The Scout Launch Vehicle Program

Home , AEROS (satellite), Algol (rocket stage), Altair (rocket stage)

The Space Congress® Proceedings 1981 (18th) The Year of the Shuttle

Apr 1st, 8:00 AM

Lee R. Foster Manager, Scout Project Office, National Aeronautics & Space Adm., Langley Research Center

Richard G. Urash Program Manager - Scout, Vought Corporation

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Scholarly Commons Citation Foster, Lee R. and Urash, Richard G., "The Scout Launch Vehicle Program" (1981). The Space Congress® Proceedings. 2. https://commons.erau.edu/space-congress-proceedings/proceedings-1981-18th/session-6/2

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]. THE SCOUT LAUNCH VEHICLE PROGRAM

Mr. Lee R. Foster, Jr. Mr. Richard G. Urash Manager, Scout Project Office Program Manager - Scout National Aeronautics & Space Adm. Vought Corporation Langley Research Center P.O. Box 225907 Hampton, Virginia 23665 Dallas, Texas 75265

ABSTRACT vehicle's structure and systems so that, in The NASA/DOD Scout launch vehicle was con addition to the orbital capability, probe ceived in the 1950's by the NASA Langley and reentry missions could be flown with Research Center. Their concept was to utilize no changes other than in mission planning. solid propel!ant rockets developed by the DOD The result was a four stage all solid pro- to provide a reliable and low cost vehicle pellant launch vehicle. The technical for both scientific and applications spacecraft. soundness of the original design may be The program's history indicates both objectives demonstrated by the fact that the following have been met. In addition to emphasizing description of the current Scout G-1 con mission success and low cost, the utility of motor Scout has been enhanced over the years by a figuration, except for the rocket conservative approach to increasing both its designators, is also quite applicable to performance and usable payload volume. As the initial versions. part of a unique international cooperative effort, a third (in addition to NASA Wallops Vehicle Description Flight Center and Vandenberg Air Force Base) The Scout vehicle, shown in Fig. 1, consists Scout launch complex was activated in 1967 of four solid propulsion rockets with inter by the Italian Government off the east coast connecting structural transition sections of Kenya. Scout's current launch schedule which provide structural continuity and also shows the program continuing under NASA house components of various systems. Begin management with missions planned thru CY 1985 ning at the bottom is the Base Section A. with payloads primarily for the DOD. New This section surrounds the Algol IIIA first roles for this proven "workhorse" are being stage motor nozzle and contains the hydrau- explored by the Systems Management Contractor. lically actuated first stage control system powering vanes in the exhaust and aero History dynamic controls on the fin tips. Between the first stage and the Castor IIA powered Concept second stage is Transition Section B which contains a separation diaphragm and the The Scout launch Vehicle Program was con second stage control system, which uses ceived in 1957 by personnel at the Langley hydrogen peroxide jets to provide control Research Center of the National Aeronautics moments. Joining the second stage and the and Space Administration (NASA). Their Antares IIIA powered third stage is Transi purpose was to provide an inexpensive launch tion Section C, containing a separation vehicle for relatively small research space diaphragm and the third stage hydrogen craft. Their concept was to select from a peroxide fueled control system. Between the growing inventory of rocket motors, produced third and fourth stages is Transition Section for the Department of Defense (DOD), an D which houses the major components of the optimum "stack" with a design objective to Guidance, Ignition, Beacon, and Telemetry deliver a 45 kilogram (KG) (100 pound) pay- Systems. Mounted on the fourth stage is load to a 555 kilometer (KM) (300 nautical Transition Section E, to which the spacecraft mile (n.mi.)) circular altitude launched due is attached by means of a separation clamp, east from the NASA Wallops Flight Center, in addition to a payload separation ignition Another design objective was to configure the system and a fourth stage Telemetry System.

