C00212846 ??? Document 4 of 25 for FBIS ??' DOCK 000056961 PD-rG R 151430Z FEB 95 FM FM FBIS BRUSSELS BE TO TO RUCWAAA/FBIS RESTON VA RHCTAAA/500SS.FALCON AFB CO//IN// RHCTAAA/11SWS FALCON AFB CO//DOA// RHDIAAA/NASA LANGLEY FLD HAMPTON VA RHEHWSR/WHITE HOUSE SITUATION ROOM WASHINGTON DC//OSTP// RHHMMCY/JICPAC HONOLULU HI RUAJMAB/JDET KAMI SEYA JA RUCEAAB/HQ AFSPC INTEL PETERSON AFB CO RUCEAAM/COMBINED INTEL CTR CHEYENNE MTN AS CO RUCWAAA/FBIS RESTON VA//TECHT// RUDKMKB/FBIS LONDON UK//BBC// RUDKMKE/FBIS LONDON UK RUDMONI/ONI WASHINGTON DC//214// RUEAIIS/STORAGE CENTER FBIS RESTON VA RUEALGX/DEFINTAGNCY WASH DC RUEANAT/NASA HQ WASHINGTON DC//FOR CODE IR// RUEANAT/NASA HQ WASHINGTON DC//FOR CODE ID// RUEHFR/USDAO PARIS FR RUEHFR/AMEMBASSY PARIS//ATTN NATIONAL SCIENCE FOUNDATION REP// RUEHFR/AMEMBASSY PARIS//SCIENCE COUNSELOR// RUEHUS/AMEMBASSY BONN//USAF RDLO// RUEHUS/AMEMBASSY BONN//ATTN SCIENCE COUNSELOR// RUEOAYC/CDRFSTC CHARLOTTESVILLE VA//IAAIF-ICB/HEMMER// RUESDI/F$IS NICOSIA CY RUESDJ/FBIS OKINAWA JA RUETIAV/DIRNSA FT GEO G MEADE MD//W15/G79/T5// RULSLAJ/NAVSPOC DAHLGREN VA RUWMEMA/21OSS PETERSON AFB CO//OGSI// RUWOHEA/NASA/ARC MOFFETT FLD CA RUWOHEA/NASA GSFC GREENBELT MD RUWOHEA/NASA JET PROPULSION LAB PASADENA CA RUWTAEA/NAIC WRIGHT PATTERSON AFB OH//TAI// RUWTAEA/NAIC WRIGHT PATTERSON AFB OH//TATD./FIENE// RUWTBCA/NASA JOHNSON SPACE CEN HOUSTON TX RUWTNOK/HQ USSPACECOM.PETERSON AFB CO//POLAD// ACCT F BBR-EWDK ST CLAS UNCLAS 7S/EST01B LD SERI SERIAL: BR1502143095 PASS PASS: ATTN BBC SD COPY TO 40 COUN COUNTRY: FRANCE SUBJ SUBJ: TAKE 2 OF 2 -- HYPERVELOCITY TEST TECHNIQUES DISCUSSED REF REF: BR1502142895 PARIS NEWS FROM PROSPACE ENGLISH DEC 94/// EXPERIMENTAL RESULTS ((SUBHEAD)) ((FBIS TRANSCRIBED EXCERPT)) ((PASSAGE OMITTED ON DELICACY OF EXPERIMENTS)) THE FLATNESS OF EACH INTERMEDIATE LAUNCH PLAYS A VITAL ROLE IN ACCELERATING THE LAST STAGE. ANY DIVERGENCE OF THE SHOCK WAVE, AT ANY LEVEL, MEANS A CORRESPONDING DECREASE IN ENERGY TRANSMITED TO THE' PROJECTILE, WHILE INCREASING THE RISK OF FRAGMENTING THE PROJECTILE RIGHT FROM THE BEGINNING. FOR THIS REASON THE DIAMETER OF THE PROJECTILE IS LIMITED TO A FRACTION OF THE CARTRIDGE DIAMETER (LESS THAN 25 PERCENT, BUT VARIABLE DEPENDING ON MATERIAL USED.) BY COMBINING A JUDICIOUS CHOICE OF CARTRIDGE SIZE WITH VARIABLE PROJECTILE THICKNESS AND DIAMETERS, THIS TECHNIQUE OPENS THE WAY TQ pprove C00212846 A VAST RANGE OF SPEEDS AND WEIGHTS. IT IS ALSO THEORETICALLY