may be deployed with the RSS mated with the vehicle. It is also designed to clear the RSS as the RSS rotates back out of the way. Accessibility to the Orbiter aft compartment via the 50-1 door had to be maintained

Tatem, B. C., Jr.

English

NASA Technical Reports Server

ROLLING BEAM UMBILICAL SYSTEM 
ABSTRACT 
The d e c i s i o n  t o  make t h e  Centaur v e h i c l e  a Space T ranspo r ta t i on  System 
(STS) payload meant t h a t  new ground suppor t  equipment p r o v i s i o n s  a t  Launch Pads 
Pads 39A and 39B were requ i red .  These new equipment p r o v i s i o n s  were needed 
t o  s e r v i c e  t h e  Centaur v e h i c l e  w h i l e  i t  was i n s t a l  l e d  i n  t h e  O r b i t e r ' s  pay- 
l oad  bay p r i o r  t o  launch. Th i s  paper descr ibes t he  des ign o f  a  new r o l l i n g  
beam u m b i l i c a l  system (RBUS) be ing  added t o  t he  pad f i x e d  s e r v i c e  s t r u c t u r e  
(FSS) i n  o rde r  t o  p rov ide  t he  p r imary  f unc t i ons  o f  1  i q u i d  hydrogen (LH2) f i l l ,  
d ra in ,  and vent.  The c a r r i e r  p l a t e  i t s e l f  i s  a  Government-furnished equipment 
i t e m  and o f  necess i t y  became a  T-0 d isconnect .  Th i s  permi ts  qu i ck  o f f l o a d i n g  
i n  t h e  event  o f  an a b o r t  p r i o r  t o  l i f t - o f f .  I n  a d d i t i o n  t o  t h e  r o l l i n g  beam 
s t r u c t u r e ,  mechanisms, and f l u i d  l i n e s ,  i t  was necessary t o  des ign  and b u i l d  
a  c a r r i e r  p l a t e  s i m u l a t o r  t o  suppor t  e a r l y  development t e s t i n g  o f  t he  mast 
a t  t h e  Launch Equipment Tes t  F a c i l i t y  a t  Kennedy Space Center. 
The RBUS i s  designed t o  be compat ible w i t h  t h e  r o t a t i n g  se rv i ce  s t r u c t u r e  
(RSS) t o  t h e  ex ten t  t h a t  t h e  u m b i l i c a l  may be deployed w i t h  t h e  RSS mated w i t h  
t h e  vehicle.  It i s  a l s o  designed t o  c l e a r  t h e  RSS as the  RSS r o t a t e s  back out 
o f  t h e  way. A c c e s s i b i l i t y  t o  t h e  O r b i t e r  a f t  compartment v i a  t h e  50-1 door 
had t o  be maintained. 
The RBUS c o n s i s t s  o f  an u m b i l i c a l  assembly t h a t  supports t he  c a r r i e r  
p l a t e  on t h e  end o f  a  t r u s s  beam ex tend ing  f rom a  ca r r i age  assembly t h a t  
t r a n s l a t e s  on double r a i l s  by means o f  crane t r a c k  wheels. A  porch s t r u c t u r e  
was added t o  t h e  FSS t o  mount t h e  i n c l i n e  p o r t i o n  o f  t h e  assembly t h a t  con- 
t a i n s  t h e  r a i l s .  A  s u i t a b l e  s to rage  l o c a t i o n  on t h e  FSS d i c t a t e d  a  6-degree 
i n c l i n e  up t o  t h e  Centaur i n t e r f a c e  l oca ted  on t h e  p o r t  s ide  o f  t h e  O r b i t e r  i n  
e s s e n t i a l l y  t he  same l o c a t i o n  as t he  p rev ious  T-4 i n t e r f a c e  on t h e  p o r t  side. 