6-48 Surrounding the Altai r IIIA fourth stage and Wallops complex had a significant effect on spacecraft is a heatshield to protect them the design from aerodynamic of the launcher and the environ heating during ascent. Ver mental protection for the assembled vehicle satility in trajectory design and implementa in the tion is development for the Vandenberg site. provided thru the use of an Intervalo- Assembly methods for ease in handling re meter and a Programmer which are pre-set for sulted specific missions. in the horizontal assembly of the At the pre-calculated vehicle on a transporter as opposed to verti time, the Intervalometer switches selected cal voltage assembly on the launcher at Wallops. levels from the Programmer to the Vehicle processing on the launcher in an Pitch Gyro torquer, causing the gyro to environmentally controlled shelter, with generate an error signal subsequently nulled vertical erection as a complete assembly, out by rotation of the vehicle due to the resulted in a considerably more efficient action of the control system. Thus the and reliable operation. This configuration, vehicle is guided in the pitch plane while (Fig. 3), subsequently became the standard stabilized about all three axes. The fourth for all Scout launch sites. ttage is not controlled by the guidance system but is spin stabilized during that portion of Activation of the VAFB complex brought about the flight. Total length of the vehicle is even greater DOD participation in the program. 23 meters (M) (75 feet) and its weight is In addition to the U.S. Navy's Strategic 21,600 KG (47,500 pounds). Services Project Office Navigation Satellites, a number of USAF satellites - both operational Organization and First Launch and research - were launched. All of these early VAFB launches were conducted - from The NASA Langley Scout Project Office (SPO) receiving inspection of transition sections was created in 1958 to convert the concept to and rocket motors to manning the Blockhouse reality and in so doing, performed the role for the Countdown - by highly skilled officers of systems management to insure proper inte and men of the USAF 6595th ATW at VAFB. Many gration of all the activities and designs of of these men had previous experience on Scout the many contractors involved. When the pro at Cape Canaveral with the 6555th ATW. The gram was approaching the Operational Phase, USAF Launch Crew was augmented by a small the role of systems management was turned group of NASA and Vought personnel to provide over to the Vought Corporation in 1960, per liaison with their home organizations and mitting NASA to concentrate once again on their with the Vought Launch Crew at Wallops. prime mission of research. Vought, under the management of the NASA/SPO, has performed this Operational Phase task since that time. Scout, like all of the pioneering launch The first launch, whose liftoff is shown in vehicles and missile systems, suffered a Fig. 2, was conducted at NASA Wallops on number of disappointments during the early July 1, 1960. In the next two years, it was '60's, but the program - Government and followed by another eight Development launches, Industry - persevered. With meticulous also from Wallops, the only launch sitel/or ground testing, the institution of rigid the NASA Scout at the time. Simultaneously, requirements and quality and configuration the Air Force was launching the same number of controls and the following of very specific a slightly different configuration from a operational procedures, the vehicle's mobile launcher at Cape Canaveral. reliability was improved to the level which has been maintained over the years. During the Development Phase, the shared need for the inexpensive vehicle prompted both the The launch of Explorer XIX, an air density NASA and the DOD to form a combined Government experiment, on 19 December 1963, marked the management structure for the program, to main entrance of Scout into the Nation's stable tain the Scout capability and to satisfy the of Operational Launch Vehicles. Todate in requirements of both agencies. This manage the Operational Phase, 78 vehicles have been ment structure, defined in a formal Memorandum launched and have established a mission of Agreement, was identified at the NASA/DOD success record of 95%. Within this record, Scout Coordination Committee. It remains to shown in Fig. 4, is included 37 consecutive this date the single Government entity respon successful launches. While all the members sible for Scout Program activities. of the Government and Industry team that contributed to these launches are rightfully Vandenberg Air Force Base (VAFB) Launch Site proud of their record, the real pride of the program stems not so much from successful Requirements of both NASA and DOD for polar vehicle launches but from the accomplishments launches resulted in the establishment of a of so many and so varied a spectrum of Scout launch site at VAFB in early 1962. The successful missions. operational experience from the original NASA

6-49 Missions and Accomplishments Some of Scout's missions have produced dis coupled with a Papal blessing bestowed on the coveries of phenomena hither to unsuspected, program - has resulted in a 100% mission such as the finding of new x-ray sources, success ratio with a series of eight missions quasars, and the first "black hole" in space having been conducted with Italian, United by the Small Astronomy Satellite series. The Kingdom, and American spacecraft. U.S. Navy-'s Transit satellites, which are used primarily to provide accurate navigation infor Capabilities mation to the Fleet are, since 1967, also used by an estimated 6,000 commercial enterprises Pay!oad Weight and foreign countries for navigational assis tance. In addition, they are currently in use Since the beginning of the program there has to provide accurate location information for been steady improvement in the Scout vehicle off-shore oil exploration as a requisite prior as the needs of the users warranted. And to drilling. Some of our early missions in from the beginning, the need for more refined volved research into the problems associated measurements, more detailed investigations, with the safety of manned flight into space, additional experiments and, finally, direct investigating phenomena and evaluating applications has led to heavier and larger materials for such subjects as micrometeoroid volume spacecraft and the subsequent demand density and protection, and the effects of for increased performance from the launch reentry heating on various materials. The vehicles. A history of the increase in per output of thesemissions contributed to the formance capability of Scout is illustrated successful Mercury, Gemini, and Apollo pro by the fact that the pay!oad weight for a grams. Many other Scout missions dealt with 555 KM (300 n.mi.) orbit from Wallops has pure research of outer space phenomena, one been increased from 59 KG (131 pounds) for established test confirmation of Einstein's the Development vehicle to the present Scout Gravitational and Relativity Theories. More G-l capability of 218 KG (481 pounds) with recent missions investigated the effects of a 0.86 M (34 inch) diameter heatshield. This aerosol contamination of the Earth's atmosphere is 3.7 times the original capability and an and mapped the Earth's magnetic field. This increase of over 265 percent. The method later mission, called MAGSAT, is expected to used to achieve increased performance has produce major payoffs in assisting geologists been primarily to take advantage of improve in their search for natural resources. Fig. 5 ments in the state-of-the-art of solid is a brief tabulation of some of the contribu propulsion technology to upgrade the output tions of Scout launched spacecraft. of individual stage rocket motors. Fig. 10 shows this sequential performance growth In addition to NASA and DOD missions, Scout along with the gains achieved. In every case, has had 22 cooperative or reimbursable missions the impact of the rocket motor change on the with foreign spacecraft. Participants have vehicle structure and systems was, by design, included France, Germany, Italy, the-Netherlands, held to an absolute minimum. This approach the United Kingdom, and the European Space kept the risks to the minimum associated Research Organization; the total spectrum of strictly with the improvement, thereby insur Scout users is shown in Fig. 6. ing no changes to other flight proven systems. It also assured minimum impact on the cost of San Marco the vehicle. In no case was a performance improvement step undertaken purely for the Another aspect of the Scout Program that empha sake of improvement. It happened only when sizes its international flavor is the Scout missions required greater performance than San Marco launch complex near the equator off was then available, or when economic consi the coast of Kenya. The Italian Centro Ricerche derations dictated resourcing the fabrication Aerospaziali (CRA) of the University of Rome of a particular stage rocket motor. This is had the bold concept of placing Scout launch not to say, however, that when greater per and range facilities on two mobile platforms, formance was required our approach could be shown in Fig's. 7 & 8, off the Kenya coast in characterized as timid. An example of this Ngwana Bay. This concept, in a cooperative is our latest third stage motor, the Antares program between the U.S. and Italy, was brought IIIA, which features a high solids content to fruition on 26 April 1967. This successful HTPB, a Kevlar case, and a carbon/carbon launch of the Italian's atmospheric physics throat insert. spacecraft, San Marco B, shown at liftoff in Fig. 9, demonstrated the soundness of this This extensive upgrading of Scout was not concept. This program is aptly named since accomplished at the expense of economy. On Saint Mark is the patron saint of "risky the contrary, a rigorous cost control pro ventures"; however, the superb effort of the gram has been followed, the success of which Italian and American personnel involved - is demonstrated by a comparison of both