EASY TO CALCULATE PERFORMANCE. A NUMBER OF TEST SHOTS HAVE BEEN FIRED USING COPPER, ALUMINUM AND, MORE RECENTLY, LIGHTER MATERIALS SUCH AS MAGNESIUM. THREE TYPES OF TEST DIAGNOSTICS ARE GENERALLY USED, PARTICUL.ARLY-FOR SPEED MEASUTREDCNT: FLASH X-RAY AND LASER DOPPLER INTER::EROMETRY FOR THE SINGLE-STAGE AND OCCASIONALLY TWO-STAGE LAUNCHERS, AND CHRONOMETRIC SWITCHES FOR TEE THREE-STAGE LAUNCHERS. PROMISES AND PROBLEMS ((SUBHEAD)) THE BEST TEST RESULTS OBTAINED TO DATE ARE: - 2-STAGE: 9.5KM/S (9 GRAMS OF STEEL) - 3-STAGE: 13.8 KM/S (1.75 GRAMS OF ALUMINUM) THE MULTISTAGE LAUNCHER TECHNIQUE IS POTENTIALLY WELL AAPTED TO THE STUDY OF SPACE DEBRIS, SINCE THE PROJECTILES USED ARE ORTHOCYLINDERS WITH VARIABLE FORMATS, THAT CAN BE MODELED AND ARE VERY GRADUALLY ACCELERATED, THANKS TO THE MULTISTAGE DESIGN AND THE PRESENCE OF AIR LAYERS. THE MATERIAL IS HOMOGENEOUS, DOES NOT DEFORM DURING FLIGHT, AND THE PROJECTILES REMAIN IN A SOLID STATE. HOWEVER, FIRING IN A VACUUM MAY BE REQUIRED FOR LONG FLIGHTS TO AVOID INADVERTENT ROTATION OR BRAKING. THIS TECHNIQUE OFFERS A HIGH DEGREE OF FLEXIBILITY IN ACHIEVING MASS/SPEED GOALS, BUT PROBLEMS - MAJOR ONES - STILL EXIST, IN TERMS OF PROJECTILE SEPARATION AND LAUNCHER COST. UNLIKE THE HY?ERVELOCITY JETS, A LARGE AMOUNT OF MATTER IS ACCELERATED ALONG WITH THE PROJECTILE ITSELF. AS FOR THE SINGLE-STAGE LAUNCHERS, SEVERAL TECHNIQUES HELP TO 'ELIMINATE, OR AT LEAST LIMIT, THE "UFOS" - UNDESIRABLE FLYING OBJECTS. ONE IS OF COURSE THE CONICAL FORM OF THE PROJECTILE SUPPORT RING THAT CAUSES A SLIGHT DEVIATION IN THE TRAJECTORY OF THESE UNDESIRABLE FBAG CNTS. ANOTHER IS TO INSTALL ALONG THE TRAJECTORY INCLINED "FRAGMENT SKIMMERS WITH HOLES CALIBRATED ACCORDING TO THE SIZE OF THE PROJECTILE. FOR THE MULTISTAGE DESIGN, THE WEIGHT OF THE INTERMEDIATE STAGES CAN BE VARIED, THUS TAXING MAXIMUM ADVANTAGE OF THE SO-CALLED "BILLIARD BALL" EFFECT: I.E., THE COMPLETE HALT OF A STAGE WHEN IT HITS THE NEXT ONE, AND OPTIMIZED TRANSFER OF QUANTITATIVE INERTIA. ALSO WORTH NOTING IS THE NON-NEGLIGIBLE, AND UNEXPECTED, ADVANTAGE OFFERED BY THE ACTIVE INTERMEDIATE MEDIA, WHICH AFTER DETONATION ARE TRANSFORMED INTO GASES THAT HAVE NO EFFECT ON THE TARGET. ((PASSAGE OMMITTED ON COST FOR USE IN SPACE DEBRIS TESTING)) THIS REPORT MAY CONTAIN COPYRIGHTED MATERIAL. COPYING AND DISSEMINATION IS PROHIBITED WITHOUT PERMISSION OF THE COPYRIGHT OWNERS. (ENDALL) DEC 94 15/1430Z FEEB498 BT #0990 NNNN NNN 4 =--EOD---