The r o l l i n g  beam t r a v e l s  a d is tance  o f  11 m (36 f t )  t o  the  stowed p o s i t i o n  i n  
t h e  FSS. Power f o r  acce le ra t i on  o f  t he  r o l l i n g  beam assembly i s  p rov ided  by a  
dropweight assembly. A l i n e a r  d i s k  brake decelerates the r o l l i n g  beam t o  i t s  
parked o r  stowed pos i t i on .  Upon i n i t i a l  mot ion o f  the  car r iage ,  the  r o l l i n g  
beam separates i t s e l f  f rom the  ground supply l i n e s  as we l l  as f rom the veh i -  
c le.  Th i s  was d i c t a t e d  by the  l o n g  r e t r a c t  distance. Th is  paper presents  
impor tant  design approaches considered but  not  used, i n  addi  t i  on t o  desc r i  b i  ng 
t h e  r o l l i n g  beam, which i s  i n  t h e  process o f  be ing  implemented. 
Th i s  RBUS was des i  gned by P lann i  ng Research Corporat ion,  Systems Serv ices  
Company under c o n t r a c t  t o  NASA's Kennedy Space Center i n  F lo r i da .  
*Bemis C, Tatem, J r, , Plann ing  Research Co rpo ra t i  on, Kennedy Space Center, 
F l o r i d a  
https://ntrs.nasa.gov/search.jsp?R=19830016629 2020-03-21T04:13:14+00:00Z
INTRODUCTION 
I n  e a r l y  1981, an ex tens i ve  t r a d e  study was conducted t o  determine t h e  
best approach t o  t a k e  t o  p rov i de  f o r  t h e  STSICentaur LH2 s e r v i c i n g  r equ i r e -  
ments. Numerous concepts were prepared, a'nd t h e  ones cons idered most promi s -  
i n g  are:  
a. T a i l  s e r v i c e  mast (TSM) w i t h  Centaur s e r v i c e  added 
b. RBUS 
c. TSM mounted reusable  pay load umbi li ca l  mast 
d. TSM mounted expendable pay1 oad umbi 1 i ca l  mast 
TSM Wi th  Centaur Se rv i ce  Added. Necessary a d d i t i o n a l  l i n e s  would be 
added t o  t h e  e x i s t i n g  TSM's c a r r i e r  p l a t e s  as dep ic ted  i n  f i g u r e  1. L ines  
would be rou ted  down t h e  s e r v i c e  masts as shown i n  f i g u r e  2. An o v e r r i d i n g  
disadvantage o f  t h i s  approach was i t s  adverse e f f e c t  on O r b i t e r  f l i g h t  weight  
f o r  t h e  LH2 s e r v i c e  funct ions.  
RBUS. An e l e v a t i o n  view o f  t h i s  approach i s  shown i n  f i g u r e  3 and i s  
-
descr ibed  i n  more d e t a i l  i n  t h i s  paper. The o v e r r i d i n g  advantage o f  t h i s  
approach i s  t h a t  i t  i s  l oca ted  on t h e  FSS w i t h  no impact on t h e  Veh i c l e  
Assembly B u i l d i n g  (VAB) o r  t h e  mobi le  launcher  p la t fo rm.  
TSM Mounted Reusable Payload U m b i l i c a l  Mast. An e l e v a t i o n  view o f  t h i s  
approach i s  shown i n  f i g u r e  4. Th i s  system i s  s i m i l a r  t o  a s h o r t  r o l l i n g  beam 
except i t  r e t r a c t s  i n t o  a hardened hous ing mounted on t o p  o f  t he  TSM. The 
c a r r i a g e  moves on a smal l  t rack .  Dropweight i n i t i a t i o n  would be by a t r i g g e r  
ac tua ted  by t h e  TSM dropwei ght. The TSM would r e q u i r e  s t r u c t u r a l  a d d i t i o n s  t o  
support  t h e  added weight and b l a s t  l oad  due t o  added s a i l  area o f  t he  pay load  
u m b i l i c a l  mast. The i n s t a l l a t i o n  has major impact on VAB p la t f o rms  as w e l l  as 
t h e  RSS. 
TSM Mounted Expendable Pay1 oad Umbi 1 i c a l  Mast. The c a r r i e r  p l a t e  suppor t  
i s  s i m i l a r  t o  t h e  r o l l i n g  beam, bu t  a r o t a t i n g  mast w i t h  counterweight  i s  used 
t o  r e t r a c t  t h e  c a r r i e r  p l a t e  pas t  t h e  v e h i c l e  1 i f t - o f f  d r i f t  curve. Lanyards 
pene t ra te  t h e  t o p  o f  t h e  TSM and use t h e  TSM dropweights f o r  t h e  normal re -  
t r a c t i o n .  Th is  approach i s  dep i c t ed  i n  f i g u r e  5. Th is  approach was r u l e d  ou t  
because o f  closeness t o  t h e  O r b i t e r  w ing and impact on t h e  VAB. 
