Space Test Program

The Space Congress® Proceedings 1973 (10th) Technology Today and Tomorrow

Apr 1st, 8:00 AM

Space Test Program

Neal T. Anderson Project Officer, HQ SAMSO/Spaee Test Program, Los Angeles, CA 90009

Follow this and additional works at: https://commons.erau.edu/space-congress-proceedings

Scholarly Commons Citation Anderson, Neal T., "Space Test Program" (1973). The Space Congress® Proceedings. 4. https://commons.erau.edu/space-congress-proceedings/proceedings-1973-10th/session-6/4

This Event is brought to you for free and open access by the Conferences at Scholarly Commons. It has been accepted for inclusion in The Space Congress® Proceedings by an authorized administrator of Scholarly Commons. For more information, please contact [email protected]. SPACE TEST PROGRAM

Neal T. Anderson, Capt, USAF Project Officer HQ SAMSO/Spaee Test Program Los Angeles, CA 90009

ABSTRACT The Department of Defense Space Test Program is a certain operational payloads. The only limitation unique organization dedicated to stimulating space- on this charter is that the payloads must not be related technology by providing launch and orbital authorized their own means of spaceflight. The support for research and development payloads. Program was never intended to be a launch agency This paper delineates program management techniques, for the large space programs. past accomplishments, and current activities. The benefit to the DOD is discussed. To achieve this objective a governing philosophy was established which required the Program to: INTRODUCTION • be comprehensive in scope In large measure the military power of the United • select and support the most States depends upon the possession of space systems beneficial payloads which are products of superior technology. To maintain a superior technological base and thereby • minimize individual mission fully exploit the potential of space, a broadly costs so as to maximize the based research, development, test, and evaluation number of missions function is required. • minimize the lead-time between As the military space program matured in the mid- payload identification and 1960s, high management levels in the Department of launch Defense recognized that the timely development of technology was being hindered by the lack of an on- The management procedures which evolved early in orbit research and test capability. Basic research the Program's history are in accordance with this of the space environment was being successfully philosophy. Higher management levels have main pursued by the Air Force's Office of Aerospace tained streamlined but effective control, while the Research (OAR). But the availability of space- Program Office is allowed to exercise decentralized flight support to developmental and pre-operational and efficient management techniques. The following payloads was largely non-existent. The stimulation sections of this paper will illustrate that the of all areas of technological development depended Program is achieving its objective by operating in upon an organized capability to select high quality the manner outlined above. payloads and insure prompt spa ceflight support. The embodiment of this capability had to be a low cost, rapidly responsive, flexible program. PROGRAM MANAGEMENT In May 1965, the Director of Defense Research and Space-related Research and Development activities, Engineering authorized the establishment of the while predominantly performed in the Air Force, are Space Experiments Support Program (SESP). Tri- widely distributed throughout the DOD. To stimu service in nature, the Air Force was designated the late this broad technological base, the opportunity executive agency. Within Air Force Systems Command to participate in the Space Test Program Is offered (AFSC), a Program Office was established at the to all DOD and government agencies. Under certain Space Systems Division (now the Space and Missile circumstances industry and foreign governments may Systems Organization), Los Angeles, California. also obtain the management and technical services Originally chartered to support Advanced Develop of the Program. ment (6.3) and Engineering Development (6.10 payloads, SESP's scope was increased in 1968 to in As stated in the Introduction, the Space Test clude the Basic Research (6.1) and Exploratory Program is a DOD program for which the Air Force Development (6.2) payloads previously supported by is the executive agency. To avoid any debilita OAR. In June 1971 the program was redesignated the ting effects of potential differences between the Space Test Program, participating organizations, representatives of all payload sponsoring agencies are involved in major The objective of the Space Test Program is the time program decisions. The Army, Navy, and Air Force ly spa ceflight of DOD research, development, and are, in essence, voting members at all meetings

6-1 Include: which approve or prioritize payloads, allocate re prioritization sources, or determine schedules. A joint Army, near-term, specifies Space Test • Urgency - immediate, Navy and Air Force manual or far-term usage Program management procedures. Final authority for the payload and spaceflight plan approval rests in - operational, Defense Research and • Mission Orientation Office of the Director of subsystem development, general Engineering (ODDR&E). research The most difficult task in the overall management Important, it ization • Programmatic - essential, of the program is the selection and prior to sponsoring program's crucial to effective ad secondary of payloads. Absolutely goals vancement of technology is the launch of high qual is ity, directly beneficial payloads. The task is approved by ODDR&E prior to proposed payloads can This Master List complicated by the fact that transmittal to Hq SAMSO/DIE for detailing flight In any one of dozens of laboratories and originate planning. organizations. They can fall within any of four from basic research to engineer categories ranging With 60-70 payloads in the program at any given ing development. time, the process of approving and prioritizing a major effort. It has been and priorItization flow is payloads represents The payload submission efficiently and successfully conducted at the var Illustrated in Figure 1* Each sponsoring agency to knowledgeable etc.) is ious levels by assigning the task (i.e., Army, Navy, Air Force, ARPA, NASA, cooperative groups. Large the proposed payload individuals and small responsible for insuring that committees inundated with paperwork are spaceflight and that funding sup standing actually requires not utilized. port to build the payload is available. The spon the payloads in soring agency must then prioritize of the Master List of Accepted Pay- own Internal procedures and Upon receipt accordance with its loads, the Planning Function of the Space Test submit an Integrated list to Hq USAF, Deputy Chief Plans delineating (DCS/R&D). Program prepares Spaceflight of Staff, Research and Development performance, schedules, and costs for a variety of Within DCS/R&D, the Director of Space with the is approved, the missions. Once a Spaceflight Plan assistance of the payload sponsors combines planning, procurement, and engineer establish a Master List of Accept the detailed various lists to ing activities which follow are solely the ed Bayloads. Factors utilized in the overall

