Camera protecting device for use in photographing rocket engine nozzles or other engine component

Bailey, R. L.

Tibbitts, W. C.

English

NASA Technical Reports Server

REPLY TO 
ATTN OF: Gp 
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION 
WASHINGTON, D.C. 20546 
November 19, 1970 . 
u s ~ / ~ c i e n t i E i c  & Technical Xnfonnatlton Div is ion  
Aetentiont Mise Winnia M. Morgan 
FROM t ~p/Of%ice of A s s i ~ t a q t  General Counsel for 
Patent Matters 
Su5JEZT:. Anno~cement: of NASA-Owned U.  S,  Patents in Sr2AR 
In accordance w i t h  the procedures agreed upon by Code GP 
and Code USI, the attached NASA-owned U, S .  Patent is being 
forwarded for abstracting and announcenlcant i n  NASA STARo 
. 
,ma t o ~ o u f n g  fnfonaafgori j.s '$roviitear 
U. S .  Patent No. 
Government or 
Corporate Employee 
Supplementary Corporate 
Source (if applicable) : Jet propulsion Laboratory 
- Xi! this pateat ewers an Amenticm mad"%t a a m  
cb D emkrerctor, the following Le applt&l6r 
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https://ntrs.nasa.gov/search.jsp?R=19710008990 2020-03-17T02:48:25+00:00Z

July 94, 1970 JAMES E. -WEBB 3,520,238 
ADMiNISTRAfQR OF ^$"HE N A f  lONAL AERONASTECS 
AND SPACE ADMINBSTRATION 
APPARATUS .$ND METHOD F O R  PROTSCTIME A PHCTOGRAQMIC D C V E C C  
Filed Bec. 13, 2.961 2 Sheets-Sheet 2 
United States Patent Of i  3,520,238 ce Pa,, ed ,I,,, 1, ,970 
1 2 
High preccrirc gas introduced into the iitlci: erhaustc 
3,520,238 
AND pdETHOD FOR A t1110"gh the vlewing cltrci no7zle as a high velocity jrt 
PHOTOGRAPHIC DEVICE which deflects the engine exhaust gases and particles and 
James E. Webb, AdministPator of the National Aeronau- Plevents them flom entering the duct and danlaging the 
tics and Space Adnninistrat;cPn, with respec( to an invela- protective wiirdow. Preferably, the enclosure walls are 
tion of Richard I,. Bailey and William C. Tibbitts, both ' formed with a plurality of passages for ducting cooling 
of Eancaster, Calif. Auid therethrough to maintain the tempelatuse within the 
Filed Dec. 13, 1967, Ser. No. 690,163 enclosure at a level satisfactory for the camera. Also, to 
Pnt. CI. GQ3b 17/02 minimize the possibility of palticles entering the en- 
U.S. Cl. 95-11 C'aiinls closuie, a pressurized inert gas is ductcd through the 
l0 enclosule to maintain a positive pressure within the en- 
ABSTRACT OF THE DPSCEOSURE closure at all times. With this combination of a pressurized camera zone with auxiliary water cooling and a gas-swept 
A camera to photograph a rocket engine nozzle in viewing zone, a rocket engine nozzle may be satisfactorily 
operation is positioned within a rugged enclosure cooled photographed in opelation without damaging the camera 
by water and pressuiized by inert nitiogen to pievent equipment. 
