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T.Jor Objectives Measure Temperature and Pres LUNIK br MECHTA (U.S.S.R.) SPACE ACTIVITIES SUMMARY Pro .ct: Lunik I or Mechta (Dream) t.jor Objectives Measure temperature and pres - S sure inside vehicle; study gas components of in- terplanetary matter and corpuscular radiation of Project Direction: U. S. S. R. sin; magnetic fields of Earth and II oon; meteoric particles; heavy nuclei in primary cosmic /radiation. Launched: January 2, 1959 Major R.sults: Placed fl orbit around the Sun. From: Northeast of Ural Lakes Llf.tlm.: (Indefinite) Flight P,ogrn Launch V.hlck: Believed to be a Stages: (1) Modified ICBM, Thrust 220 tons (liquid) + 80 tons (solid); (2) Modified IRBM; (3) Special. Lift.Off Weight: Not Available Dim•nsions: Believed to be 110 feet high. Program: Place instrumented satellite in orbit around Sun. Program Results: Orbit achieved. Perigee (Miles): 91 million from Sun Inclination: 1 degree to Ecliptic 42I3 days . Apogee (Miles): 120 million from Sun Period: Velocity: Average 63,100 mph with respect to Sun. Payload And Instrumentation Dimensions: Not Available Payload WeIghts.Toal weight in flight reported to be 3, 245 pounds; Instrument capsule 800 pounds. Payload Configuration: Hermetically sealed sphere of aluminum magnesium alloy. Instrumentation: To measure temperature andpresure inside vehicle study gas components of in- .terplauet?.ry matter and &rpusôular radiatlon of sim; rn,aetic fields of Earththid i4on, metsx. ic particles; heavy nuclei in primary cosmic radiation, sodium cloud generator. LTi 1 ransmitt.rs: Three: 19. 997 MC and 190995 MC signals of 1. 6 second duration; 19. 993 MC and 183.6 MC. Power Supply: Not Available. '1 0 -I -I Additional Data: fl S Sources: UNOFFICIAL from U.S. and Soviet Pres and Radio. Date: Preparedeptember, 1960 Pr.par.d by Offic. of Public information, U.S. National Asronautics and Spec. Administration, Washington 25, D.C. CDA# ArTIVIIWC JIMUARY VANGUARD. II (iqsq A1h Major Obj.ctiv.s Place satellite. in orbit for Pro I.ct: Vanguard II C (1959 Alpha) study of cloud cOver. Pro oct DIr.ction: NASA . C. C Major R..ult.: Satellite placedin orbit but Launch.d: February 17, 1959 . ;ate1lite precession or wobble prevented inter- From: Atlantic Missile Range pretation of cloud cover data. Lifetim.: . 10 years or more Flight Pro grn Launch V.hlcI.: Vanguard (Satellite Launching Vehicle 4). Stages: (1) Liquid. (2) Liquid. (3) Solid. DimensIons: 72 ft. high, 45 in. diameter. Lift.Off W.Ight: 22, 600 lbs. Program: Place satellite in Earth orbit Program R.sults: Placed satellite in elliptical Earth orbif. Inclination: 32.86 degrees to Equator P.rig.. (Mu..): 314.7'(Sept. 1960) Period: 125.3. minutes Apog.. CMII..): 2, ok6(Sept. 1960) VelocIty: 18, 299 mph at perigee • 13, 109 mph at apogee Payload And Instrumentation Payload W.Ights: 21. 5 lbs. DIm.nslons: .20 in. diameter Sphere with shell of highly polished silicon-monoxide-coated magnesium. Payload Configuration: Instrumentation: Chiefly two infrared photocells and accessory equipment. z Transmitt.rs: 108.00 MC at 10 mw (tracking) lasted 27 days. 108.03 MC at 1 watt triggered from ground lasted 18 days. Pow.r Supply: Mercury batteries. Additional Data: Sources: NASA Dat.: Prepared September, 1960 I Pr.par.d by Offic. of. Public Information, U.S. National A.ronautics and Spac. Administration, Washington 25, D.C. SPACE ACTIVITIES SUMMARY DIOVERER I (1959 Betal & Project: Discoverer I Major Obj.ctiv.s Demonstrate orbital (1959 Beta) capability of Discoverer-Thor com- 0'I . bination and capability of its ground Project Direction: ARPA support equipment. ii r') Launched: Feb. 28, 1959, 1:49 PM (PsT) Major Results: Satellite placed in near- polar orbit. Difficulty in stabili- From: Vandenberg AFB, Calif. zation caused tumbling which hampered continuous tracking. LIfetIme:10 days (approx.)* Flight Program Launch Vehicle: Thor-Agena. Stages: (i) Modified Thor IRBM. (2) Agena. Lift.OHW.ight:Over 100,000 lbs. Dimensions: 78.2 ft. high, 5 . ft. base diameter Program: Place satellite in near-polar orbit. Program Results: Satellite placed in elliptical near-polar orbit. No recovery planned. Perigee (Miles): 176 Inclination: .3 degrees off North-auth axis Apogee (Miles): 519 Period: 95.57 minutes S Velocity: Payload And Instrumentation Dimensions:18.8 ft. high, 5 ft. dianeter Payload Weights: 1,300 total lbs. 1nclu.n second stage casing& all components and 11.0 lbs. of instruments. Payload Configuration: Cylindrical Guidance system including both a pneumatic, Jet control system H Instrumentation: and a hydraulic control system; VHF low power beacon trans- mitter; radar beacon transmitter with t±ansponder, No separate capsule. Transmitters:Includes telemetry and tracking beacon as above. Power Supply: Not available. I—I Additional Data: *Reentered atmosphere