NASA News

A. National Aeronautics and

Space Administration
Washington. D.C 20546
AC 202 755-8370

For Release:
IMMEDIATE

PRESS KIT
RELEASE NO: 75-259 Contents
PROJECT: Atmosphere

GENERAL RELEASE.......................... 1-5

MISSION DESCRIPTION ..................... 6-7

AE-D MISSION FACTS AT A GLANCE ............... 8-9

LAUNCH VEHICLE OPERATIONS ................... 10-11

MAJOR AE-D/DELTA FLIGHT EVENTS .............. 12

STRAIGHT-EIGHT DELTA FACTS AND FIGURES ........13-14

SPACECRAFT DESCRIPTION ...................... 15-16

SCIENTIFIC INSTRUMENTS ...................... 16-19

TRACKING AND DAT 2A ACQUISITION ............... 20

AE-D/DELTA TEAM .................... ....... 21-22

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 National Aeronautics and
Space Administration
Washington, D.C. 20546
AC 202 755-8370

. For Release:
Jim Kukowski
Headquarters, Washington, D.C. IMMEDIATE
(Phone: 202/755-8370)

Joe McRoberts
Goddard Space Flight Center, Greenbelt, Md.
(Phone: 301/982-4955)

RELEASE NO: 75-259

ATMOSPHERE EXPLORER SET FOR LAUNCH

NASA will launch the second in a series of three

maneuverable, unmanned spacecraft to explore in detail an

area of the Earth's outer atmosphere where importnt energy

transfer, atomic and molecular processes and chemical reac-
tions occur that are critical to the heat balance of the
atmosphere.

Atmosphere Explorer-D (Explorer- 54 in orbit) is

scheduled for launch into a polar orbit about Oct. 1 on

board a Delta rocket from the Western Test Range, Lompoc,

Calif.

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As in the AE-C or Explorer-51 mission, and another

mission scheduled fcr later this year (AE-E), the spacecraft
will be linked through a sophisticated ground computer with

scientists in widely scattered parts of the country studying

the outer atmosphere.

The area of the upper atmosphere of primary interest

is between 130 and 300 kilometers (80 to 120 miles).

The first mission, AE-C or Explorer 51, found the

weather in this region is constantly changing with winds
10
times as severe as those normally found on the Earth's
sur-
face. For example, the winds may be measured blowing from
west to east at 160 knots and a few kilometers higher they

will be coming from the opposite direction at the same speed.

The usual direction is from dayside to nightside. Prior
to
AE-C's launch in December 1973 it was believed the atmosphere
at this region, the thermosphere, behaved predictably and
was relatively stable. Now we know it is very dynamic
and
unpredictable.

AE-C was the first unmanned spacecraft able to dip in

and out of the Earth's atmosphere on a global basis to measure
the thermosphere and to give scientists an extended look
at
this region.

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Before the orbit adjustable Atmosphere Explorer, most

information on the area came from sounding rockets gathering
a few seconds of data, and other satellites slowly falling
back to Earth as their orbits decayed.

AE-D will continue the work of its predecessor, sampling

regions over both poles that AE-C couldn't reach because of

its 68 degree orbit. In fact, AE-C although successfully

accomplishing its mission last spring, will be used again to
work with AE-D in the first few weeks so that areas of interest
at different altitudes can be sampled simultaneously.

Another successful aspect of the previous mission,

real time exchange of spacecraft scientific information among

participating scientists, will be continued on AE-D and the

next one, AE-E, scheduled for launch in November from Cape
Canaveral, Fla., into an equatorial orbit.

Should a solar flare or other disturbance phenomenon

occur, a central ground computer complex at Goddard Space
Flight Center, Greenbelt, Md., will enable the 15 scientist

investigators and theorists utilizing the 12 onboard instru-

ments to coordinate their activities while the event is

actually happening.

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The scientific instruments on AE-D are almost identical

to those carried on the previous spacecraft and include a

photometer to measure nitric oxide. Nitric oxide is one of
the main constituents which control the ozone layer. These
measurements of nitric oxide, in conjunction with a direct
measurement of ozone scheduled for AE-E, will be a major step

forward in understanding the interaction of upper atmosphere

constituents with solar ultraviolet light and the resulting
impact on Earth's ozone layer.

