NASA-미확인 이상 현상(UAP)-D018, Gemini 4 실험 보고, 1967년

Gemini IV was the second crewed mission of the Gemini series. Astronauts James McDivitt and Edward White successfully completed the four-day flight between June 3 and June 7, 1965. The mission included the first American spacewalk. This collection of documents contains a transcription of the astronauts recounting their observations of bright particles outside the spacecraft, dated circa June 25, 1967, on pages 78-81, and page 101. 

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NASA FORM 26 APR 69 PREVIOUS EDITIONS MAY BE USED

Mission Operation Report
No. M-913-65-04
MEMORANDUM June 1, 1965
To A/Administrator
From M/Associate Administrator for Manned Space Flight
Subject: Gemini Flight Number Four (GT-4) Additional Flight Activities
Subsequent to the preparation of the GT-4 Mission Operation Report several
new procedures and items of equipment have progressed to a stage of flight
readiness. Consequently, three significant additional flight activities are
now possible and have been included in the mission. These activities are:
extra vehicular activities (EVA); extra vehicular propulsion; and demonstration
of rendezvous with the booster second stage. Additional details of these
flight plan activities are provided in the attached supplement to the basic
report.
Enclosure:
MOR No. 913-65-04
Change 1
FOR INTERNAL USE ONLY

M-913-65-04
ADDITIONAL GT-4 FLIGHT PLAN ACTIVITIES
Three additional special engineering and operational objectives are now
planned for the first four orbits of the GT-4 Mission:
1. Demonstration of extravehicular activities (EVA) using a 25 foot
umbilical. Potential future application includes crew transfer, in­
flight repair, and inspection of orbiting objects.
2. Demonstration of extravehicular maneuvering using a simple, one­
man propulsion unit. This device could be used with or without
a spacecraft tether on future missions.
3. Demonstration of rendezvous with the booster second stage. This
activity wilI provide valuable early information and maneuvering
procedures necessary to rendezvous with a target vehicle. Flashing
lights identical to those designed for the Gemini/Agena Vehicle
have been instaI led on the booster second stage for th is test.
The Flight Plan sequence involves post-launch separation from the launch
vehicle, then maneuvering to stop the spacecraft separation velocity. The
first two orbits wilI be flown with the spacecraft at distances less than one
quarter of a mile from the launch vehicle. Nighttime separation will be
sufficient to prevent the flashing lights from disturbing the pilot's visual dark
adaptation. The first orbit will be occupied with operational checks of the
spacecraft guidance, maneuvering, and environmental control systems. The
pilots will utilize the second orbit to prepare for the extravehicular activity.
This procedure involves unstowing and assembling a 25-foot umbilical, the
emergency oxygen pack, a maneuvering unit, and the cameras. Over Hawaii,
at daybreak, near the end of the second orbit, the cabin will be depressurized
and Jim McDivitt will maneuver to within close proximity of the booster. At
this point, the right hatch will be opened and Ed White will climb out and
hold on the right forward portion of the spacecraft unti I McDivitt gives him a
release command. Upon command, White wi II push off slowly and reorient
himself with the hand-held maneuvering unit to face the booster. A 35-mm still
camera (Zeiss-Contarex) mounted on the maneuvering unit will be used to photo­
graph the booster and spacecraft with various earth/sky backgrounds. After
testing his ability to maneuver in a zero gravity environment, White will
maneuver back toward the spacecraft and ingress. The total time separated
from the spacecraft will be approximately 10 minutes. He will be inside
with the cabin repressurized by the time the spacecraft posses over Ascension
Island on the start of the third orbit.
Shortly ofter passing Ascension, McDivitt wil I maneuver ahead of the booster
with 5 feet per second separation velocity. Because this maneuver places the
spacecraft in a higher altitude and longer period orbit than the booster, it will
rise above and fall behind the booster. One orbit later, the spacecraft
6/1/65 Page 1