particles from entering the enclosure. A viewing duct in 
the wall of the enclosuie aligned with the camera lens BRIEF DESCRIPTION OF THE DRAWINGS 
is formed with a protective window at its inner end and For a more thorough undeistanding of the invention 
a reduced diameter viewing port at its outel end. High reference may be had to the following detailed desciip- 
pressure gas injected into the duct exhausts through the 20 tion and diawings wherein: 
port as a high pressure jet which deflects the engine ex- FIG. 1 is a schematic view showing the photoglaphic 
haust and prevents it from enteiing the duct and dainag- device of the invention in position to photogiaph a rocket 
ing the window or the camera. engine nozzle; 
FIG. 2 is an enlarged side cross-sectional view of the 
25 piotective enclosure of the invention; and 
ORIGIN OF THE INVENTION FIG. 3 is an elevational view of the left end of the 
enclosure of FIG. 2. The invention described herein was made in thc pel- 
formance of work under a NASA contract and is sub- DESCRIPTION OF THE PREFERRED 
iect to the vrovisions of Section 305 of the National 30 EMBODIMENT 
~eronaut ics  and Space Act of 1958, Public Law 85-568 
(72. Stat. 435; 42 USC 2457). In FIG. 1, the photographic device 10 of the invention is shown mounted on a tripod 12 anchored securely in a 
BACKGROUND OF THE INVENTION supporting surface 14 with the device aligned on the axis 
 hi^ invention relates to a means for a 35 16 of a rocket engine nozzle 18. The photogiaphic device 
camera or similar device to enable the camera to be 10 be seen in FIGS. 2 and 3 to include a stlong, 
utilized to take photographs of a rocket nozzle or other rugged enclosule 20 surrounding a camera 22.  he en- 
engine component while the camera is located in high closure 20 includes an inverted U-shaped, upper poition 
temperature exhaust of a rocket or engine. 24 having side walls 26, a top wall 28, and end walls 30 
In the development and testing of high temperature sys- 4 0  and 31. A s ~ l ~ ~ o r t i n g  flame 29 attached to the walls 26, 
terns such as rocket engines 01 gas turbines, it is highly 30, and 31  by angle brackets 33 provide additional 
desirable to be able to observe the erosion of the engine Strength the unit. 
components while in operation. It is also desirable in The side, top and end walls of the upper portion 24 of 
some instances to study the high temperature exhaust the enclosure are piovided with a plurality of intercon- 
gas stream from the engine,  hi^ of course requires that 45 nected Passages schematically illustrated at 60 for cir- 
the camera be protected from the high temperatures and circulating coolant such as water for cooling the interior 
pressures that exist and also from the high velocity of the enclosure. Coolant is admitted to the passages 60 
particles which are often present, paiticularly in solid through an 52 in the the upper 
propellant rockets. These problems are most severe if the portion 24 of the enclosure 20, passes through the pas- 
photographic device is positioned directly in the exhaust 50 Sages 60 in the front, side, top and rear walls and leaves 
stream where it is often desiiable to make observations. the passages through an outlet 64 in the rear wall 31 of 
While theie have been some attempts to protect a the 
camera properly in such extreme environments these have Two pair of spaced vertically oriented lug plates 32 
only been partially successful and in many instances ob- are attached to the lower portion of the flont wall 30. 
servation of the erosion of a rocket engine nozzle for ex- 55 A pair of spaced lugs 34 mounted on a base ~ssembly 
ample has been limited to study after the englne is shut 36 extend between the 11% plates 3%. A pivot pin 38 
off. extending through each lug 34 and each pair of lug plates 
It  is also desirable that the carneia protective appaI atus 32 Connects the upper poltion 24 of the enclosute .Lo 
be a self-coniaincd unir which can function wilhout ex- (he base zssemb!y 36. 
pensive engine modificatioir, and a,hich can be r n o ~ ~ e d  60 AS Can be seen from FIG. 2, the base assembly 36 in- 
to various locations for pelforming observntlon func- clude~ a pair air metal plates 39 and 40 wii:ch a re  ~i7i'cld 
t~ons  in a variety of extreme eiivironments. by a ~1111al:ty of rib\ 42 d r h n ~ n g  di: elongat-d pr<\njie 
43 mithlil the base a~sernbly 36 The pasup?? 43 t.iiend\ SUMMARY OF PHE LhVLN1IC)i.I fiorn an ~nlet 44 near the fol~%ard end of tlrc base asseill- 
In accordance with the invention, the apparatus for 65 bly 36 and terminates at an outlet 46 neat the rear of 
protecting a camera while photographing a rocket engine the base assembly. The lower plate 40 is mounted on a. 