6-50 performance and vehicle cost from 1960 thru the The G-l, from VAFB with a 270 KG (595 pound) program's last lot of vehicles fabricated in payload, with 1980. Fig. 11 shows two stages fired on ascent and that performance has the remaining two fired subsequent to apogee increased 267% while the vehicle cost has can achieve the following: increased only 48%. This cost increase - averaging only 2.4%/year - compares with the Reentry Value Cost of Living growth in the same time period at of 196%. Trajectory Parameter Fourth Stage Burnout Range 1,200 KM 7,775 KM Orbital Inclinations Altitude 91 KM 122 KM Relative Velocity 5.4 KM/Sec 6.9 KM/Sec The original NASA Wallops Launch site, due to Flight Path Angle -20° -20° its inherant range safety launch azimuth limits, is used to provide orbital inclinations only Probe between 37.7° and 51.5°. The second Scout launch site, VAFB, is used for Polar and Sun From NASA Wallops, the G-l probe capability Synchronous orbits and has a range of attain is identified below: able inclinations between 75.5° and 146°. The third site, San Marco, is attractive for near- Payload Weight Time at Zero "g 1 Equatorial orbits and its inclination range is between 2.9° and 38.5°. These sites are de 91 KG 14,631 KM 4.38 hours picted in Fig. 12. 181 KG 3,111 KM 1.93 hours Scout is quite unique in this regard since, Payload Volume with its three launch sites, any orbital incli nation is attainable by direct injection, As the need for greater weight carrying capa except for bands between 51.5° and 75.5° and bility grew, so did the need for greater between 0° and 2.9 . Even this can be overcome, usable volume under the heatshield grow. In since the vehicle - with no additional hard fact, it grew at a larger rate than did the ware - can be maneuvered in the yaw plane and performance need. Usable Volume, as dis by so "dog legging" the trajectory, the in cussed here, means that volume which the clination band limitations for direct injection spacecraft can take up under the heatshield may, and have been, penetrated. with adequate clearances allowed between it and the vehicle structure and systems to This flexibility in providing such a wide account for the dynamics of flight. range of inclinations, shown in Fig. 13 in earth coverage, coupled with the ability to The Scout heatshield has been enlarged signi fly orbits, probes, and reentry missions ficantly since the original 0.54 M (21 inch) emphasize the versatility of the program. This diameter configuration with 0.14 cubic meters versatility is summarized in Fig. 14. No other (5 cubic feet) of Usable Volume. Two differ launch vehicle offers this coverage. ent length versions of a 0.86 M (34 inch) diameter heatshield provide Usable Volumes Current Scout Capability of 0.48 cubic meters (17 cubic feet) and 0.68 cubic meters (24 cubic feet). The Orbital 1.07 M (42 inch) diameter heatshield contains 0.99 cubic meters (35 cubic feet) and is Today's G-l configuration, equipped with a 42 currently the most popular. Growth of Usable inch diameter heatshield, can place the follow Volume, from 0.14 to 0.99 cubic meters, is a ing weights into a 555 KM (300 n.mi) circular 600% increase or about 2,5 times the perfor orbit with the inclination noted: mance increase. a. From NASA Wallops - 208 KG (458 pounds) Mission Integration Time Spans at 38° inclination. For a "typical" mission it takes about 24 b. From VAFB - 167 KG (367 pounds) at months from its time of assignment to the 90° inclination. Scout vehicle to launch. Invariably, it is c. From San Marco - 221 KG (486 pounds) tfte development, design, and testing of the at 2.9° inclination. spacecraft that is the pacing factor. On occasion, an existing experiment or sensor Parametric performance for the G-l configura package can be synergetically matched to an tion from all three Scout launch sites is existing spacecraft "bus" and the whole contained in the appendices. integration cycle reduced to a very short time. Such an example is the USAF/STP P76-5 Reentry Mission which from concept to launch required only 9 months. On other occasions, other