Office of the Director of Defense Research and Engineering_____ Proposed Master List of P Approved Master List, Proposed Flight Plans Approved Flight Plans

Approved Master List Hq USAF/DCS R&D Proposed Plans Director of Space Flight Approved Flight Plans

Payloads

Laboratories Centers Organizations

Figure 1 Payload Submission and Spaceflight Plan Approval Flow

6-2 responsibility of the Space Test Program Office. costs due to changes in payload requirements or Located at the Space and Missile Systems Organiza late delivery. The last feature assures that the tion (SAMSO) in Los Angeles, it is the overall DOD payload agencies adequately define their require management agency with complete authority to plan, ments. It also assures that they closely manage organize, and direct the progress of each launch. their activities. It does so by funding and procuring boosters, spacecraft, and payload integration. It also ob tains launch and orbital support as required. PAST ACCOMPLISHMENTS The Space Test Program is also the overall DOD On 29 June 1967, five months after contractual go- management agency for the assignment of payloads ahead, a Thor/Burner II lifted off from Vandenberg to secondary (excess) capability on launch vehicles AFS carrying an Army satellite and a Navy satellite. and spacecraft of other DOD programs. It is also Successful injection into a 2100 NM orbit by the the central agency for requesting secondary payload specially developed apogee insertion system marked space on NASA programs. In performing this func the completion of the first primary Space Test tion, the Program Office maintains current informa Program mission. Slightly over a month later, a tion on the secondary payload capabilities of all classified Air Force satellite was launched carry DOD and NASA programs. ing three additional payloads representing the first secondary Space Test Program mission. The Due to the large number and variety of the payloads Program 1 s complete launch history is presented in flown, the Program is not expected to manage pay- Table 1. load development. A vast increase in personnel, monetary resources, technical support, and manage In the late 1960s, the majority of the payloads ment control would be required. Each payload submitted by the various participating organiza agency is responsible for the design, fabrication, tions were self-contained satellites. T5ie Space and test of their hardware. They are required to Test Program's function was largely integrating fully fund and manage these activities without ex these diverse satellites into a composite payload. tensive Space Test Program involvement. The secondary mission being flown also involved self-contained satellites. By 1970, however, there A detailed discussion of the methods used to mini was a marked change in the type of payload being mize individual mission cost and lead-time is be submitted. The small basic research black-box and yond the scope of this paper. However, the major satellite were being replaced by the much larger, guidelines can be presented. The Program has been more complex, highly developmental payload. The successful in controlling cost and schedule by: Program's budget was sharply increased to $l6M per year to permit the procurement of spacecraft neces • utilizing previously flight-proven/ sary to support these payloads. To illustrate this flight-qualified hardware transition the payloads and capabilities of Flights P70-2, P71-2, S71-3, and P72-1 will be presented in • utilizing low-cost launch vehicle greater detail. systems FTQ-2: This flight was the last primary mission to • rigorously negotiating payload predominantly support research-related payloads. "desirements" until well defined Cannonball II was an 810 Ib, 26 inch diameter "requirements" are established sphere, built by the AF Cambridge Research Labora tory (APCRL). Together with Musketball, also built • procuring competitively (if by AFCRL, it investigated atmospheric density in appropriate) the region of 70-150 NM, Cannonball II was inte grated on the forward section of an OV1 Propulsion Such control is largely achieved in the mission Module (OV1-20) and placed into a 72 x 1064 NM planning phase. A process is used which is actu orbit. Mustketball was integrated with the forward ally the reverse of the classical approach of de structure of OV1-21 and was placed into a 75 x 483 fining requirements and then estimating costs. NM orbit. The use of two OV1 Propulsion Modules The Planning Function utilizes projections of out- permitted the insertion of payloads to three dif year funding and knowledge of the missions to be ferent orbits. Reference Figure 2* flown to determine the resources which can be allo cated to any particular mission. Extensive know The 75 x 1050 NM nominal orbit was Ideal for the ledge of spacecraft and launch vehicle capabilities investigation of high energy protons and other and costs is then used to establish the maximum particles. Batteries, telemetry equipment, thermal capabilities those resources can procure. Payload control surfaces, and a stabilization boom were "desirements" can generally be negotiated consist added to the OV1-20 Propulsion Module to 8 ent with these capabilities without degrading the days of mission, life for APCRL's Energetic Breton payload objectives. Analyzer and Particle Energy and Flux payloacls* In essence the Space Test Program controls cost The other payloads assigned to the mission all re and schedule by firmly establishing requirements quired a 400-500 NM orbit. Therefore, an and by knowing, before initiating procurement kick motor was added to the OV1-21 Propulsion activity, how much a mission will cost. Subsequent Module* After circularization the Grid Sphere Drag to contract award a small, dedicated project team payload built by the AF Avionics laboratory was assures effective management. The payload agencies separated. "Three inflatable 7 foot spheres were are liable for increases in Space Test Program 'utilized to investigate the transition point from