The conc lus ion  o f  these s tud ies  was t h a t  t h e  RBUS approach was se lec ted  
t o  per fo rm t h e  t a s k  o f  p r o v i d i n g  LH2 s e r v i c e  f o r  t h e  STSICentaur a t  Launch 
Pads 39A and 39B. The des ign o f  t h e  p ro to t ype  RBUS was j u s t  completed a t  t h e  
t ime  o f  submission o f  t h i s  paper. Th i s  p ro to t ype  i s  t o  be t e s t e d  a t  t h e  
Launch Equipment Tes t  F a c i l i t y  t h i s  summer. 
ROLLING BEAM DESCRIPTION 
Ma jo r  assemblies o f  t h e  se l ec ted  RBUS i nc l ude :  




I ORB. - DRIFT CURVE 
CARRIER PLATE LANYARD I LCARRIER PLATE 
ARM RETRACT LANYARD 
SHOCK ABSORBER 
Xo 1368 4.3 m 
(14 FT 
2 IN) 
LANYARD GUIDE I 
I y LH2 TSM I \ I I k 
EXST TSM MAST DROPWEIGHT 
-_ . I / 
T-O INTFC f+" 
I 
-54- 
Figure 5. Payload Umbilical Mast - Expendabl e-El evation View 
a. STSICentaur r o l l i n g  beam assembly ( f i g u r e  6 )  
b. U m b i l i c a l  c a r r i e r  p l a t e  assembly ( f i g u r e  7 )  
c. Dropweight tower assembly ( f i g u r e  8 )  
I n s t a l l a t i o n  o f  t h i s  equipment a t  t he  Launch Equipment Tes t  F a c i l i t y  f o r  
t e s t  e v a l u a t i o n  and development p r i o r  t o  d e l i v e r y  t o  Launch Complex 39A i s  
shown i n  f i g u r e  9. A d e s c r i p t i o n  o f  t he  cryogenic  supply system i s  beyond t h e  
scope o f  t h i s  paper. 
Umbi 1  i c a l  Assembly. The umbi 1  i ca l  assembly cons i s t s  o f  the  ground ca r -  
r i e r  p l a t e  ( supp l i ed  by Rockwell I n t e r n a t i o n a l  ) suppo r t i ng  l i n k s ,  t h e  LH2 f i  11 
and d r a i n  vacuum-jacketed (VJ) f l e x  l i n e ,  and t h e  LH2 vent VJ f l e x  1  ine. The 
l i n k s  w i l l  be equipped w i t h  b a l l  j o i n t s  t o  permi t  s i de - t o - s i de  mot ion as w e l l  
as up and down. These l i n k s  support  t he  c a r r i e r  p l a t e  a f t e r  disconnect, The 
u m b i l i c a l  assembly inc ludes  t he  hockey s t i c k  d isconnect  lanyards and t h e  
s t a t i c  lanyards t o  prevent  r o t a t i o n  o f  the ground c a r r i e r  p l a t e  towards t h e  
O r b i t e r  a f t e r  disconnect. 
R o l l  i n g  Beam Assembly. The r o l l i n g  beam assembly cons is ts  o f  a  tapered 
t r u s s  beam. One end o f  t he  beam supports t he  u m b i l i c a l  assembly. The o t h e r  
end o f  t he  beam i s  b o l t e d  t o  t h e  ca r r i age  assembly. The c a r r i a g e  assembly 
con ta ins  wheels t h a t  capture t h e  c a r r i a g e  t o  t h e  r a i l s .  The c a r r i a g e  assembly 
con ta ins  a  ground separat ion p l a t e  t o  support  t h e  c a r r i a g e  mounted c ryogen ic  
l i n e  qu i ck  disconnects,  t h e  c a r r i e r  p l a t e  purge disconnect,  and the var ious  
hazardous gas sensing l i n e  disconnects. The LH2 fill and d r a i n  l i n e s  make a 
180-degree t u r n  f rom t h e  beam t o  l i n e  up i n  t he  c a r r i a g e  w i t h  the ground 
separa t ion  p la te .  