6-51 programs knowing they will be assigned to Scout, Larger Heatshields begin their integration activities as much as 36 months before launch. The need for greater Usable Volume within the heatshield envelope continues to be in demand. Within the 24 months for a "typical" mission, This fact was emphasized by the response in is a requirement for the flight spacecraft Europe to the San Marco Scout configuration to be at the launch site about 25 working wherein several potential users expressed a days prior to launch in order to be dynami strong desire to have a larger heatshield cally balanced with Scout's fourth stage and to complement the performance gain. The to undergo compatibility checks with the major problem associated with increasing vehicle at the launch pad. The actual count heatshield diameter is dynamic and static down for launch takes approximately 7 hours. stability. However, studies for the San Marco Scout have shown that volumes up to One unique feature about Scout in this area, 3.7 cubic meters (130 cubic feet) are attain is the agreement with the U.S. Navy to provide able without change in vehicle design. Exist for a Transit (Navigation Satellite) launch ing 0.86 and 1.07 M (34 and 42 inch) heat- within 30 days of their "call up". To do this, shields used with the G-l configuration of a completely checked out vehicle has been Scout can be modified to yield an increase preassigned - as has a Transit spacecraft - of 25% in Usable Volume without any vehicle and is in ready storage, prepared for immediate structural redesign. Some of these growth shipment to VAFB at a moments notice. Work configurations are shown in the appendices. begins immediately upon receipt of the "call", and within 30 calendar days the vehicle and Individual Rocket Motors spacecraft is launched on its mission. Since our present performance resulted from Recent Studies of Improved Capabilities improvements in individual stage motors, some are naturally closer to today's propul San Marco Scout sion state-of-the-art than the others. The design vintage of the current "stack" ranges Recently, a feasibility study for the Italian from 2 to 16 years old. Recent inputs from CRA to investigate the use of an advanced motor manufacturers indicate current poten configuration of Scout as the launch vehicle tial performance gains of 8 to 10% for the for a series of proposed Italian communication Algol IIIA first stage and 6 to 8% for the satellites was completed. Altair IIIA fourth stage. If implemented, both of these improvements could increase our The selected configuration consists of the current 555 KM (300 n.mi) circular performance basic four stage 6-1 configuration with the at 38° from 208 to 237 KG (458 to 522 addition of a "zero" stage of four additional pounds). Algol IIIA motors "strapped-on", i.e., a five stage vehicle. This is depicted in Fig. 15. Current Plans The feasibility study covered the stability and At this time, there are 16 Scout launch control aspects of the configuration, both vehicles in the inventory. Missions have vehicle and launcher structural loads, mods been assigned to 15 of these vehicles, and required to the major structural GSE, vehicle the 16th is being held as a back up vehicle assembly and checkout flow. Thermal analyses for the Navy's Navigational Satellite pro due to the strap-ons on both the vehicle and gram. All of these 15 missions will be launcher, separation analyses of the strap-ons, conducted between this year and 1985 as shock shown in Fig. 16. Included are two Italian evaluation of the induced vibration and in environments, and a reliability assessment spacecraft, SM-DL and SM-DM, for launch were also covered. '82 and '83, respectively, from the San Marco site. These are both NASA/Italian The results of the study indicate the con cooperative missions whose common objective figuration is quite feasible and, with minimum is the study of relationships between solar change to the basic vehicle* results in a activity and meteorological phenomena. One significant performance improvement. of the spacecraft, DL, will be investigating these relationships in the troposphere and The resultant five stage vehicle has a capa the other in the lower altitude thermosphere. bility of placing a 340 KG (750 pound) These two scientific missions are the last payload into a 1296 KM (700 n.mi.) circular scheduled NASA launches. All of the others . orbit at a 2,9° inclination. It can also be are DOD missions. used as a four stage configuration by deleting the Altair IIIA upper stage motor and in this Despite the fact that current plans show the case performance is 590 KG (1300 pounds) at Program conducting launches well into the STS 555 KM' (300 n.mi.) circular at 2,9°, operational period at ETR and the early WTR.