The main energy input to the atmosphere is known to

come from the absorption of solar ultraviolet radiation; but
a significant portion comes from the solar wind (a mass of
ionized gas flowing out of the Sun) interacting with the

atmosphere in the polar regions. An immediate consequence

of this interaction can be seen in the aurorae, whose bands
of light consume more energy than is used by the entire United
States. The magnitude and variability of this high latitude
heat source, which during geomagnetic storms causes worldwide
radio blackouts, is poorly understood. An important objec-
tive of this mission is to investigate these processes and
mechanisms.

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 The spacecraft will also examine particle fluxes,
airglow intensities, plasma densities and temperatures and

magnetic fields at the low altitudes where the energy dis-

sipation occurs. These measurements will be used to assess
the heat balance and energy conversion mechanisms, as well
as the flow of heat or energy from one hemisphere to the

other,

The spacecraft design, making use of existing tech-

nology, is relatively inexpensive. Costs for all three
spacecraft are expected to total about $24 million.

The general configuration of the AE satellite is a 16-

sided polyhedron. The drum-shaped spacecraft is 135 centi-

meters (53.2 inches) in diameter and 115 cm (45 in.) high.
It weighs 675 kg (1,488 lb.) including 95 kg (210 lb.) of

instrumentation.

Overall program direction is the responsibility of NASA's

Office of Space Science, Washington, D.C., with Goddard Space
Flight Center providing the spacecraft and rocket direct
management. Launch operations have been assigned to Kennedy
Space Center's Western Test Range, Operations Division. RCA
Corp., Princeton, N.J., is the spacecraft prime contractor
and McDonnell Douglas Corp., Huntington Beach, Calif., builds

the launch vehicle.

(END OF GENERAL RELEASE. BACKGROUND INFORMATION FOLLOWS.)

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MISSION DESCRIPTION

Atmosphere Explorers C, D and E mark a new approach n

scientific spacecraft. They differ in the orbit flown, in
the team approach taken by the investigators, in the degree
of interaction between the investigators and the spacecraft
and data operations, and in the rapidity with which data must
be acquired, processed and analyzed.

The data of each investigator are available to all

investigators, and the investigators interact as a team to
contribute to operational decisions. c

These second generation Atmosphere Explorers represent

a logical continuation and extension of a basic program in
aeronomy being conducted by NASA. The first aeronomy satel-
lite, Explorer 17, was launched April 2, 1963, and another,
Explorer 32, in May 1966.

The resulting new data and concepts indicated the need

for conducting measurements during flights in a way that would
permit separating the effects of local time, latitude and
altitude.
The results of these missions demonstrated the need to
conduct satellite measurements at significantly lower alti-
tudes. In particular, it became evident that the behavior
of the upper thermosphere is strongly governed by the lower
thermosphere, because most of the solar ultraviolet energy
is absorbed at altitudes below those normally attainable by
satellites. Experimental study of the lower thermosphere
thus became a primary goal of the aeronomy program.
AE-D will be placed initially in a highly eccentric
orbit with 90 degrees i.,;i..ation, perigee near 157 km (93
mi.) and apogee of 3,800 km (2,375 mi.). At intervals of
several weeks perigee may be lowered for brief periods to
the lowest altitude consistent with spacecraft and instrument
safety.
Over a period of months the apogee will be allowed to
fall and, through the use of propulsion, a sequence of cir-
cular orbits will be established at each of several pre-
selected altitudes in the range of 250 to 700 km (150-420
mi.). This circular orbit phase of the mission will continue
until the fuel is nearly depleted, perhaps a year after launch.
In the final phase the remaining fuel may be used to place
the satellite in a stable orbit that will provide optimum
long range sampling. This final orbit will be complementary
with the orbit of the remaining AE mission.

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The AE spacecraft has an orbit-adjust

propulsion
system carrying 168 kg (370 lb.) of fuel and employing
hydrazine thrusters to provide a means of adjusting three
and apogee altitudes. Firing will be done primarily perigee
despin mode with the spacecraft in either the in the
inverted position to either increase standard or
or decrease the velocity
and, therefore, change the orbit. A backup spinning
mode will also be provided. The main thrust thrust
O will be a 1.8 kg
(3.96 lb.) flight qualified unit. Spzcecraft
errors must be small enough to allow velocity dynamics and
2.5 m (8.15 ft.) per second without increments of
altitude errors. It is expected to exceeding the space-raft
use 2.3 kg (5.06 lb.) or
propellant for each "up" or "down" excursion
using approxi-
mately six pounds of propellant for one maneuver.
considerations make the AE spacecraft capable of Design
ing aerodynamic heating effects withstand-
at a perigee
mi.) while spinning and 150 km (90 mi.) when of 120 km (72
despun.

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AE-D MISSION FACTS AT A GLANCE
:
Launch:
From Western Test
Range, Lompoc, California.
Launch Vehicle:
Two stage Delta with nine
solid fuel strap-on motors.
Nominal orbit:
Apogee: 3800 kilometers
(2,375 miles)

Perigee: 157 kilometers

(93 miles)

Period: 127 minutes

Inclination: 90 degrees
Operating Lifetime:
At least one year
Spacecraft Weight:
675 kilograms (1,488 pounds)
Structure:
Drum-shaped (16-sided poly-
hedron), 137 centimeters (53.2
inches) in diameter and 117
centimeters (45 inches) high.
Consists of two shells, inner
and outer, with solar cells,
telemetry antennas and viewing
ports on outer shell. Inner
shell holds 12 scientific
instruments and four engineer-
ing measurements (95 kilograms,
212 pounds), electronic pack-
ages, attitude control system,
hydrazine thruster subsystem.

Power System:
Solar cells on exterior of
spacecraft, redundant nickel
cadmium batteries. Provides
120 watts of power during
normal operation.
Communications and Data
Handling:
Telemetry, tracking and
command and control and
the antennas.

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Telemetry: Pulse-coded Modulation

(PCM) operating at
137.23 MHz, VHF 2289.50 MHz
S-Band
Tracking and Data
Acquisition: Stations of the Spacefliqht
Tracking and Data Network
(STDN) operatei by GSFC.

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LAUNCH VEHICLE OPERATIONS

For AE-D, a two stage Delta 2910 launch vehicle will

be used. The vehicle has an overall length of approximately
35 meters (116 feet) and a maximum body diameter of 2.48
meters (6 feet). The nominal launch weight is 130,913
kilograms (290,920 pounds), including the nine booster
thrust-augmentation solid motors.

The standard 8-foot diameter Delta fairing protects

the spacecraft from aerodynamic h-cdting during the boost
flight and, is jettisoned as soon as the vehicle leaves
the sensible atmosphere shortly after second stage igni-
tion.

Guidance

An all-inertial guidance system consisting of an

inertial sensor package and digital guidance computer
controls the vehicle and sequence of operations from
liftoff to spacecraft separation. The sensor package
provides vehicle attitude and acceleration information
to the guidance computer. The guidance computer generates
vehicle steering commands to each stage to correct tra-
jectory deviations by comparing computed position and
velocity against prestored values.

In addition, the guidance computations perform the

functions of timing and staging as well as issuing pre-
programmed command attitude rates during the open loop
and coast guidance phases.

First Stage

The first stage is a McDonnell Douglas Astronautics

Company modified Thor booster incorporating nine strap-on
Thiokol solid fuel rocket motors. The booster is powered
by a Rocketdyne RS-27 engine using liquid oxygen and
liquid hydrocarbon propellants. The main engine is
gimbal mounted to provide pitch and yaw control from lift-
off to main engine cutoff (MECO). Two liquid propellant
vernier engines provide roll control throughout first
stage operation and pitch and yaw control from DECO to
stages I-II separation.

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MAJOR AE-D/DELTA FLIGHT EVENTIS

Event Time Altitude

L Minutes/Seconds Kilometers N.Riles S.Miles
Liftoff 0:00 0 0 0
Six Solid Motors Burnout 0:38
6.0 3.2 3.7
Three Solid Motors
Ignite 0:39 6.1 3.3 3.8
Three Solid Motors
Burnout 1:18 22.2 12 13.8
Jettison Nine Motor
Casings 1:27 25.9 14 16.1
Main Engine Cutoff
(MECO) 3:50 113.0 61 70.2
Vernier Engine Cutoff
(VECO) 3:56 1210.4 65 74.8
Stage I/II Separation 3:58 122.1 66 75.9
Stage II Ignition Signal 4:02 127.8 69 79.4
Jettison Fairing 4:34 157.4 85 97.8
Stage II Cutoff (SECO) 9:09 227.7 123 141.5
Stage II/Spacecraft
Separation 12:30 161.1 87 100.1

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STRAIGHT-EIGHT DELTA FACTS AND FIGURES

Height: 35.4 meters (116 feet) including shroud

Maximum diameter: 2.4 m (8 ft.) without
attached solids
Liftoff weight: 131,959 kilograms (290,920 pounds)
Liftoff thrust: 1,725,780 newtons (387,816 pounds)
including strap-on solids

First Stage-- (liquid only) consists

of an extended long
tank Thor, produced by McDonnell Douglas.
produced by the Rocketdyne Division of The RS-27 engines,
have the following characteristics- Rockwell International,

diameter--2.4 m (8 ft.)