nozzle or similar situation includes a rugged enclosure supporting beam 48 which extends from front to rear 
surrounding the camera, with the enclosure having a view- at the middle of the base assembly 36.  The base assembly 
ing duct in one wall which tapers from a large inner further includes a heavy inner supporting plate 50 which 
diameter to a srnall diameter nozzle at its outer end. A is attached to the plate 39 for supporting vertically 
strong window extends across the duct to perrnit light to oriented memers 52 which in turn support the camera 22. 
enter the enclosure while protecting the camera lens. The entire base assembly 36 is attached to a bracing 
:;>??20>-2:3t3 
3 4 
post 51 which as sceil In i-iG 7 cxter;d\ thro~rgl, tile be dflven 111to the nlte ioi of rhe c-nclo,uie rn vicl.c cf 
&L pl,iit, 31 '~rld 46 1s reicasahiy dLlaciiLd l l ~  lower "1- < '  i i ~~> \ ' - i~~ i  diifiitl~tr~ l~ ~ ~ 0 1 d ~ d  TO i 1 1 1 i i i i 1 ~ i i ~  ih t  
cyd b,r n uill 55 an  scchct ;il,-m?.iti 56 of [he pis~bi l l iy  ~f such paitlcles er7[eiirg the eq~iosure, an 
tripod assenlbly 12, shown in FTG 1 me1 t g a i  arich as nitrogen rs c~vppliect throrigh the i ~ l e t  
The r~ppel poitzon 24 of the enclosure 20 \ecored 66 to the rnielic! OF tile enclozure 20 and allowed lo cx- 
to the babe asseiiibly 36 by a plurallty of clamps 58 '4""" though the outlet 68. Nltiogeil pieqsures of ap- 
spaced around the per~phery of the base assembly and ~~oxlmate iy  25 pounds per sqL1ale Inch have been found 
extcnd~ng through the base and an outwardly extending adequate fol this purpose. 
flange 59 attached to the side walls 26 and front and To provide a wind-swept viewing alea for the camela 
rear walls 30 and 31 of the enclosure. 22 and to plotect the w ~ n d o v ~  90 from the h ~ g h  velocity 
Positioned in the front wall 30 of the enclosure is a lo exhaust particles, an inert gas, such as nitrogen, is also 
gas inlet line 66 which leads into the interior of the fed into the duct assembly 70 through the main mamfold 
enclosure. A gas outlet line 68 extends through the tear inlet 90, manifold tube 88 and tubes 92. This gas ex- 
wail 31 of the enclosure. hausts outwardly or forwardly through the nozzle 78 
In the front wall 30 of the enclosure, there is also 15 against the force of the learwardly moving engine exhaust 
mounted a viewing duct assembly 70 axially gases. Th? nitrogen exiting through the nozzle 78 effec- 
the lerls unit 72 of the camera 22. ~h~ duct assembly 70 tively deflects the engine exhaust stlean1 containing the 
includes a short, heavy cylindricat member 74 and a hot gases and the particles which nolmally would im- 
member 76 having a cylindrical inner end 7(jn which pinge upon and damage the protective window 80. 
mates with the cylindrical member 74 and having a 20 The viewing duct assembly 70 including the window 
frusta-con~cal outer end 76b whlch tapers to a rela- 80 is of rugged design to withstand pressures of at least 
tively small diameter. A tubular nozzle or viewing port 1000 pounds per square inch. Prefeiably nitrogen is intro- 
78 posit~oned within the outel end of the menlber 760 duced through the manifold assembly at pressules of 
defines an outlet from the duct assembly 70. 600-900 pounds per square inch, to maintain a pressule 
A thick transparent plotective quartz window 80 is 25 of about 600 pounds per square inch at the nozzle 78. 
positioned adjacent an outwardly extending flange 7 4 ~  In a working example of the invention, the nozzle 78 
on the inner end of the cylindrical member 74 and a sul- was nro~ided with an inner drameter of approximately 
loundlng cap 82 attached to the flange 74rt secures the one inch A viewing polt of this si7e permits the entire 
window in the position shown. Suitable seals 84 are rocket engine nozzle to be photop~aphed with the camera 
located a~ound the circumfe~ence of the window $0 and 30 positioned approximately as i~dlcated above. A q~naller 
on each axial face of the window adlacent ~ t s  outer PC- diameter p o ~ t  7'8 on the viewing duct assembly 70 would 
riphely to prevent gas leakage around the v,~lr;doa requlre less nitlogcn to prevent partl~le5 from entc~ing, 
Referring to FIG. 3, there is shown a manifold dS5en7- but it would be necessary to move the canlela ?2 further 
bly 86 including a manifold tube $8 which extellds about f ~ o ~ n  the subject to obtain the same field of vision. 
two-thirds around the circumference of the real portlon 35 With the arrangement described, it was found 
76n of the member 76. A main inlet 90 is connected to that excellent photographs of a rocket engine in opera- 
the manifold tube 88 and thlee circumferentially spaced tion can be made and thus it is possible to observe the 
tubes 92 connect the manifold tube 88 to the interior of erosion of the rocket nozzle as it occurs. Since the camera 
the duct assembly 70. unit is self-contained it can be utilized where needed 
In operation, the tripod 12 for the photographic device 40 without any engine modification. 
10 is seculely mounted to the supporting surface 14 at Wllile only a single embodiment of the invention hab 
the desired location, spnced to the rear of the rocket been illustrated and desclibed, it should be understood 
engine nozzle 18 on the axis 16, as shouln in FIG. 1.  that valious modifications will now be appalent to one 
The preferred distance between the photographic device skilled in the art. Accordingly, it is intended that all 10 and the end of the rocket engine naturally depends 45 such variations and modifications that are included with- 
on the size of the components involved and the view in the true spirit and scope of the invention be included 
desired. During one use of the device, it was placed about in the appended claims. 
7 or 8 feet from the engine and the entire throat of the What is claimed is: 
rocket engine nozzle could be observed. When in position, 1. Apparatus for protecting a photogiaphic device com- 
the upper portion 24 of the enclosure is pivoted upwardly 50 plising: 
SO that the camera 22 may be filmlp secured to the sup- means defining a strong, rugged enclosure surrounding 
port members 52 with its lens unit 72 aligned with the the device; 
window 80 and the nozzle 78. The upper portion 24 of a tubular viewing duct extending through one wall of 
the enclosure is then closed and clamped to the base the enclosure and aligned with the lens of the de- 
assembly 36. 55 vice, the duct having a protective, helmetically sealed 
To maintain the interior of the enclosure below a pre- window extending across its inner end and having 
determined maximum, such as about 100" F., water is a reduced diameter at its opposite end defining a gas 
inttoduced to the inlet 44 and the passage 43 in the base discharge nozzle; and 
assembly 36 to cool the bottom of the enclosure Cooling means foi introduclng gas under pressure into the duct 
water is similarly supplied through the inlet 62 to the 60 to be exhausted flom said gas discharge nozzle. 
passages 60 within the front, side, and top walls of the 2. The apparatus of c lam 1 wherein: 
ltpper portioii 24 of the enclosure 20 The passages 43 aarci viewlng duct includes a cylindrical portion posi- 
and 6@ are sked to handle the volumt necessary io kctp rloned in rhe wail of rlie en~losure and a f i~~s to~onicd i  
the teinpe~atures suficiently low portron extending outrvardty from the cylindrrcal 
The exhalist from the rocket engine produces exlrempiy 65 portion and terminating as the no~rle;  and 
high teniperalures, such as in excess of 2000" F, ,ind the means f o ~  tntrodu~lng high pressure gas Into the 
also plod~~ces '3 r-iprdiy rnovrnr. gas srrearn nli1c1.t tatro duct ~ncludes a manifold surror1ndln.g a poltlon of 
duces considerable f o ~ c e  on the devi~e 10 and tile tr~imd the duct arld a plurality of tubes connecting the rnanl- 
