Secret
and Technical Intelligence Report
Free-World Sounding Rockets, Ballistic Missiles, and Satellite Launch Vehicles
ig
SECRET
Scienlific and Technical Intelligence Report
FREE-WORLD SOUNDING ROCKETS, BALLISTIC MISSILES, AND SATELLITE LAUNCH VEHICLES
9
CENTRAL INTELLIGENCE AGENCY DIRECTORATE OF SCIENCE AND TECHNOLOGY FOREIGNNDANALYSIS CENTER
SCd?=T
SECRET
PREFACE
This handbookn it single document, (he technicalflight test tiUtory, and performance capabilities ol the principal ballistic missile and span- rocket systems that have been developed outside the US. the USSR, end Communist China. Thepresented include sounding rockets used primarily for space research, special military test vehicles, satellite and other spacesystems, and ballistic missiles. Dnigtu in these categories are included if ihev were capected to reach the night-test stage before tbe end
The basic criterion for inclusion of particular systems within the above categoriesange (ot attitude capabilityseful pay load)auticalSeveralnot listed in the Handbook arc conducting scientific rocket firings, including Brazil. India, Norway, Pakistan, and Spain. In these cases the rockets being fired arc US or French lockots, or if of native design, are well below Ihe criteria listed above.
Much of the data in this lianclbook comes from unclassified sources, but all available inforrnaiion has been used. Tlie cutoff date for research
se&ret
JERICHO) SHORT-RANGE BALLISTIC MISSILE
Tlie French/ Israeli short-rangeobile system based on two tandem solid-propellant Topaz motors. The Topaz was tbe second composite propellant motor* developed by the French and was the first to be guided by an autopilot controlling four gimbaled nozzles. The motor case is constructed of stceL and the composite propellant consists of ammonium perchlorate oxidizer and aluminum and polyurethartesame constituents used in at least some of the IHBM motors.
The first stage is very similar to theopaz motor but with the thrust termination devices omitted. The secOnd-slagc motor differs somewhat from the first stage. The four rotating nozzles, which protrude beyond the motor case, have been replacedingle fixed nozzle. Control of second stage is achieved by aerodynamic fins. The thrust termination ports have been retained on tbe second stage to reduce the range.
The missile probably uses an inertial guidance system, somewhat similar to that used in die French silo-launched missile. This could resultEP as small aseetangeautical miles.issile with this short range, however, an autopilot could be developed toEP of perhaps between one and two nautical miles.
Reportedly, at one time the Mirage IV nuclear weapon was to be modified for installation on thehich probablyeentry vehicle weight ofounds. Use of the Mirage IV weapon now seems unlikely, and it appears thatuclear device is developed by the Israelis, it williameter of aboutnchesighter reentry veluelc weight.eapon could be installedeentry vehicleength of about five feet ifwereafer section containing flaps is attached to the rear of the reentry vehicle in order to stabilize the BV on reentering the atmosphere. Because of the missiles short range the reentry vehicle design is not expected to present any significant difficulties.
Two modes of deployment are being considered by the Israelis. Oneissile-undcr-mountain concept (MUM) where the missiles would be cmplaced in tunnels in the side of hills and mountains and rolled out and erected to he fired. The second mode willemitrailer transporter-erector-launcher (TEL) towedheeled tractor which also is the launch control center. Its total length is reported to be abouteet and itseet. Each missile unit will consist of four of these TEL's each carrying one missile. Three additional missiles for each TEL will be carried on tractor-trailers, one to each vehicle,otal ofissiles per launching unit. Reload and relaunching time is about one hour; thus, four missiles can be fired from each TEL in
" Th* first compotrte motor developed was the Agate) which wm on guided. Ilomposite propellant consulting of polyurethaoe andammonium perchlorate but Km no aluminum.
SECaRFT
se^et
about three hours. The missile is erectedydraulic control system mounted on the trailer. The missile will be enclosed in an environmental cover which is removed before firing. The countdown will normally require abouteconds. The time to fireoad march condition is unknown.
The flight test program for theegan early5 at the HeMissile Test Range. Very little information on flight tests has beenhut the program probably has been completed.
The system probably wiO be produced in Israel with some of the components purchased from France.
CHARACTERISTICS OF THERBM (values are approximate)
DEVELOPING ORGANIZATIONAvions Marcel Dassault CONFIGURATIONTwo-stage tandem
MAXIMUM BASIC OPERATIONAL RANGE0) TOTAL LENGTHft
REENTRY VEHICLE LENGTHft
GROSS WEIGHT AT0)
GUIDANCE SYSTEMProbably mertial
ACCURACYoftm range
DEPLOYMENT(TEL)
INITIAL OPERATIONAL CAPABILITYStage
stack
'hop hx.-tkk*
Topax)
(ft)
5
(including
section)
(in)
weight (lb)
wctght (lb)
weirfil (lb)
weight fraction .
time (teo)
*a
(lb)
)
(vac)
i!)
(vac)
Original document.
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