L i n e a r  Brake. A l i n e a r  brake ac t s  on a  f r i c t i o n  p l a t e  mounted t o  t h e  
c a r r i a g e  t o  s top  t h e  r o l l i n g  beam assembly. The brake system inc ludes  gu ide  
r o l  l e r s  i n  f r o n t  o f  t he  brake. The brake cons is ts  o f  two s p r i  ng-actuated 
ca l  i p e r - d i  sk-type u n i t s  t h a t  a re  pneumati c a l  l y  re t rac ted .  
I n c l i n e  Assembly. The i n c l i n e  assembly se ts  t he  r o l l i n g  beam on a  6- 
degree angle necessary t o  i n t e r f a c e  w i t h  t h e  O r b i t e r  and p rov ide  stowage ca- 
p a b i l i t y  upon r e t r a c t  w i t h i n  t h e  FSS. I n  a d d i t i o n  t o  the  l i n e a r  brake de- 
s c r i b e d  above, t he  i n c l i n e  con ta ins  f i n a l  overrun s top  energy absorbers de- 
s igned f o r  11,340 k g  (25,000 l b )  over a  d i s tance  o f  0.472 m  (18.6 i n ) .  The 
i n c l i n e  assembly supports t he  s t a t i c  h a l f  o f  t he  ground separat ion p l a t e  f o r  
t h e  LH2 f i l l  and d r a i n  l i n e s  and the  gaseous hydrogen vent l i ne .  A pneumati- 
c a l  l y  powered winch prov ides t he  c a p a b i l i t y  t o  l i f t  t h e  r o l l  i n g  beam up t h e  
i n c l i n e .  Upper guide r a i l  and r o l  l e r s  1  i m i t  c a r r i a g e  sway. S t a i r s  and access 
p l a t f o rms  are p rov ided  on t h e  i n c l i n e ,  g i v i n g  access t o  t he  r o l l i n g  beam i n -  
c l  ud ing  umbi 1 i ca l  and ground separa t ion  p la tes.  Cool i n g  water nozzles and 
p i p i n g  w i l l  be mounted t o  t h e  i n c l i n e  t o  p r o t e c t  t h e  u m b i l i c a l  c a r r i e r  p la te .  
ENERGY 
ABSORBERS 
VENT 1,- L H ~  FILL & DRAIN 
PLAN 
IU 
CO 
'T FLUID SEPARATION PLATE PLATES (MOUNTED ON PYROTECHNIC 
CARRIAGE) RELEASE 
ARM 
ELEVATION 
F i g u r e  6. STS/Centaur  Roll i 'ng Beam Assembly 
LIMIT LANYARDS 
HOCKEY STICK 
xo = 1290 
SECONDARY LOWER LINKS 
TRANSITION ARM 
HOCKEY STICK CARRIER PLATE 
CRYOGENIC LINES 
Figure 7. STS/Centaur Umbil ical Carrier Plate Assembly 
Figure 8. STSICentaur Rolling Beam Dropweight Tower Assembly 

Dropwei ght  Tower. The dropwei ght  tower con ta i  ns t h e  dropwei ght, drop- 
weight 1  i f t i  ng winch, energy absorbers, k i n e t i c  and s t a t i c  sheaves and cables,  
and cab le  s lack  takeup weight,  bungee, and pu l ley .  Cable l eng th  i s  ad jus ted  
a t  t h e  attachment t o  t h e  cab le  s lack  takeup weights and pu l leys .  The main 
dropweight c a b l e ' i s  rou ted  through sheaves t o  t h e  ca r r i age  a t t a c h  p o i n t  on t h e  
i n i t i a t i n g  arm, which w i l l  be descr ibed l a t e r .  To permi t  l i f t i n g  the  drop- 
weight,  t h e  ca r r i age  end o f  t h e  main cable i s  secured e i t h e r  t o  t he  c a r r i a g e  
o r  t o  t h e  i n c l i n e  s t r u c t u r e  a t t a c h  p o i n t  ( f o r  weight l i f t i n g  only). 