Height--21.3 m (70 ft.)

propellants--RF-l kerosene as the fuel
and liquid
oxygen as the oxidizer
thrust--912,000 N (205,000 lbs.)

burning time--about 3.48 minutes

weight--about 84,000 kg (185,000 lbs.)
excluding
strap-on solids
Strap-on solids consist of nine solid
propellant rockets
produced by the Thiokol Chemical Corporation,
following features: with the

diameter--0.8m (31 inches)

height--7 m (23.6 ft.)

total weight--4G,300 kg (88,650 lbs.)

for nine
4,475 kg (9,850 lbs.) each
thrust--2,083,000 N (468,000 lbs.) for
nine
231,400 N (52,000 lbs.) each
burning time--38
seconds

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Second Stage--Produced by McDonnell Douglas Astronautics

Co., utilizing a TRW TR-201 rocket engine. Major contrac-
tors for the vehicle inertial guidance system located on
the second stage are Hamilton Standard, Teledyne and Delco.
Characteristics are:

diameter--l.5 m (5 ft.) plus 2.4 m (8 ft.) attached

ring
height--6.4 m (21 ft.)

weight--6,180 kg (13,596 lbs.)

propellants--liquid, consisting of Aerozene 50 for the

fuel and Nitrogen Tetroxide (N2 04 ) for the
i oxidizer 4
thrust--about 42,923 N (9,650 lbs.)

total burning time--335 seconds

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SPACECRAFT DESCRIPTION

The Atmosphere Explorer spacecraft is 135 cm (53.2 in.)

in diameter and 115 cm (45 in.) high. The spacecraft includ-
ing experiments will weigh approximately 675 kg (1,488 lb.).
Solar cells mounted on the top and sides of the outer shells
will supply electrical power for the spacecraft and experi-
ments. Various sensors and probes will project through the
outer skin to collect data and provide spacecraft attitude
control information. The spacecraft is equipped with hydra-
zine thrusters to provide orbit adjustment capability, thus
permitting data collection over a great range of orbits.
Structural Subsystem
The spacecraft structure consists of reinforced plat-
forms for equipment mounting, an adapter section for launch
vehicle compatibility, a suitable number of reinforced hand-
ling and lifting pads, and the outer covers.

Thermal Subsystem
Aerodynamic heating as well as solar heating in both
the spin and despin modes will contribute to the spacecraft
thermal input. Active thermal control provided by a ther-
mally actuated set of louvres on the bottom of the spacecraft
that along with heat sinks, insulation and isolation will
confine the temperatures of the spacecraft internal equipment
to a range of 10 degrees C to 35 degrees C (40 degrees F. to
95 degrees F.).
Attitude Control Subsystem
The attitude control subsystem has a momentum wheel
for spinning body stabilizaion, magnetic torquers for orien-
tation and momentum control, nutation dampers for oscillation
control and attitude sensors.
Orbit Adjust Propulsion Subsystem

The orbit-adjust propulsion subsystem uses one or more

hydrazine thrusters to provide a means for adjusting perigee
and apogee altitudes.

The main thruster is a 1.8 kg (4 lb.) flight-qualified

unit. Spacecraft dynamics and alignment errors will be small
enough to allow velocity increments of 2.5 m (8.2 ft.) per
second without exceeding the spacecraft attitude errors. The
spacecraft tankage system is capable of carrying 168 kg (370
lb.) of propellant to produce a total change in velocity of
approximately 6005 (1,980 ft.) per second.
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Power Subsystem

Spacecraft power is supplied by a subsystem consisting

of a negative N-on-P solar array, redundant nickel cadmium
(NiCd) batteries and the associated power distribution unit,
chargers, power regulators and converters.

The solar array covers the top and sides of the space-
craft. The spacecraft bus voltage is 24.5 volts.
Communications and Data Handling

The communications and data-handling subsystem consist

of four distinct areas: telemetry, tracking, command and
control, and the antennas.

Telemetering of instrument and spacecraft data is

accomplished via redundant encoders, spacecraft clocks, tape
recorders and S-Band and VHF transmitters.

Tracking is via transponders and 0.25-watt beacons.

Spacecraft command and c ntrol will be accomplished by
utilizing a PCM instruction command system and omnidirectional
VHF and S-Band antennas.
Engineering Measurements System (EMS)

The EMS is a set of sensors that provides essential

engineering data for the operation and evaluation of the
spacecraft system and scientific instrumentation. Pressure
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gauges and accelerometers are required for control of orbit
adjustments and evaluation of drag performance.