6-52 days, the NASA has agreed to continue its overall management of the Program through 1985. Government management will be through the traditional NASA/SPO and NASA/HQ channels working in conjunction with the NASA/DOD Scout Coordination Committee. Systems management of the program will continue to be performed by Vought. Future Plans With the last scheduled NASA launch in 1983, Scout will be nearing the end of its tradi tional role and when the last Navy navigation satellite is launched, its role will have been fulfilled. The role has been one of a very versatile launch vehicle for a wide range of uses in terms of both mission types and users. However, despite the fact that Scout's utility to the NASA is coming to an end, some of its •Inherant features may make it quite attractive to other agencies that have a need for a dedicated launch vehicle. These features include such things as its low cost, its demonstrated reliability and its capability of long storage and short time to launch. This potential of working with a dedicated program is being pursued by the Systems Management Contractor. Those of us who have spent a large portion of our professional and personal lives on Scout - the Program will be 25 years old in 1985 - are hopeful that a new, dedicated role will be estab- 11 shed, and that Scout can continue its service to the United States.

6-63

P1-623-t2

Hydraulic Hydraulic

Separation Separation

Spin-Up Spin-Up

Spin Spin

Separation Separation

Tip Tip

Separation 2nd 2nd

Diaphragm

Separation Separation

Diaphragm

Jet Jet

Telemetry Telemetry

Major Major

Guidance

Controls

Attitude

Control

Controls

Attitudi

Control

Bearings

System

Motors

Stage

Vanes

Fins

Payload Payload

Clamp

Transition Transition

Scout Scout

Section Section

Assemblies

"A" "A"

"B" "B"

"E"

"D"

1st 1st

2nd 2nd 4th 4th

3rd 3rd

Stage

-First -First

-Third -Third

Stage Stage

Motor

Heatshield

Stage

Motor

Second

Stage Stage

Motor

Stage

Motor

Fourth VOLJGHT 1 First 1 J

3/3

0.95

VOUGHT

1/1 1/1

3/3

2/3

Record

6/6

1/1

Successes

5/5

Launches

7/7

4/4

Figure

Consecutive

Phase Launch

2/2

Operational

7/7

«————————————————————^

•78

7/9

HH^M

9/9

5/5

Operational

10/11

1/1

[1963|1964|1965|1966|1967|1968|1969|1970|1971|1972|1973|1974{1975|1976|1977|1978[1979]

1.0-1 0.8- 0.4- 0.6- 1.0-•

0.8- 0.6- 0.4- 0.2-

0.2-

P1-623-11

Launch Ratio Operational

Success/ Ratio

Operational Success

Average) (Running

Sensing

VOUC5HT

Mission

and and

Experiments

Satellite

Mapping Mapping

Atmospheric Atmospheric

Aerosol Aerosol

Otolith

Field Field

Probes

Kingdom)

and and

Field Field

Frog Frog

Force

Series

Radiation

Missions

Materials

Capacity Capacity

Air Air

Series

Experiment

Fields Fields

(United (United

Contributions

Hawkeye

Magnetic Magnetic

U.S. U.S.

Gravitational Gravitational

Solar Solar

OV3-5

Ionosphere Ionosphere

Heat Heat

BE-B

Gas Gas

P76-5

Stratospheric Stratospheric

TRANSAT

RFD RFD

Reentry Reentry

SERT-1

OV3-6

OV3-4

X-4 X-4

Orbiting Orbiting

- -

Special Special

- -

Earth Earth

- -

Biology

- -

Reentry Reentry

- -

Spacecraft Spacecraft Technology

- -

Figure Figure

Series

Range Range

Spacecraft Spacecraft

Satellite

Space Space

Satellite

of of

(Italy)

Kingdom)

Series

Satellite Satellite

Measurements Measurements

Satellite Satellite

Research

Series

Scout Scout

Netherland Netherland

(Germany)

(European (European

Applications Applications

Correlation Correlation

Technology Technology

(United (United

Attenuation Attenuation

Organization)

Series

(France)

Density

Explorer Explorer

Environment

SECOR-5)

Series Series

Scientific Scientific

Series Series

Astronomy Astronomy

Air Air

(France)

Marco Marco Series

Series Series

Meteoroid Meteoroid

Satellite Satellite

P1-623-8

Micrometeoroid Micrometeoroid

Beacon Beacon

Satellite Satellite

(Army (Army

Sequential Sequential

Dual Dual

Measurement Measurement

Cooperative Cooperative

FR-1 FR-1

Aeros Aeros

San San

Radiation Radiation

ESRO-4

Small Small

Research Research

ESRO ESRO

UK UK

Small Small

Astronomical Astronomical

- -

Meteroid Meteroid

- -

Geodesy

Meteorology

- -

Communications Communications

- -

Astronomy s VOUSHT

4 1

101

Administration

Users

Figure

Space

and

Scout

Force

______

Commission

Navy

Air

Aeronautics

Energy

States

States Army

States

Kingdom

(ESA)