6-3 by these pay- free molecular to laminar flow. The Propulsion The numerous orbits of data obtained and the canister contain loads will further the understanding of atmospheric Module was then reoriented of ing the Army's Lincoln Calibration Sphere was jet composition and phenomena. The integration was placed in orbit to pro these payloads into the Agena ! s power, telemetry, tisoned. This sphere in 5 months at a vide a radar calibration target with a known signa and command systems was completed ture. cost of $139K. separation of these self-contained F72-1; Tftis flight marks the departure of the Subsequent to the utilizing the upper pay loads a stabilization boom was deployed and the Program from the practice of spun-up. Primary batteries and a stage as the spacecraft. The requirements of pre Propulsion Module the cost effective real-time telemetry system provided support to vious missions had resulted in booms, each 60 ft in modification of Burner II 's, OV1 Propulsion three other payloads. Two of the P72-1 length, were deployed from the Navy's ELF/VLF Modules, and Agena s. The requirements to investigate the propa payloads and the changing stable of launch vehicles Antenna Effects payload A separable gation characteristics of signals in this region. mitigated against this approach. Spectrometer and an Atmospheric spacecraft, as well as the upper stage, was com A Velocity Mass Figure k. Neutral Composition Payload were also supported. petitively procured. Reference pay- launched by an Atlas F booster. Integrated within the spacecraft were four The mission was Project Agency's The OV1 Propulsion Modules and all associated payloads. The Advanced Research integration functions were pro Gamma Spectrometers required a spinning spacecraft load and mission of the gamma ray vided by General Efynamics/Convair Astronautics. to permit complete measurement the total background. This method of stabilization was also Excluding payloads and data reduction, Low $5»5M. The mission was launched well suited to the Extreme UV Radiation and mission cost was built by Naval Research 13 months after contract award. Altitude Bartlcle payloads Laboratories and AFCRL respectively. Completing represents the most complex the payload complement within the spacecraft were J?21~2; This flight provided by spacecraft launched to date by the Space Test groupings of Thermal Control Coating vehicle was utilized as a the AF Materials Laboratory. Supported by one of Program. The Agena capacities ever three-axis, earth-oriented spacecraft. Control the largest tape recorder storage system, and a complex tele built into a spacecraft these payloads have pro moment gyros, a power in the first five metry system were added to support four payloads. duced a massive amount of data R."f Fig 3. AF Aero Propulsion Flexible Solar months of operation. Array and a mechanically cooled SAMSO Celestial IR integrated into the forward struc Mounted atop the spacecraft was a k ft diameter, Telescope were Radar Calibra tural rack. The 32 ft x 5 ft, sun-tracking array, 10 ft long, V50 Ib cylinder. This provided 1,5 KW of power for use by the IR Tele tion Target submitted by the Army's Advanced Particle Interactions were Ballistic Missile Defense Agency was separated scope. Ionospheric control of thoroughly investigated by an Office of Naval Re from the spacecraft while still under containing 21 different sensors. the Burner II upper stage. A reorientatlon maneu search payload separation of The fourth payload, Command and Control Interfaces, ver was required prior to spin- up and was submitted by the National Security Agency. the spacecraft. F booster. Still operating after 18 months on orbit, this The mission was launched on an Atlas a wealth of information. The The Boeing Company provided the Burner II, the mission has provided of the feasibility of large flexible arrays has been dem separable spacecraft, and the integration a complete map of celestial IB Radar Calibration Target under a 19-month contract. onstrated. Nearly payloads, was sources has been obtained. The vast quantity of The total mission cost, exclusive of data collected by the Navy's particle sensors will understanding of the ionospheric lead to improved as well as disturbances which cause communication black-outs. Hae characteristics of these missions, was realized when this payload others outlined in Table 1, should make apparent A significant bonus the Space Test measured the large solar flare which occurred last the breadth of support capabilities point in time' the spacecraft and Program can provide. Bay loads weighing 0.5 Ib, August. At that 8 bps of payloads were 5 months past their nominal life. requiring 1 W of power, and outputting data have been integrated with payloads weighing power, and Lockheed Missiles and Space Company modified the hundreds of pounds, requiring 500 W of Agena and Integrated the payloads in an 18-month outputting 256 kbps of data, dese payloads have mission costs, exclusive of been approved, prioritized, and flown based solely period. The total flexible payloads, was $17.^M. upon the benefit derived by the DOB. The but rigorous manner in which the Program plans, S71-3J This secondary mission is typical of the procures, and manages its missions has insured capabilities available to payloads incorporated on timely and cost effective support, programs. Two AFCRL 'pay- spacecraft of other DGD or in loads were Integrated into the aft rack of an The large number of flights under contract Cathode Ion Gauge was mounted on a the procurement process is a further indication Agena* The Cold of stimu boom to insure an unobstructed view forward along that the Program is satisfying its goal the velocity vector. Two instruments provided lating technological development. nadir and zenith view angles for the Nightglow Photometer.