Porch Assembly. The porch assembly prov ides the  necessary ex tens ion  o f  
t h e  FSS t o  support  t h e  r o l l i n g  beam assembly i n  p o s i t i o n  t o  se rv i ce  t h e  
Centaur payload i n  t h e  O r b i t e r  payload bay. 
Disconnect Mechanisms. The d isconnect  mechanisms schematic i s  shown i n  
f i q u r e  10. A l a t c h  mechanism ho lds  t he  r o l l i n g  beam i n  O r b i t e r  mated p o s i t i o n  
on-the i n c l i n e  p r i o r  t o  launch w i t h  t h e  dropweight app l y i ng  s t a t i c  t ens ion  t o  
t h e  dropweight cable. The dropweight cab le  i s  a t tached t o  t h e  i n i t i a t i n g  arm 
mounted i n  t h e  carr iage.  Th is  i n i t i a t i n g  arm f i r s t  mot ion a c t i v a t e s  t he  hock- 
ey s t i c k  re lease  lanyards and then  t r ansm i t s  t h e  a c c e l e r a t i n g  f o r c e  o f  t h e  
dropwei ght t o  t h e  c a r r i  age. A redundant re1 ease mechani s~n t r i  ggers t h i s  ac- 
t i on .  Pr imary re lease  i s  by a py ro techn ic  b o l t  w i t h  dual charges. E i t h e r  o f  
these d i scha rg ing  w i  11 separate t h e  py ro techn ic  b o l t  and re lease t he  i n i t i  a t -  
i n g  arm. I f  t h e  py ro techn ic  b o l t  does not  separate, an overcenter  mechanism 
w i l l  be re leased by a l anya rd  t h a t  i s  a c t i v a t e d  by c a r r i e r  p l a t e  lower l e v e r  
extension, which takes p lace  as t he  Space S h u t t l e  veh i c l e  l i f t s .  The i n i t i a l  
p ro to type  r o l l  i ng beam w i  11 i nco rpo ra te  a py ro techn ic  b o l t  s imu la to r  t h a t  i s  
re leased by a gaseous n i t r o g e n  pressure supply. 
I n i t i a t i n g  Arm. The i n i t i a t i n g  arm and i t s  assoc ia ted py ro techn ic  re-  
lease arm a r e  t h e  hea r t  o f  t he  re lease mechanism, as they coord ina te  and con- 
t r o l  t h e  f unc t i ons  o f  dropwei ght  tens ion,  py ro techn ic  release, hockey s t i c k  
a c t i v a t i o n ,  and mechanical secondary re1 ease. The t r i  gger t h a t  mates w i t h  t h e  
py ro techn ic  re lease  arm i s  a  be1 1 crank at tached t o  t h e  overcenter  l inkage. 
The l anya rd  a c t i o n  t o  break t h i s  l i n kage  over  cen te r  w i  11 re lease the  t r i g g e r  
and permi t  r o l l i n g  beam a c t i o n  t o  s t a r t  i n  t h e  event t h e  redundant py ro techn ic  
b o l t  f a i  1s t o  discharge. 
DESIGN CRITERIA 
P e r t i n e n t  design c r i t e r i a  f o r  t h e  RBUS are g iven i n  t a b l e  1. A f t e r  
s e r v i n g  t h e  f u n c t i o n  o f  l oad ing  LH2 on to  t h e  Centaur payload, t he  r o l l  i n g  beam 
must remain mated w i t h  t h e  O r b i t e r  u n t i l  1  i f t - o f f  t o  p rov ide  f o r  qu ick o f f -  
l o a d i n g  i n  t h e  event o f  a  launch abor t  requirement. The s i gna l  t o  s t a r t  t he  
r e t r a c t i o n  sequence o f  t he  r o l l i n g  beam i s  i n i t i a t e d  a t  s o l i d  rocke t  boos te r  
i g n i t i o n .  W i t h i n  l e s s  than 3 s  f rom t h e  r e c e i p t  o f  t h i s  s igna l ,  the  r o l l i n g  
beam i s  t o  be r e t r a c t e d  t he  necessary 11 m (36 f t )  o f  i n c l i n e  d i s tance  and i s  
s t o r e d  w i t h i n  t h e  i n c l i n e  s t r u c t u r e  where i t  i s  sprayed w i t h  c o o l i n g  wate r  t o  
p r o t e c t  i t  f o r  t h e  next requi  red 'launch. 