M-913-65-04
will trail 16 miles behind the booster. At this point, a spacecraft retardation
maneuver of 13 feet per second will initiate the visual rendezvous sequence.
The spacecraft will approach the booster from behind and below. Because of
unknown variation in the atmospheric density and drag of the slowly tumbling
booster, the exact approach trajectory cannot be predicted. The flight crew
will measure elevation angles of the booster and wil I initiate rendezvous
maneuvers when the booster is approximately 45 degrees elevation angle above
the spacecraft. By observing the movement of the booster with respect to the
star background and with respect to the spacecraft inertial platform display, the
crew can determine the proper lateral maneuver to null the lateral component
of velocity thereby resulting in a spacecraft velocity vector which is directly
toward the booster. After removing the lateral velocity difference, the pilot
will apply a series of breaking maneuvers with the forward firing thrusters to
reduce the closing velocity. The flight crew will measure with onboard
instruments the total maneuvering velocity required for the rendezvous procedure.
The spacecraft should be back in close proximity of the launch vehicle over
the Northeast coast of South America at the beginning of the fifth orbit.
After the rendezvous operation is complete, the spacecraft will again separate
from the booster - this time using a maneuver which will place the Gemini
spacecraft on an orbit with a predicted lifetime of four days.
The EVA suit is the new G4C suit which replaces the G3C suit used so
successfully by the GT-3 flight crew. The G4C suit has the following new
features:
a. Helmet - incorporation of triple lens shield (visors) for visual, thermal,
impact, and micrometeorite protection.
b. Torso -
1. Change to Nomex (HT-1) 11 Linknet11 in restraint layer for increased
structure I strength.
2. Incorporation of strain relief zipper in sealing closure.
3. Incorporation of redesigned ventilation inlet and outlet fittings with
automatic locking and redundant sealing features.
4. Replace Nomex (HT-1) coverlayer with integrated thermal and
mi crometeori ty cover layer.
c. Gloves - Incorporate new design with increased mobility, abrasion
resistance and thermal protection.
d. Bio-connector - Self-alighment, pin protective design.
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M-913-65-04
Figure 1 depicts the
principal physical
differences between
the old G3C suit
and the new EVA
G4C suit. Figure
2 shows that with
one visor down on
the new G4C helmet,
there is practi caI ly
no attenutation of
Ii ght entering, whereas
Figure 3 shows that
with two of the visors
down there is a
noticeable difference
in the amount of
light that enters the
astronaut's eyes. FIG.
With the third visor
down, there would
be a similar decrease
in the amount of
I ight al lowed to enter
the helmet.
The multivarious layers
of materials used in
the EVA G4C suits
are delineated in
Figure 4. It should
G-4C
be noted that the old
OVER VISOR
G3C suit consisted
SPACE
only of the pressure
HELMET
and restraint layers
of Figure 4 with the
HT -1 nylon outer
protective layer.
The EVA spacesuit
has received the
following qualifi­
cation tests:
6/1/65 Page 3

• M-913-65-04
G-4C
OVERVISOR
SPACE
HELMET
FIG. 3
G-4C EXTRAVEHICULAR SUIT
THERMAL AND PRESSURE AND
MICROMETEOROID RESTRAINT
HH NYLON OUITR LAYERS LAYERS
~6~~ T~~~~~} ~~~;:)
USE: WEAR AND
SOLAR REFLECTANCE
COTTON CONSTANT "[AR
~Ng~~;:r~~m
OXFORD NYLOt-i
COf.JORT LAY.R
11 oz,vo 2 swu
PRCSSURE LAYER
____ NEOPRE~E COATEO NYLON
11-1·2ozvo21
r----- RESTRAINT lAVlR
UM( NH DACRON
Al.;Q HflO~
7 LAYERS ALUMINIZEO u-J 4 oz vo 21
MYLAR SEPARATED BY
7 LAYCAS UNWOVEN
DACRON SPACERS HH NYLON INNER MICROr,,'tnOROID
STOPPER LAYERS
!EACH 6. 8 OZ/YD2 WHIT[I USE: WEAR
ANO MICR0~,1£TEO ROI D PRO TE CT ION
FIG. 4
6/1/65 Page 4

M-913-65-04
a. Leakage
b. Proof pressure
c. 02 compatibility
d. Ejection envelope
e. Cold temperature
f. Rapid decompression
g. Life cycling
h. Visor testing
Should the 25-foot long tether fail in some manner, the pilot will be carrying
a chestpack that has been compatibility qualified with the G4C suit and con­
sists principally of an emergency oxygen bottle with automatic valving.
It should be emphasized that both the primary and backup flight crews have
undergone 40 minutes cabin depressurization with the hatches open at a
simulated altitude of 150,000 feet in the chambers at McDonnell, St. Louis
during which time they practiced opening and closing the hatches, taking
pictures, and other actions that will take place during EVA.
The extravehicular maneuvering will be accomplished using a zero g Integral
Propulsion (ZIP) Unit as shown in Figure 5. This device is handheld and
accomplishes propulsion by jetting oxygen out through a single forward firing
nozzle and two aft firing nozzles as selected and aimed by the operator. It
includes a camera mounted for convenient extravehicular photography.
FIG. 5
6/1/65 Page 5

Mission Operation Report
No. M-913-65-04
MEMORANDUM May 24, 1965
To A/Administrator
From M/Associate Administrator for Manned Space Flight
Subject: Gemini Flight Number Four (GT-4)
GT-4, the fourth in a series of twelve planned Gemini flights is scheduled to
be launched from Complex 19 at the John F. Kennedy Space Center on or after
3 June 1965. This wi 11 be the second manned Gemini mission and the longest
ever attempted by a two-man crew. The purpose of the mission is to further
demonstrate manned space flight for a period of four days.
The nominal launch time is 10 a.m. EDT (1400 GMT). The space vehicle is
to be launched on an azimuth of 72 degrees and the spacecraft wi 11 be inserted
into an initial orbit of 87-161 N.M. at an orbital inclination of 32.5 degrees.
The 62 revolution mission will have a duration of approximately 97 hours and 50
minutes. The primary and backup flight crews are of the "new generation, 11 being
members of the second group of astronauts. James A. McDivitt will be the
command pilot and Edward H. White, II will be the pilot. Because the duration
of the flight is one of the most significant aspects of their mission, the post-
flight activities will involve expanded medical evaluation as compared with
previous missions, including at least 24 hours aboard the recovery aircraft carrier,
the USS WASP.
After conducting various orbital maneuvers and the thirteen experiments during the
four-day mission, the spacecraft wi 11 reenter and touchdown approximately 400
miles southwest of Bermuda for a water landing and carrier retrieval.
Enclosure
MOR Noo M-913-65-04
FOR INTERNAL USE ONLY