National

United

ESRO France

Atomic Italy Netherlands Germany United

Total

P1-623-9

o o

9 CO

6-62 221

167

208

193

203

198

185 148 156

IIIA

Equatorial

221

Inclined

208

VOUGHT

Antares

IIIA

Altair

/\]

Altair

151

116

143

555

IIA

IIIA

122

Antares

Altair

103

Figure

Alatir

IIA

Altair

Growth

Castor IIA

Castor

Altair

Orbit

Altair

Antares

45 Antares

IIA

Altair

Antares

IIIA

Growth

IIIA

Polar

Equatorial

Antares

Capability

Castor

Antares

)astor

Algol

Castor

Algol

Vehicle

IIA

Castor

Algol

Kilograms—Payload

Kilograms—Pavload Easterly

Kilograms—Payload

555-Kilometer Circular

Scout

PI-623.13

F-1

x-1

D-1

B-1

G-1

A-1

X-4

X-3

X-2

1974

1972 1965 1979

1965

1960

1964

1963

1962 80

VOUGHT

78 79

75 76

Growth

Year

Figure

Performance

Calendar

Vehicle Living and

65 66

Cost

Performance Cost of

Cost Comparison

—

CD •

300-

225- 275-

250- 175- 200- 150-

125-

V3 CO O

P1-623-7 80

VOUGHT

Equatorial

Orbits

Easterly

Inclined

Orbits

Sites

Longitude-(degrees)

Figure

Island

Wallops

120

Polar

Orbits

Launch

160

VandenbergJ

200

40 40

Latitude

(degrees)

P1.823-8 VOUC3HT

Marco

San

Figure

Limit

Coverage

Leg

Range Dog

Earth

P1-623-5

i VOUGHT

101

Versatility

Figure

Site

Marco

Scout

Reentry Probe

Orbitai

NASA European DOD

VAFB San

Wallops

Launch

Types

Customer

Pi-623.4

VOUGHT

Scout

Marco Marco

San San

15 15 Figure Figure 1985

VOUGHT

Navy

1984

Navy

AF-4

AF-5

Navy

Schedule

1983

Figure

AF-1

AF-2

AF-3

SM-DM

Launch

1982

Scout

Navy

SM-DL

1981

NOVA-I

NOVA-II

P1-623-1

§ APPENDICES

6-70 fps)

nmi)

"g"

nmi)

hr hr

(66

Zero

(4,198

(22,639

-20'

1.93

4.38

122

kmps

Burnout

Time

7,775

6.9

Inclination

4th-Stage

fps)

nmi)

38 90

nmi)

2.9°

(49

Capability

(648

(17,717

(7,900

Value (1,680

Ib)

~20<

km km

Apogee

(367

(458

(486

G-1

Payload

kg 5.4kmps

1,200

3,111

14,631

Ib)

167

208

22^

(595

Circular

Scout

270

Ib) Ib)

Wallops

Angle

Weight

Marco

(200 (400

Velocity

Path

NASA

San NASA VAFB

VAFB

555-Kilometer

Payload

181

From

From From

Flight From Range Relative

From

Altitude

•

• • Reentry

Orbital • • Probe

P1-623-10

0 0

Length Length in in Meters VOUGHT

Motor

1.42

Stage

Stage M

4th

3rd

1.32

1.42

Configurations

Heatshield

Growth

7-1

CO CD

O) c

•*—*

-C

P1-623-3

VOUGHT

800 800 850

«SO «SO

__ __

100. 100.

MCtOHT-KILOMMI

ISO ISO

100

SO 1000000 VOUGHT

£90

±00

tfeiOHT-KlLOORAtl

150

PflYLOW

100

9 vj en 3300*111

6-76 6-77