I TRANSITION 
DROPWEIGHT 
RELEASE ARM 
PNEUMATIC - LETF 
PYROTECHNIC - PAD I 
!- PYROTECHNIC 1 
RELEASE 
NUT 
ENERGY 
ABSORBERS 
I 
I 
DROPWEIGHT I I ROLLING BEAM TOWER I ASSEMBLY 
NOPE: STRUCTURE NOT 
SHOWN FOR CLARITY 
UMBILICAL CARRIER 
PLATE ASSEMBLY 
Figure 10. STS/Centaur Rolling Beam Umbilical System-Disconnect Mechanisms Schematic 
Table 1. RBUS Design C r i t e r i a  
Sub jec t  
Beam r e t r a c t  d i  s tance 
A c c e l e r a t i o n  d i  s tance 
Coast d i s t ance  
Dece le ra t i on  d i s t ance  
Overrun d is tance  
R o l l  i ng beam we igh t  
R o l l  i ng beam mate r i  a1 
F a c t o r  o f  s a f e t y  - dynamic members 
F a c t o r  o f  s a f e t y  - s t a t i c  members 
Beam r e t r a c t  t ime  
A c c e l e r a t i o n  G's 
Dece le ra t i on  G's  ( d i s k  brakes o n l y )  
D ropwei ght:  
R o l l i n g  beamldropweight t r a v e l  r a t i o  
D ropwei gh t  t r a v e l  
D ropwei gh t  energy absorp t ion  
R o l l i n g  beam module 
R o l l i n g  beam i n c l u d i n g  u m b i l i c a l  
I n c l i n e  
Porch 
To ta l  weight  t o  be t r a n s p o r t e d  
Brake t y p e  
Brake f o r c e  
Normal c o e f f i c i e n t  o f  f r i c t i o n  
E s t i m a t e d c o e f f i c i e n t  o f  f r i c t i o n  
v a r i a t i o n  
F i n a l  s top  overrun 
F i n a l  s top  overrun f o r c e  
I n c l i n e  angle  
Urnbi 1  i c a l  t y p e  
Coo l i ng  p r o v i s i o n  (wa te r )  
Umbi li c a l  re lease  - p r imary  
Umbi 1  i c a l  re lease  - secondary 
U m b i l i c a l  re lease  - t e r t i a r y  
R o l l i n g  beam re lease  - pr imary  
R o l l i n g  beam re lease  - secondary 
C r i t e r i a  
11.7 m  (38.3 f t )  
6.1 m (20.0 f t )  
3.0 m (10.0 f t )  
2.5 m ( 8.3 f t )  
0.46 m ( 1.5 f t )  
4,990 k g  (11,000 l b )  
ASTM A36 
2.0 minimum on y i e l d  
AISC c r i t e r i a  
<3.0 s  
<l. 0 
<2.5 (normal ) 
<5.0 (abnormal ) 
2  t o  1 
3  m (10 f t )  
2X(14,062 kg)X 0.41 m  
90% s t a t u s  we igh t  
4,990 k g  (11,000 l b )  
15,876 k g  (35,000 7b) 
8,618 k g  (19,000 l b )  
29,484 k g  (65,000 l b )  
L i n e a r  d isk  
11,340 k g  (<25,000 l b )  
0.30 
0 . 2 5 t 0 0 . 3 0  
Energy absorber 
2X(5,670 k g )  
6.00 degrees 
TSM approach 
1,782 l / m i n  (500 gal /min) 
Lanyard re1 ease 
Col 1  e t  ope ra t i on  normal 
Hockey s t i c k  a c t i  vates c o l l  e t  
Lanyard re1 ease 
Col 1  e t  f a i  1  ed 
Hockey s t i c k  breaks c o l l  e t  shear p i n  
Lanyard re1 ease 
Hockey s t i c k  f rozen  
Tension breaks c o l l e t  shear p i n  
Py ro techn i c  b o l t  
Lanyard re1 ease o f  mechanical t r i g g e r  


Rolling Beam Umbilical System

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