Report No. M-913-65-04
MISSION OPERATION REPORT
GEMINI FLIGHT NUMBER FOUR
(GT-4)
OFFICE OF MANNED SPACE FLIGHT
FOR INTERNAL USE ONLY

FOREWORD
MISSION OPERATION REPORTS are published expressly for the
use of NASA General Management as required by the Administra­
tor in NASA Instruction 6-2-10 dated August 15, 1963 . The pur­
pose of these reports is to provide NASA General Management with
timely, complete and definitive information on flight mission plans
and results from launchings with Scout class or larger vehicles.
Initial reports are to be prepared and issued for each flight project
just prior to launch. Following launch, updating reports for each
mission will be issued to keep General Management currently in­
formed as provided in NASA Instruction 6-2-10.
Distribution of these reports has been specifically directed by Gen­
eral Management and they are not available for additional or general
distribution . The Office of Pub I ic Affairs pub I ishes a comprehensive
series of pre-launch and post-launch reports on NASA flight missions
which are available for general distribution.
Pub I ishec and Distributed
by
OFFICE OF PROGRAM REPORTS
OFFICE OF PROGRAMMING
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
Washington, D. C. 20546

M-913-65-04
GENERAL
Gemini Flight Number Four (GT-4) is the second
Rtndczvous guidance
& recovery system ____ _, manned orbital flight in the Gemini Program and
11 Ft the fourth flight in a series of twelve planned to
develop long-duration and rendezvous capability,
docking techniques, extra-vehicular activities,
8 Ft
and controlled reentry. The first three Gemini
flights demonstrated: orbital insertion capability;
Separation point spacecraft structural integrity; and spacecraft
Oxidizer tank systems performance and crew accommodation
•Equipment bay qualities, respectively. This GT-4 mission is
intended to further demonstrate manned space
27 Ft
flight for a period of four days, the longest
ever flown by two astronauts. The space vehicle
is depicted in Figure 1.
Stage 11 engine
thrust chamber MISSION OBJECTIVES
PRIMARY
108 Ft
10 Ft • Demonstrate and evaluate the performance of
the Gemini spacecraft systems for a period
exceeding four days.
• Evaluate the effects of prolonged exposure
to the space environment on the two-man
flight crew in preparation for missions of
Oxidizer
tank longer duration.
SECONDARY
• Demonstrate OAMS capability to perform retro fire
backup.
• Demonstrate the capability of the spacecraft and
flight crew to make significant in-plane and
out-of-plane maneuvers.
Stage I engine
g1mbal point • Conduct further evaluation of spacecraft
systems as outlined below:
1. Structure and thermo I protection
2. Environmental Control Systems (ECS)
•Equipment bay contains: 3. Crew stations
• Batteries· 4. Guidance and Control System
• Malfunction detection system IMOSI units
5. Orbital Attitude and Maneuver System
• Range safety command control system
• Programmer (OAMS)
• Three-axis reference system !TARSI
• Radio guidance system IRGSI
• Autopilot • Execute the fol Io wing experiments:
• Instrumentation and telemetry system
• D-1, Basic Object Photography
FIG.
• D-6, Surface Photography
• D-8, Radiation in Spacecraft
• D-9, Simple Navigation
• M-3, In-Flight Exercises
• M-4, In-Flight Phonocardiogram
• M-6, Bone Demineralization
• MSC-1, Electrostatic Charge
5/24/65 Page 1

M-913-65-04
• MSC-2, Proton Electron Spectrometer
• MSC-3, Tri-Axis Magnetometer
• MSC-10, Two-Color Earth's Limb Photos
• S-5, Synoptic Terrain Photography
• S-6, Synoptic Weather Photography
UNUSUAL TASKS OF THIS MISSION
One of the interesting tasks of this mission is the duration of the flight. It
will be the longest ever to be conducted by a two-man crew. Another highly
interesting item is that control of the mission for the first time wil I be from the
Mission Control Center (MCC) Houston. Some elements of the Mission Control
Center at Cape Kennedy and the GSFC computing facility will be standing by as
a backup during the launch phase. The computing facilities at GSFC will also be
used as a backup to MCC-Houston during the orbital phase. Flight controllers will
man the MCC in three shifts to give complete round-the-clock coverage of the four­
day mission.