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space wire
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 | Jupiter missile
Credit: © Mark Wade
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 | Juno 2
Credit: © Mark Wade
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To set foot on the soil of the asteroids, to lift by hand a rock from the Moon, to observe Mars from a distance of several tens of kilometers, to land on its satellite or even on its surface, what can be more fantastic? From the moment of using rocket devices a new great era will begin in astronomy: the epoch of the more intensive study of the firmament.
---Tsiolkovskiy
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 | Juno 2
Juno 2 - COSPAR 1959-Iota
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Orbital launch vehicle. Year: 1958. Family: Jupiter. Country: USA. Status: Hardware. Manufacturer: Von Braun. Satellite launcher derived from Jupiter IRBM. Basic 4 stage vehicle consisted of 1 x Jupiter + 1 x Cluster stage 2 + 1 x Cluster stage 3 + 1 x RTV Motor Launches: 10. Failures: 6. Success Rate: 40.00% pct. First Launch Date: 06 December 1958. Last Launch Date: 24 May 1961. Launch data is: complete. LEO Payload: 41 kg. to: 200 km Orbit. Payload: 6 kg. to a: Translunar trajectory. Liftoff Thrust: 68,040 kgf. Liftoff Thrust: 667.20 kN. Total Mass: 55,110 kg. Core Diameter: 2.67 m. Total Length: 24.00 m. Development Cost $: 84.50 million. in 1958 average dollars. Launch Price $: 10.83 million. in 1985 price dollars. Total Development Built: 30. Total Production Built: 68. Flyaway Unit Cost $: 0.74 million. in 1960 unit dollars. Cost comments: Development cost, flyaway cost is for Jupiter IRBM.
- Model: Juno II (3). Family: Jupiter.
3 stage version consisting of 1 x Jupiter + 1 x Cluster stage 2 + 1 x Cluster stage 3 LEO Payload: 50 kg. Apogee: 1,000 km. Liftoff Thrust: 667.00 kN. Total Mass: 55,300 kg. Core Diameter: 2.67 m. Total Length: 23.40 m.
- Model: Juno II. Family: Jupiter.
Satellite launcher derived from Jupiter IRBM. Basic 4 stage vehicle consisted of 1 x Jupiter + 1 x Cluster stage 2 + 1 x Cluster stage 3 + 1 x RTV Motor LEO Payload: 41 kg. to: 200 km Orbit. Payload: 6 kg. to a: Translunar trajectory. Liftoff Thrust: 68,040 kgf. Liftoff Thrust: 667.20 kN. Total Mass: 55,110 kg. Core Diameter: 2.67 m. Total Length: 24.00 m.
Stage Data - Juno II- Stage Number: 1. 1 x Jupiter Gross Mass: 54,431 kg. Empty Mass: 5,443 kg. Thrust (vac): 77,367 kgf. Isp: 282 sec. Burn time: 182 sec. Isp(sl): 248 sec. Diameter: 2.67 m. Span: 2.67 m. Length: 18.28 m. Propellants: Lox/Kerosene No Engines: 1. S-3 Status: Hardware.
- Stage Number: 2. 11 x Sergeant Gross Mass: 42 kg. Empty Mass: 21 kg. Thrust (vac): 680 kgf. Isp: 235 sec. Burn time: 6 sec. Isp(sl): 214 sec. Diameter: 0.30 m. Span: 0.30 m. Length: 1.00 m. Propellants: Solid No Engines: 1. Sergeant Status: Hardware.
- Stage Number: 3. 3 x Sergeant Gross Mass: 42 kg. Empty Mass: 21 kg. Thrust (vac): 680 kgf. Isp: 235 sec. Burn time: 6 sec. Isp(sl): 214 sec. Diameter: 0.30 m. Span: 0.30 m. Length: 1.00 m. Propellants: Solid No Engines: 1. Sergeant Status: Hardware.
- Stage Number: 4. 1 x Sergeant Gross Mass: 42 kg. Empty Mass: 21 kg. Thrust (vac): 680 kgf. Isp: 235 sec. Burn time: 6 sec. Isp(sl): 214 sec. Diameter: 0.30 m. Span: 0.30 m. Length: 1.00 m. Propellants: Solid No Engines: 1. Sergeant Status: Hardware.
Juno II Chronology
1955 Jul 1 - Jupiter IRBM proposed. Huntsville proposes Jupiter 1500 miles range/2500 lb payload. AF proposes Thor. Both authorized. Jupiter also ship-launch capable.
1955 Nov 8 - Thor and Jupiter projects approved. Secretary of Defense approved Jupiter and Thor IRBM programs, the first based on experience gained by Redstone Arsenal team from V-2 and Redstone, the latter on experience gained from Atlas program.
1956 Aug 8 - Jupiter test stand completed. Largest U.S. test stand for rocket motors was completed at Redstone Arsenal, slated for Jupiter IRBM.
1956 Nov 1 - Jupiter loses Navy support. Following Navy withdrawal from the Jupiter IRBM program, separate Army and Navy Ballistic Missile Committees were established under chairmanship of respective service secretaries. Navy withdrawal based on interest in solid-propellant Polaris as ship-based IRBM.
1956 Nov 26 - DoD assigns long range missiles to Air Force. Secretary of Defence Wilson rules that Army could not develop missiles over 200 mile range. Jupiter assigned to AF.
1958 Jan 15 - Jupiter put into operation service. 4751st Air Defense Missile Wing to develop and conduct training program for Bomarc units, and the 864th Strategic Missile Squadron to be equipped with Jupiter IRBM, were both activated.
1958 Dec 6 5:44 - First Stage shut down too early. Partial Failure.. Juno II AM-11 Cape Canaveral. LC: LC5.
1959 Mar 3 5:10 - Juno II AM-14 Cape Canaveral. LC: LC5.
1959 Jun 6 - Jupiter biological test results. Army announced that sea urchin eggs fertilized before Jupiter nose cone flight continued to grow normally.
1959 Jul 8 - Jupiter deleted as Mercury launch vehicle. As developmental planning for Project Mercury evolved, NASA notified the Army that to reduce the variety of launching vehicles to Jupiter missile would not be used for Project Mercury tests.
1959 Jul 16 17:37 - Control lost after 5.5 sec. Destroyed by range safety.. Juno II AM-16 Cape Canaveral. LC: LC5.
1959 Aug 15 0:31 - First stage shut down too early; no attitude control for upper stages.. Juno II AM-19B Cape Canaveral. LC: LC26B.
1959 Oct 13 15:30 - