Control device and operational mode for fuel flow depletion in sensors - oscillator, switch drive, output switch, and wet-dry simulato

Remington, R. W.

English

NASA Technical Reports Server

1 July 1563 to 1 5  M a r c h  1965 
Contract and CGi?trol No. XAS8 -5431 
SENSOR: FTEL DEPLETXOX 
Prepared  for  
Acoustica Associates, Inc . ,  3331 W e s t  104th Strcet, Los A n ~ c l e s .  California 90045 
(21 3)  ~ P T i r l o  5 - 2 4 1  0 
5 
https://ntrs.nasa.gov/search.jsp?R=19650013608 2020-03-17T00:09:26+00:00Z
I .  0 INTliODUCTICIN e 
This is the sLrnrzar;; reiiort ,  as d e f i n e d  rac ie r  contract number r\iAi5’s-5471 
for  George  C .  Marshall Space Flight Center  ef th ,  Na:icnal A,~ron3- i : ics  
and Spa[-e A c i ~ i i i i i ~ t ~ a ~ i c ~ n ,  s ~ h n ~ i t t e d  by Acotrstri-a Assdiiatcs, h c .  T’.lis 
repor t  covers the period of technical effort  fL.orn 1 Jul-; I 9 6 3  t1-iro~;E-i 
1 5  March  1965, and is the summary of Acoustica Associates,  Lic .  Docu- 
ment DO 5721 and DO 5750 throu:;i: DO 5756-iY. 
2-: 
The t rans is tor  current Lain ?and  the turns raLio of thr feedback trazs- 
f o r m e r  windings a r e  the lirnitin: fac tors  i?? t&c desic;n of fit osci l la tor .  
i h e  operating point of the tzansis tor  1s ~ e l z c t ~ t i  to o ~ t a i r ,  SatCratiJ: l  in 
col lector  cur ren t ,  resuit ing in  a partially cIip2ec1 sinusoidal ~ u p c : .  
m 
In carr);ing out an analysis  of the osciliator c i rcc i t  to escaSlish the 
range of var iables  (in par t icular ,  the feedback k r n s  ratio and the 
cuiresit gain of the t rans is tor ) ,  i t  is necessary to note that the t ran-  
s i s to r  is a cu r ren t  sensit ive device and the circuit configuration must  
lend itself to supplying the base current xequircn;cnt. 
the fredback circui t  comprising secondary of T1 and CZ of scheimatic 
10257 3 ,  is  a s c r i z s  c i rcui i  having an idealized ini,>edance a t  
approxirr-ating the inLJu? ilrlpedance of the base c i rcu i t  of the ::-an- 
sistor in paral le l  with t i ~  equivalen: bias network (IC2 and RT).  
For this reason 
kc, 
and t h e  h l z e  parameter  fo r  tlie t ransis tor  is 
for closely co:.pled coils and a reasonable load on t h e  feedback ~ i z d i n ~ ; .  
3 - 2  