SCIENTIFIC INSTRUMENTS

AE-D carries 12 scientific instruments. These will

perform simultaneous measurements of incoming solar radiation
and Earth's atmosphere to provide information on the physical
processes that govern the composition of the lower thermo-
sphere and the ionosphere, thus making possible study of the
closely interlocking cause-and-effect relationships that con-
trol Earth's near-space environment.

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Ultraviolet (Nitric Oxide) Photometer

The ultraviolet nitric oxide (UVNO) photometer will

measure the ultraviolet radiation from the upper atmosphere
to determine the distribution of nitric oxide in the Earth's
atmosphere as a function of altitude, location and time.

Investigator: C. A. Barth, University of Colorado

Cylindrical Electrostatic Probe

The cylindrical electrostatic probe (CEP) will obtain
measurem its of electron temperature and concentration re-
quired for the studies of the thermal and particle balance
of the thermosphere. In addition, the probe measurements
will be employed in conjunction with concurrent ionosphere
spacecraft in studies relating the structure and behavior of
the lower F-region to that of the upper F-region.
Investigator: Larry Brace, Goddard Space Flight Center.

Atmosphere Density Accelerometer

The atmosphere density accelerometer (MESA) will
measure the neutral density of the atmosphere in the alti-
tude range 120-400 km (75-250 mi.) by measurements of space-
craft deceleration due to aerodynamic drag. Accurate know-
ledge of the neutral density and its variations is required
for a comprehensive understanding of the processes and energy
mechanisms which control the structure and behavior of the
upper atmosphere.
Investigator: K. Champion, Air Force Cambridge
Research Laboratories

Photoelectroa Spectrometer

The photoelectron spectrometer (PES) will measure the

intensity and energy distribution of the photoelectron flux
in the thermosphere in the 2 to 100 electron volt (ev) range,
and primary electrons from 50 ev to 500 ev. It will provide
high resolution data on the photoelectron energy spectrum
and will monitor the energetic particle flux to above 100 kev.
Investigator: J. Doering, Johns Hopkins University

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Retarding Potential Analyzer

The retarding potential analyzer (RPA) will provide

accurate measurements of ion temperature, concentration
composition. In addition, the instrument will and
measure
ion drift velocity and the thermal and suprathermal the
electron
energy distributions.

Investigator: W.B. Hanson, University of Texas

at Dallas

C
Visual Airglow Photometer
The visual a4rglow photometer (VAE) will provide
detailed data on the rates of excitation of the atomic and
molecular constitutents in the thermosphere.

Measurements will be made of dayglow, aurora and night-

glow phenomena.

Investigator: P.B. Hayes, University of Michigan

Solar Extreme Ultraviolet Spectrophotometer

The solar extreme ultraviolet spectrophotometer

will measure the spectral distribution of intensity in (EUVS)
the
wavelength range extending from 1.40 to 1,850 Angstroms. The
instrument consists of 24 monochromators, 12 of which will
record intensities at certain fixed wavelengths which are
critical to studies of atmospheric structure and to an
under-
standing of mechanisms of dissipation of the input radiant
energy. Each of the remaining monochromators will scan a
limited wavelength range to give, in total, complete
of the 140 to 1,850 A region. coverage

Investigator: H.E. Hinteregger, Air Force Cambridge

Research Laboratories
Magnetic Ion Mass Spectrometer

The magnetic ion mass spectrometer (MIMS) will give

absolute concentrations of each positive ion species
ionosphere in the mass range 1 to 64 emu to achieve ain the
quanti-
tative understanding of the physical, chemical and dynamic
processes that take place in the thermosphere.

Investigator: J.H. Hoffman, University of Texas

at Dallas

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Low Energy Electron Spectrometer

The low energy electron (LEE) spectrometer will monitor

the energy input to the thermosphere from
electrons in ihe
energy range 0.2 to 25 kev, determine
the characteristics of
field aligned currents in the transauroral zone,
and whether
electric fields parellel to the magnetic field
lines exist
obtain their location and strength; and
will study the mag-
netospheric substorm precipitation with
complete electron
measurements.