6-4 CURRENT ACTIVITIES Radiometer will investigate the UV characteristics of the earth's horizon. Wideband Radio propaga The Space Test Program flights which are currently tion measurements will be performed by a Defense under contract or in the procurement process are Nuclear Agency payload. The Office of Naval Re outlined in Table 2* These flights are the result search will provide a Preliminary Aerosol Monitor, of intensive planning and procurement activities the forerunner of far more sophisticated instrumen during 1971 and 1972. Similar to past flights, the tation. Reference Figure 5* spacecraft and orbital transfer systems being uti lized were configured with regard to both payload To be built by North American Rockwell In a 20- requirements and cost constraints. A brief discus month period, this Integrated Spacecraft is esti sion of these current flights will serve to identi mated to cost $8.3M. Tfoe total mission cost, in fy the most recent trends in the Program and out cluding the Atlas F booster but excluding the pay- line future capabilities. loads, is $13.2M. S73-5, S73-6, 87*1-2! The Small Secondary Satellite F73-3: This flight will place a Navy navigation (S3) Project represents the development of a major Technology Satellite (NTS-1) into a 7500 NM, 1^5° secondary mission capability. Three similar satel orbit. NTS-1 represents the first mission of a lites will be launched "piggy-back"^ cooperative AF/Navy effort to develop the Defense Navigation Satellite System. The Pay load Transfer System and supporting mission integration analyses A solid rocket motor is incorporated in each of the will be provided under a 11 month contract soon to three satellites. After separation from the host be awarded. The Atlas F will be utilized as the vehicle, each satellite will spin-up, coast an booster. Reference Figure 6. appropriate period, and ignite the solid rocket motor. By varying the size of the motor, widely Ffo-1; This flight will be the first Space Test different orbits will be obtained. Program utilization of a Titan IIIC launch vehicle since 1968. Two Air Force Lincoln Experimental Including the solid rocket motor each satellite Satellites (LES 8/9) and two Navy Solar Activity weighs approximately 580 Ibs. Seventeen different and Forecasting Satellites (SQIJ*AD 11 A/B) will be research-related payloads provided by Air Force and integrated into a composite payload system. Al Navy laboratories will be supported. Seventy-one though the hardware being procured is largely different instruments and packages will be furnish structural in nature, many supporting analyses ed to the Boeing Company for integration. must be performed. This Integration effort will be performed during a 19 month contract by TRW The first satellite will be available for launch 16 Systems, Inc. Reference Figure 7* months after contract award. Including the cost associated with incorporating these satellites on LES 8/9 are experimental communication satellites the host vehicle, the total S3 Project is currently intended to demonstrate advanced communication estimated at $9-5 million. Each satellite is cost techniques. They will be placed In a synchronous ing approximately $2.7 million. altitude, 23° orbit. Bae SOIRAD 11 A/B satellites will be transferred out to a 69,000 NM orbit to S73-7: Similar to the S3 Satellites this flight insure undisturbed monitoring of solar activity. will be launched by another program. However, When separated 180 degrees In this orbit, nearly the payload is itself a self-contained satellite. continuous real-time monitoring of solar activity The hardware being procured for this mission is a will be possible. dual burn orbital transfer system. Once the ^30 * V30 NM orbit is achieved the transfer system will Tiiese flights comprise those which will be launch be despun and the ARPA Calibration Satellite sepa ed in CY 73 and CY Jk. Several CY 75 and CI 76 rated. missions are in the preliminary planning phases, However, they lack sufficient definition to be in P72-2 : Flight P72-1 marked the first use of a cluded in this paper. A launch rate of 1-2 pri completely separable satellite. Flight P72-2 rep mary missions and. 2-3 secondary missions per year resents the first use of an Integrated Spacecraft, is expected in the mid and late 1970s. Planning that is, one in which the propulsive capabilities for use of the Space Transportation System (STS) of an upper stage are incorporated in the space has been initiated but the impact of the STS upon craft. At the time this mission was being planned the Program's operations will not be established it was recognized that the full performance of a for several years. Burner II upper stage would not be utilized. Con sequently, the attendant cost and complexity were not warranted. Since the spacecraft had to have a BENEFIT TO POD rigid stabilization system for other reasons, a small solid rocket motor was added to perform the The benefits of the Space Test Program, to the BOD injection function. have been as varied as the payloads which have been flown. The area of investigation for each of The spacecraft makes maximum use of flight-proven the payloads is indicated In Tables 1 and 2* Some equipment, although the overall configuration is have been research-oriented and obtained data new. Three-axis, earth-oriented stabilization is which will not be Immediately utilized 'by existing; provided for the four payloads. The SAMSO Radio programs. However, the majority of the Program's meter-20 payload will measure the earth's back funding has been allocated to developmental or ground. An accompanying SAMSO Ultraviolet nearly operational payloads. These payloads have