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9-3  
that i i i r b u l ~ ~ i i r  flowr character is t ics  wil l  gene ra l ly  be cxpti i  i.-.nced. 
Howrver ,  L ~ L '  Reynolds '  Numbcr  is ir: the ?ransi:;onal zone arid 
f1Gctua:ion be tween 1an:inar a n d  tt;rbclcnt f low i s  a d i rec t  ~ O S -  
sibifit); of the Lrariahles. 
flow airfoil  ics ts  in a wind tur,nel and S tevcm water tank. 
fatter is used to determine t h e  Froudcs'  Nuniber.  
Fagc and Walke; cor.ductcd 1ar:~iiiar. 
The 
Tlic results showed that the same airfoil  produccd turbuleiit flow 
charac te r i s t ics  a t  a l o w e r  Reynolds' N u m b e r  than xcsu l t s  of the 
wind tunnel. Therefore  at the same Reynolds' N u m b e r ,  i t  is 
p o s s i b l e  to see turbulent flow ir? w a t e r  and lanrinar flow in air  
f o r  thc same configuration. 
'3. General f low character is t ics  of the ,>ropellant a r d  E e n s o r .  The 
Thc d r a g  cocfiicicnt, 
Reynolds '  N w n b e r  describes the f lu id  interaction c h a r a c k r i s t i c  s 
of a cylindrical  sensor  in tlie propellant. 
C o s  for a cylindef. is 
CD = 1.  2 for  low Reynolds' Number  (iarcinai- f low) 
CY) = I .  0 fo r  low-medium Reynolds' Nurnbcr (tuibulerit flow). 
The difference in  CJ-J is attributable r,?ainly to the. separation at 
t h e  end ar iip of the sensor. 
Number difference. 
I: a l so  r c f l v c t s  tlie Re;.-?:ald>,' 
It  can bc shown in  figure 2 and 5 that d r a g  cha;acteristics a r e  
determined fl-om Fioudes '  Number. 
3. c 
d 
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.. -  
P 
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w h e r e  Cp = pressure  coefficient 
S = drag a rea ,  s q u a r e  f e e t  
Figure 4. Length Ratio, X/D-% 
3 
-5 
As long as the bounda-.y layer  condit.iony 3131 2 :Le tank ~\.al! d o  
riot inte:ce,3i the sensor  t ip ,  t he  boundary faycr  p;oiilcA jjcr b e  
will not inte;ferc witli the function of tlie sensor ti:>. 
estimated that the t l \ . id flow vclocity !>assin; by t:iu sensor 
t ip  i s  approxin-,aidy the xi id-s t ream velocity of the fluid. 
The variation cv!iich n i a y  affect the pcrformance of the sensor' 
is the eddy or funncl effects of the outlet and its i-vlaLions\.iL> 
to the tank botton . However, this niay be offset by a n,u i -e  
favorabld 2 r e s s u r e  gradient ir, the sensor localc. 
I' is 
The b0ulldai-y layer calculation is  ;>resented to show thaL It 
does not have any d f e c t  upon sensor and its loi.atitjn. F o r  
tur Lulcn t flow clia rac: te r ist ic s, til e se  vc:n ~ 1 '  powe i' bcltzntia Y 1 
layer I:,iofilio cquation is uscd. 
R e  = Xeynolds' Number 
rp i h e  sensor p r o b e  extends i n t o  thc fliiid 2 inches.  
iaye i .  t k i c k n c s s  i s  assurxted as 2 inches,  then 
If the boundary 
The valuc of the calLulated X,  distance t:pstream from the 
station measured, is nicsh grea te r  than the installation. The 
boundary l aye r  build up will no: exceed 2 inches at the sen6oi 
station. To reitera ' 2 ,  
boundary layei effects. Therdoi -e ,  the sensol t ip will feel  
ii:ll mid-strcarn velocity of the propellant. 
znalysic i s  based iipon a flat plate 
The scnsor tip and sensor body are a unit m a d e  of two di i icrent  
dian!etrical cylinders. The ubt: of a simple cylindrical sha;>e 
LO caliulatc va:ious flow chaIacter is t ics  is not a1terc.d by t l ~ c  
ac tua l  configuration fo r  this Re-j-nulds' Xurnber ran,:e. 
SUhifbiARY AND CONCLUSION 
The followin,;, i s  a suinrnary and conclusior? of tlie events. 
1 .  The Xeg'notds' Number  for this installation ,;encially ciasr,ifitxs 
the flow as t u rhu lcn t .  
4. There is sii i i icient evidence by  var ious analo';ies that h e  total 
per formance  a: the sensor in the 'tiven cn\i:onn:ent will pdr for im 
acc ordin;; to the Acoustics specifications. 
9 - 8  


Sensor, fuel depletion summary report, 1 jul. 1963 - 15 mar. 1965

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