and decayed in early March 1959. I S Sources: DOD Date: Prepared September, 1960 Pr.par.d by Offic. of Public Information, U.S. National A.ronautics and Spac. Administration, Washington 25, D.C. SPACE ACTIVITIES SUMMARY YIONEER IV Project: Pioneer IV Major Objectives: Place instrumented probe in an C S Earth-Moon trajectory; measure radiation in space; test photo-electric sensor in vicinity of NASA Project Direction: Moon; sample Moon's radiation; test long-range tracking. Launched: March 3, 1959 Major Results: Achieved Earth-Moon trajectory and yielded important radiation data in space From: Atlantic Missile Range Injection below planned velocity prevented near- lunar experiments. In orbit. around Sun. Lifetime: Eternal orbit around Sun. Flight Pro gran Launch Vehicle: Juno II. Stages: (1) Modified Army Jupiter IRBM. (2) 11 scaled-down Sergeant rockets in cluster. (3) Three scaled-down Sergeants in cluster. (4) One scaled-down Sergeant. Lift-Off Weight: 121, 000 lbs. DImensions: 76 ft. high; 8-3/4 ft. diameter Program: Place instrumented vehicle man Earth-Moon trajectory. If possible, pass. within 20, 000 miles of Moon to test photoelectric sensor. Program Results: Placed in Earth-Moon trajectory and achieved orbit around Sun. Came within 37,300 miles of Moon at 5:24 p.m., EST. March 4, 1959. Perigee (Miles): 91.7 million from Sun. Inclination: .127 degrees to Ecliptic . Apogee (Miles): 107 .9million from Sun. Period: . 4Q6. 9 days Velocity: injection velocity of 24, 790 mph was 188 mph below planned velocity. Average speed in Sun orbit: 65,1L 4 mph with respect to Sun. Payload And Instrumentation Dimensions: 20 in. long; 9 in. diameter Payload W.ights: 13.40 lbs. Payload Configuration: Conical with shell of gold-washed fiberglass which also serves as conductor and antenna. Instrumentation: For measurement of radiation in space and photoelectric sensor (not used) for tests in vicinity of Moon. Transmitters: 960. 05 MC @180 .mwwlth .3 subcarriers. Lifetime: 90 hours. tj Power Supply: Mercury batteries. Additional Data: Tracked for 82 hours to a distance of 407, 000 miles. Sources: NASA Date: Prepared September, 1960 Prepared by Office of Public Information, U.S. National Aeronautics and Space Administration, Washington 25, D.C. SPACE ACTIVITIES SUMMARY VANGUARD Project: Vanguard Major Objectives: a) Place instrumented satellite in orbit to map Earth's magnetic \J1 field. b) Place inflatable sphere in orbit to r NASA Project Direction: measure density of extreme upper cji atmosphere. Launched: April 13, 1959 Major Results: No orbit due to malfunction in second stage. Payload and second stage fell From: Atlantic Missile Range into Atlantic several hundred mile from launch point. Lifetime: Not Applicable Flight Program Launch Vehicle: Vanguard (Satellite Launching Vehicle 5) Stages: (1) Liquid. (2) Liquid. (3) SolId. Lift.Off Weight: 22, 600 lbs. Dimensions: 72 ft. high, 45 in. diameter Program: Place satellite and inflatable sphere in Earth orbit. Program Results: No orbit due to malfunction in second stage. Perigee (Miles): Not Applicable Inclination: Not Applicable Apogee (Miles): Not Applicable Period: Not Applicable . Velocity: Not Applicable Payload And Instrumentation Dimensions: Satellite "A": 1,3 in. sphere topped Payload Weights: 23.3 lbs. total. by 17-1/2 x 2-1/2 in. cyl. "W': 30 in. in- flatable sphere. Payload Configuration: As above. Satellite "A" of fiberglass and phenolic resins; "B" of laminated aluminum foil and plastic sheet. Instrumentation: Satellite "A" contained precise manetometer to measure earth's magnetic field. "B" contained no instrumentation; was to be tracked optically. Transmitters: For "A", 108 MC at 10 mw for tracking and 108. 03 MC at 80 mw for telemetry at ground command. 0 Power Supply: Silver zinc batteries. Additional Data: . Sources: NASA Date: Prepared September 1960 Prepared by Office of Public Information, U.S. National Aeronautics and Space Administration, Washington 25, D.C. SPACE ACTIVITIES SUMMARY DISCOVERER II (1959 GRmmn.) Project: Discoverer II Major Objectives: to (1959 Gamiiia) gather data on propulsion, communi- fl cations, orbital performance, stabi- Project Direction: ARPA lization, recovery techniques, and measurement of cosmic radiation. Launched: April 13, 1959, 1:18 PM (PST) MajorR.sults:AChiêVed near-circular polar orbit and controlled stabili- From: Vandenberg AFB, Calif. zation. Timer malfunction caused premature capsule ejection and pre- Lifetlme:13 days (Approx.) vented recovery attempt.* Flight Program Launch Vehicle: Thor-Agena. Stages: (1) ModifIed Thor IRBN. (2) Agena LiftOff Weight: io8, 4OO lbs. (Approx.) Dlm.nslons: 78.6 ft. high, 5 ft. base diameter Program: place satellite in near-polar orbit and recover capsule. Program R.sults:Satellite placed In near-polar orbit.
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