6-5 in June 1967, the Program for the next generation Since its first launch either obtained design data grown in technical expertise, manage tested these systems. has steadily it of systems or actually ment capability, and funding resources. Today to plan, integrate, and launch the data obtained must also be has the capability The payloads and a wide variety of missions. Past and current considered within the much broader context of their loads from num contribu launches have supported advanced pay mission applications. Very significant Provided with adequate funding to each of the following erous DOD agencies. tions have been made support and managed consistent with existing phi missions: losophies, the Space Test Program will remain a force in the stimulation of space-related Ballistic Missile • Space Environment primary "Defense Investigation technology. ' Communications • Space Object Identification ACKNOWLEDGEMENT Geodetic Mapping • Spacecraft Subsystem in this paper represent the Development The missions discussed • Navigation cooperative efforts of numerous individuals within both the DOD and the aerospace industry. Each Orbit Prediction mission has been unique; each has had its peculiar set of problems. The success of the Space Test measure of the dedication and compe of the scope of the Space Test Program is a A further indication tence these individuals have repeatedly displayed. Program is the number of participating payload agencies. Within the major agencies listed below, payloads have been accepted and flown from more laboratories, commands, and or than 20 different ILLUSTRATIONS ganizations. Payload Submission and Spaceflight Plan Projects Agency (ARPA) Figure 1. Advanced Research Approval Flow 2. Flight P70-2 Launch Configuration (DNA) Figure Orbit Defense Nuclear Agency Figure 3- Artist's Concept of STP 71-2 In k. Flight Ff2-l Configuration on Spin Table (NSA) Figure In National Security Agency Figure 5. Artist's Concept of Flight P72-2 Orbit 1 Trans United States Air Force (USAF) Figure 6. Navigation Technology Satellite fer System United States Army (USA) Figure 7. Model of Flight FfU-l Configuration United States Navy (USN) relative to flight opportunities have Discussions how been held with NASA and the French Government; ever, no payloads have yet been flown from these agencies. A less tangible benefit to the DOD has been the manner in which the Program's governing philosophy was developed and implemented. Management of the overall Program is a different task involving many organizations. The large number of successful launches has demonstrated that direct communica tion, streamlined procedures, and a projectized approach can result in effective and responsive management of a complicated Program. These launch es have also demonstrated that by utilizing cost criteria, particularly during the mission planning phases, costs can be controlled* Without actually labeling it such, the Program has consistently used a "design to cost" approach. This combina tion of streamlined-management and cost-conscious philosophies has enabled the Program to provide broad support with modest resources. The Program is a continuing example of the success such philos ophies can achieve*

CONCLUSIONS The Space Test Program has achieved its goal of providing an on-orbit research and test capability.

6-6

Effects

Density

Communications Communications

Properties

Thermodynamics

Environment Environment

Background

Background Calibration Calibration

Background

Effects

Environment

Investigated

Orbital Orbital

Techniques

Ionospheric Ionospheric

Material Material

Geodesy

Geodesy Geodesy

Earth Earth

Advanced Advanced

Earth Earth

Atmospheric Atmospheric

Solar Solar Radar Radar Calibration

Space Space

Radar Radar

Earth Earth Earth Earth

Geodesy

Area Area

91°

90°

91° 26°

91° 91°

91°

91° 91°

90°

100°

91° (NM)

2100, 2100,

2163, 2163,

2156, 2156,

3°

400, 400,

2400, 2400,

400, 400,

400, 400, 400, 400,

194, 194,

590, 590,

19300, 19300,

400, 400,

x x x x

x x

Orbit Orbit

x x

Sync, Sync, 95 95

Sync, Sync,

400 400

600 600

85 85

400 400

2100 2100

400 400

2100 2100

400 400

590 590

102 102

2086 2086

2079 2079

- -

(LES-6) (LES-6)

OV2-5 OV2-5

OV5-2 OV5-2

SECOR)

(SECOR) (SECOR)

(SECOR)

( (

OV5-4

Measure Measure

Studies Studies

Measure-

Sat: Sat: Sat: Sat:

(RADCAT) (RADCAT)

(UVR)