12 Also, ln ceita~n apphcatlons such as wrth solid fuel fold to the ~nteilor of the duct. 
rtckets, the exhalist is filled with a large r~irmber of 70 3 The apparatus of clarm 1 wherein the drameter of 
rapidly moviilg paiticles which n~ould damage the camela the viewing duct polt is lalge enough to enable the entile 
22 or the protect~ve window 80 if the particles contacted exhaust nozzle of a rocket englne lo be photographed 
these components Altliough tlie t p p r  rsa~t 24 of the when the camera is only a few feet downstream from the 
enclosu~e 28 is essentially sealed to the base assembly end of rocket englne nozzle. 
36, it is st111 possible that some of these particles might 75 4. The apparatus of claim 1 including means for ducting 
5 
an inert pressurized as illto the interior of the enclosure 
to rnaint2tin a, positive pressure ?herein. 
5. The apparatus of claim 1 wherein the enclosure 
includes: 
an upper portion separably connected to a base por- 
tion; 
means defining passages in the walls of the upper and 
base portions for ducting coolant to maintain the 
temperature within the enclosure below a predeter- 
mined acceptable level; 
inlet and outlet means in the walls of the enclosure for 
ducting high pressure inert gas through the enclo- 
sure to maintain a positive pressure therein; and 
means attached to the base of the enclosure for firmly 
mounting the apparatus in the high temperature, high 
velocity atmosphere in which the photographs are 
to be taken. 
6.  Apparatus for protecting a camera while taking 
photos in a high temperature atmosphere comprising: 
a rugged enclosure surrounding the camera; 
means defining passages in the walls of the enclosure 
for ducting cooling fluid therethrough to maintain 
the temperature within the enclosure below a pre- 
6 
of the base portion for mounting the enclosure in 
the desired location, 
8. A method of protecting a photographic device while 
photographing a subject in a high ten-tperaturc, high 
velocity debris filled atmosphere comprising the steps of: 
5 mounting the photograpl~ic device in a strong rugged 
cnclosure with the lens of the device aligned with a 
viewing duct provided in the wall of the enclosure, 
the duct having a protective shield across its inner 
end and having a viewing port at its outer end; l0 introducing high pressure gas into the interior of the 
duct while simultaneously exhausting gas from the 
viewing port; 
ducting coolant through the walls of the enclosure; and 
ducting inert gas into the interior of the enclosure to 
maintain a positive pressure therein. 
3. The method of claim 8 wherein sufficient gas is in- 
troduced to the duct to maintain a pressure of approxi- 
mately six hundred pounds per square inch at the viewing 
20 port and the pressure of the gas within the enclosure is 
maintained at approximately twenty-five pounds per 
square inch. 
References Cited 
determined acceptable level; 
a viewing duct in one wall of the enclosure aligned 25 
with the lens of the camera with a window extend- 
ing across the duct to protect the lens from high 
velocity debris in the surrounding atmosphere; and 
means for ducting high pressure inert gas into the 
enclosure to maintain a positive pressure therein. 30 7. The apparatus of claim 6 wherein the enclosure in- 
cludes: 
a heavy base portion; 
an upper portion with one end pivotally attached to the 
base portion to permit a camera to be easily at- 
tached to the base or removed from the base when ';' 
desired; 
means for securing the upper portion to the base pol; 
tion; and 
a rugged support member attached to the bottom side 40 
UNITED STATES PATENTS 
2,959,090 11/1960 Davies -------------- 350-63 
3,289,557 12/1966 Garcia et al. ---------- 95-11 
3,310,356 3/1967 Borberg ------------ 350-63 
3,321,265 5/1967 Clave et al. --------- 350-63 
3,370,519 2/1968 Garcia et al. --------- 95-11 
FOREIGN PATENTS 
819,523 9/1959 Great Britain. 
NOICI'ON ANSHEK, 191 itrlnr y Examiner 
R. P. GREINER, Assistant F~aminer  
U.S. CI. X.R. 
350---63; 352-242 


Apparatus and method for protecting a photographic device Patent

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