Investigator: R.A. Hoffman, Goddard Space Flight Center

Open-Source Neutral Mass Spectrometer

The open-source neutral mass spectrometer (OSS) will

measure the concentrations and distributions of
gas constituents in the thermosphere. the neutral
These data are expected
to determine the instantaneous and global distributions
of neu-
tral hydrogen, heliumatomic and molecular oxygen,
nitrogen
and argon, and the total mass density above an altitude
proximately 120 km (75 mi.). In addition, of ap-
this spectrometer
will provide quantitative measurements
of trace constituents.
Investigator: A.O. Nier, University of Minnesota

iNeutral Atmosphere Composition Spectrometer

The neutral atmosphere composition spectrometer

(NACE)
uses a closed source mass spectrometer to measure
atmospheric concentrations of gases of mass 1 to the neutral
46 amu.
Investigator: A.E. Hedin, Goddard Space Flight Center

Neutral Atmosphere Temperature Spectrometer

# The neutral atmosphere temperature spectrometer

(NATE)
will provide direct measurements of the kinetic
temperature
of the neutral gas in the thermosphere, the molecular
density, and the total neutral gas density. nitrogen

Investigator: N. Spencer, Goddard Space Flight Center

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TRACKING AND DATA ACQUISITION

Tracking data will be forwarded from the ground stations

to the Goddard Center by means of ground and/or radio links.
4 I
In order to provide the ability to readjust the orbit
if too low after a firing, a tracking/compute capability will
be provided to permit verification of the new orbit within 15
minutes.
There will also be requirements for forwarding other
data to permit processing within two hours after acquisition
and for forwarding the remainder within 24 hours.
AE Operations Control Center
All telemetry data will flow through the AE Operations
Control Center where command verifications, information on
spacecraft and attitude data (for orbit and attitude verifi-
cations) will be stripped out and the remaining data trans-
mitted to the central processor.
Data Processing and Analysis Plan

In order to optimize the scientific return and achieve

maximum utilization of the variable orbit capabilities of
the AE spacecraft, an on-line central processing analysis
system is provided for performing the majority of data reduc-
tion and analysis for the investigators and theorists which
comprise the Aeronomy Team. Providing short turn-around times
(one to several days) on analysis of selected aeronomy prob-
lems will permit adaptive mission planning while the space-
craft is in approximately the same location. For example, the
Aeronomy Team may want to study a particular latitude in the
northern hemisphere at a perigee of 150 km (90 mi.) during a
highly disturbed condition for three consecutive days after
noting the condition existing during a one day low perigee
excursion. The adaptive planning will be made possible by
means of the fast turn-around analytical capability within
the central processor. The whole spacecraft may, thus, be
operated like a laboratory instrument.

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AE-D/DELTA TEAM

NASA Headquarters

Associate Administrator
Dr. Noel W. Hinners for Space Science

Director, Physics and

Dr. Alois W. Schardt
Astronomy

Frank W. Gaetano AEP Program Manager

Dr. E. R. Schmerling AE Program Scientist

Joseph B. Mahon Director, Launch Vehicle and

Propulsion Program

I. T. Gillam IV Small Launch Vehicles and

International Programs Manager

P. T. Eaton Delta Program Manager

Tracking and Data Analysis

Robert R. Stephens Program Manager

Goddard S ace Flight Center

Dr. John F. Clark Director

Dr. Robert S. Cooper Deputy Director

Robert N. Lindley Director of Projects

David W. Grimes Project Manager

Robert C. Weaver Deputy Project Manager,

Technical

John A. Underwood Deputy Project Manager, Resources

Nelson W. Spencer Project Scientist

Richard E. Donnelly Experiment Manager

David J. Haykin, Jr. Mission Operations Manager

Robert Baumann Associate Director of

Projects for Delta

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Goddard Space Flight Center (cont.)

,RobertGoss Chief, Missioni Integration and

Analysis

George D. Baker Chief, Mission Integration

A Francis A. Lawrence Mission Integration Engineer

Tecwyn Roberts Director of Networks

Albert Ferris Director of Mission and

Data Operations

Ed Lowe Network Support Manager

Roger V. Tetrick Mission Support Manager

Seaton B. Norman Communications Engineer

Kennedy Space Center

Lee R. Scherer Director

John J. Neilon Director, Unmanned Launch

Operations

Henry R. Van Goey Manager, Western Launch

Operations Division

Wilmer Thacker Chief, Delta Operations

Carl Latham Spacecraft Coordinator

Contractors

AE-D Spacecraft RCA Corporation, Astro Electronics

Division Hightstown, N.J.

Delta Launch Vehicle McDonnell Douglas Astronautics

Company Huntington Beach,
California

1 September 22, 1975

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