Range Range Range Range

Range Range

PROGRAM PROGRAM

1 Range Range

Satellite Satellite

of of of of

Friction Friction

of of

Auroral Auroral

(LCS-3)

Transfer: Transfer:

Title

TEST TEST

Target Target

TABLE TABLE

and and

Monitoring Monitoring

Propagation Propagation

PAST LAUNCHES PAST

Heat Heat

Vacuum Vacuum

Gravitational Gravitational

Radiometer Radiometer

SPACE SPACE

RF RF

Collation Collation Collation Collation

Collation Collation

Collation Collation Payload Payload

Sphere

and and

Space Space

LIDOS

Calibration Calibration

Particle Particle

AURORA

Liquid Liquid

- -

CAL CAL

Calibration Calibration

- -

X-ray

G G

Radiation Radiation

Drag Drag

Solar Solar Barticle Sync Sync

Lincoln Experimental Experimental Lincoln Zero Zero

Orbital Orbital

Experiment

Sequential Sequential

Ionospheric Ionospheric Geodetic Geodetic

ments ments

ORBIS ORBIS

Grid Grid

Ultra-Violet Ultra-Violet Lincoln Lincoln

Radiometer Radiometer

Sequential Sequential Solar Solar

Radar Radar

Sequential Sequential

Charged Charged

Radiometer Radiometer Radiometer Radiometer

ments ments

USAF USAF

USN

USA

USN

USAF

USA

USA USA

USAF

USA

USAF

USN

USA

Agency

Bayload Bayload

II II

Agena Agena

failure)

Launch Launch

Vehicle

Fairing Fairing

failure)

Titan

Thorad/Agena

NASA/Thorad NASA/Thorad

Atlas/Burner Atlas/Burner

Ihor/Burner Ihor/Burner

68 68

Bayload Bayload

68 68

Booster Booster

68 68

67 67

Sep Sep

May May

Aug Aug

Jun Jun

Launch Launch

Date Date

7 7

26 26

16 16

29 29

P67-2 P67-2

(Unsuccessful: (Unsuccessful:

P68-1 P68-1

S68-2 S68-2 8

S67-3 S67-3

P67-1 P67-1

Number Number

Flight Flight

I o

Density

Effects

Background

Environment

Calibration, Calibration,

Calibration

Environment

Investigated

Radar Radar Calibration

Space Space

Atmospheric Atmospheric

Development Atmospheric Atmospheric

Celestial Celestial

Attitude Subsystem Subsystem Attitude

Radar Radar

Atmospheric Atmospheric

Geodesy

Space Space Radar Radar

Space Space

Ionospheric Ionospheric

Geodesy

Space Space

Area Area

33°

88°

92°

105° 92°

90°

101°

107°

71°

88°

107°

99°

(NM)

60,982, 60,982,

61,0^6, 61,0^6, 500, 500,

61,051, 61,051,

298, 298,

H7, H7,

600, 600,

505, 505,

1*83, 1*83,

605, 605,

1060, 1060,

226, 226,

3160, 3160, lOfl*, lOfl*,

319, 319,

253, 253,

x x

x x x x

x x

Orbit Orbit x x

k k

430 430

75 75

72 72

72 72 x

311 311 72 72

311 311

tel tel

575 575

1*88 1*88

9320 9320

925^ 925^

933^ 933^

580 580

100 100

25 25

25^ 25^

217 217

(SECOR)

Devices

(LCS-10

Spheres

(OV1-20)

Studies: Studies:

(OV1-20)

OV5-5

X-Ray X-Ray

s-1

(Cont.) (Cont.)

Range Range

Monitoring Monitoring

Studies Studies

Satellite Satellite

Drag Drag

PROGRAM PROGRAM

1 1

Cannonball Cannonball

and and

Sphere Sphere

and and

of of

Flux Flux

Sensing Sensing

- -

Title

and and

IAUNCHES

Cone/Cylinder

Analyzer Analyzer

TEST TEST

and and

TABLE TABLE

Detector: Detector:

Measurements Measurements

Propagation Propagation

Density Density

Particle Particle Sat. Sat.

Measurement Measurement

PAST PAST

Particle Particle

RF RF

Attitude Attitude

Payload Payload

Atmospheric Atmospheric

SPACE SPACE

OV5-9

OV5-6

Collation Collation

OV1-19

Proton Proton Wave Wave

OV1-18

IR IR

OV1-17

Energy Energy

Belt Belt

Den. Den.

Calibration Calibration

Effects Effects

and and

Tracked Tracked

Calibration Calibration

Flare Flare

Alt. Alt.

Plasma Plasma

Lincoln Lincoln

Particle Particle

Radar Radar

Musketball

Low Low Energetic Energetic

Spacecraft Spacecraft

Celestial Celestial

Radar Radar

TOPO-A

Satellite: Satellite:

Solar Flare Flare Solar

Radar Radar

Satellite: Satellite:

Solar Solar

Sequential Sequential

Ionospheric Ionospheric

VLF VLF

ORBIS-CAL ORBIS-CAL

Satellite: Satellite:

Radiation Radiation

Satellite: Satellite:

Auroral Auroral

USA

USAF

USN

USA

USN

USAF

USA

USN

USAF

USN

USAF, USAF,

USAF, USAF, USN

Payload Payload

Agency

OV1

F/Dual F/Dual

IIIC

Burner Burner

F/Tri F/Tri

Thorad/Agena

Tfcorad/Agena

Vehicle

Atlas Atlas

Thor/ Thor/

Thor/Buroer Thor/Buroer

Tfcorad/Agena

NASA NASA

Titan Titan

NASA NASA

Atlas Atlas

71 71

70 70

69 69

Aug Aug

Jun Jun

Apr Apr

May May

Apr Apr

Mar Mar

7 7

8 8

Launch Launch Launch

Date Date

8 8

16 16 Feb

30 Sep 69 69 Sep 30

Ik Ik

23 23

IT IT

FfO-2

F70-1

S70-4

S70-3

S69-

S68-3

S69-2

F69-1

Flight Flight Number

00 T

Development Development

Propagation

Hiysics Hiysics

Density Density

Hiysics Hiysics

Effects

Composition Composition

Composition

Density Density

Background Background

Properties Properties

Signal Signal

Calibration

Environment

Subsystem Subsystem

Environment Environment

Subsystem Development Development Subsystem

Investigated

Space Space

Radar Radar

Space Space

Ionospheric Ionospheric

Material Material

Comm. Comm. Power Power

Atmospheric Atmospheric

Celestial Celestial

Atmospheric Atmospheric

Atmospheric Density Atmospheric

Atmospheric Atmospheric Density

Atmospheric Atmospheric

ELF/VLF ELF/VLF

Atmospheric Atmospheric

Area Area

98°

98° Polar

Polar

93°

Polar 93°

93°

88°

(NM)

406, 406,

411, 411,

4U, 4U,

411, 411,

434, 434,

498, 498,

499, 499,

x x

Earth, Earth,

x x

Earth, Earth,

x x Earth, Earth,

Earth, Earth, x x

x x

Orbit Orbit

x x

395 395

399 399 399 399

399 399

Low Low

432 432

Low Low

432 432

426 426

Plasma

(OV1-21)

and

and and

(RADCAT)

(Cont.) (Cont.)

Altitude

Radiation

Energetic

PROGRAM PROGRAM

1 1

Low Low

Interfaces

of of

Composition

Title

17 17

Gauge

LAUNCHES

target target

Density Density

Program

TEST TEST

of of

Gauge

TABLE TABLE

Coatings

Impedance Impedance

Array

Spectrometer Spectrometer

PAST PAST

Ion Ion

Control Control

Effects Effects

Payload Payload

Drag

SBVCE SBVCE

Ionospheric Ionospheric

Density Density

Atmos. Atmos.

Hiotometer

Mapping Mapping

Spectra Spectra

Solar Solar

Mass Mass

Bayloads: Bayloads:

Flights: Flights:

of of

UV UV

(OV1-21)

and and

Calibration Calibration

Spectrometer

Interaction

of of

and and

Sphere Sphere

Particles lonization lonization

Flux Flux

Thermal Control Control Thermal

Radar Radar

Composition

Extreme Extreme

(OV1-21)

Ionospheric Ionospheric

Command Command

Cold Cold Cathode

Nightglow Nightglow

Gamma Gamma

Mapping Mapping Part. Part.

Celestial Celestial

Flexible Flexible

Velocity Velocity

Effects Effects

ELF/VLF Antenna Antenna ELF/VLF

Atmospheric Neutral Neutral Atmospheric

Grid Grid

Number Number

load

Total Total

Total Number Number Total

USA

USAF

USN

USAF

NSA

ARPA

USAF

USN

USAF

USN

USAF

Pay Pay

Agency

II II

F/Burner F/Burner

Launch Launch

Vehicle Vehicle

Itoorad/Agena Itoorad/Agena

Thorad/Agena Thorad/Agena

Atlas Atlas

Hiorad/Agena Hiorad/Agena

Oct Oct

May May

Oct Oct

Apr Apr

Launch

Date

2 2

19 19

25 25

I? I?

Continued

Secondary

Primary Primary

- -

S S

P P

P72-1 P72-1

S71-5 S71-5

S71-3 S71-3

Ffl-2 Ffl-2

FfO-2 FfO-2

Number Number Flight Flight

Composition

Density

Density Density

Density

Density Density

Density

Density Density

Techniques

Propagation

Communication Communication Calibration

Background Background

Activities

Background Background

Environment Environment Environment Environment

Investigated

Signal Signal

Solar Solar

Techniques

Atmospheric Atmospheric

Earth Earth

Advanced Advanced

RF RF

Space Space

Earth Earth

Space Space

Atmospheric Atmospheric

Navigation Navigation

Atmospheric Atmospheric

Infra-Bed Infra-Bed

Atmospheric Density Atmospheric

Atmospheric Atmospheric

125°

98° 98°

98°

98° 98°

Polar Polar

Polar

Polar Polar

Polar

Polar Polar

Polar

Polar Polar

Polar

23°

(NM)

69,000, 69,000,

x x

7500, 7500,

400, 400,

500, 500,

430, 430,

Alt, Alt,

2000, 2000,

x x

2000, 2000,

x x

Orbit Orbit

x x

69,000 69,000

23°

Sync Sync

400 400

400 x x 400

400 400

kOO kOO

130 130

130 x x 130

130 130

85 85

7500 7500

85 85

430 430

Wideband Wideband

and and

Fields

Environment

on on

Studies

UVR UVR

A/B

and and

Density Density

Environment Environment

Satellite Satellite

Satellites Satellites

Part. Part.

11 11

Monitor

Sources

Forecasting Forecasting

Gauge

Effects Effects

Atmosphere Atmosphere

Title

A/B

Satellite

PROGRAM PROGRAM

and and

20 20

Accelerometer Accelerometer

Composition Composition

SOLRAD SOLRAD

Radiometer Radiometer

ACTIVITIES

Particles Particles

Trapped Trapped

Density Density

- -

Aerosol Aerosol

Polar Polar

Variation Variation

Heating Heating

TEST TEST

Density Density

Technology Technology

Atmospheric Atmospheric

Bayload Bayload

of of

Experimental Experimental

Zone Zone

Signals

Activity Activity

CURRENT CURRENT

SPACE SPACE

Calibration Calibration

Altitude Altitude

(LES (LES 8/9)

Satellites: Satellites:

Solar Solar

Lincoln Lincoln

Preliminary Preliminary

Trans-Ionospheric Trans-Ionospheric Ultra-Violet Ultra-Violet

Radio Radio

Radiometers Radiometers

Low Low

Localized Localized

Ionosphere Variations

Auroral Auroral

Studies

(NTS-1)

Dynamics Dynamics

lonization lonization

Piezoelectric Piezoelectric

Atmospheric Atmospheric

Navigation Navigation

T&ermospheric T&ermospheric

Low Low

Atmospheric Atmospheric

ARPA ARPA

USN USN

USAF USAF

USN USN

USAF USAF

DNA DNA

USAF USAF

USAF

USAF USAF

USN

USAF

USAF USAF

ARPA

Payload Payload

Agency

IIIC

F F

Launch Launch

Vehicle

Titan Titan

Atlas Atlas

Qtr Qtr

3 3

CY CY

2 2

CY CY

2 2

1 1

CY CY

4 4

CY CY

Launch Launch

Date Date

F74-1

F72-2

S73-6

FT3-3

S73-5

S73-7

Number

Flight Flight

M M 0

Propagation

Signal Signal

Environment

Environment Environment Environment

Investigated

Space Space

Space Space Space Space

ELF/VLF ELF/VLF

Area Area

Polar

Polar BDlar

Polar Polar

(NM)

1*-750, 1*-750, 1*750, 1*750,

¥r50, ¥r50, ^750, ^750,

Vr50, Vr50,

14-750, 14-750,

1*750, 1*750,

x x

Orbit Orbit

x x

130 130 130 x x 130

130 130

130 130 130 x x 130

a a

in in

7 7

: :

Abundances

Drift

Propagation

Spectrometer

(Cont.) (Cont.)

Ion Ion

Environment

Ion Ion

Title

PROGRAM PROGRAM

2 2

- -

Flown Flown

and and

Contract: Contract:

Monitoring Monitoring

Measurements Measurements

ffeHg ffeHg

ACTIVITIES

TEST TEST

Particle Particle

TABLE TABLE

to to be

Bay load load Bay

Electron Electron

under under

Fields Fields

Field Field

Proton Proton

Antenna Antenna

Orbit

SPACE SPACE

CURRENT CURRENT

Energy Energy

Rayloads Rayloads

Flights Flights

Polar Polar

Low Low

Trapped Trapped

Electric Electric

ELF/VLF ELF/VLF Energetic Energetic

Electric Electric

Magnetosphere Magnetosphere

of of

load load

USAF

Number Number

USAF USAF

USAF

USAF USAF

USAF

Number Number

USN

Pay Pay

Agency

Launch Launch

Vehicle Vehicle

Mission

Mission Mission

Qtr Qtr

3 3

CY CY Launch Launch

Date

Primary Primary

Secondary Secondary

- -

S S

P P

5714-2 5714-2

Flight Flight Number Number ; lifi6Efc OF FLIGHT Ff%-l

6-12 NAVIGATIONTECHNOLOGY

SATELLITEI

TRANSFERSYSTEM Figure 5

ARTIST*S CONCEPTOF FLIGHT FT2-2 IN CEBIT CA&IHH&f ION, 1HRGBT

6-15

4 4

H T

CALIBRATION

LIBCOM LIBCOM SPHERE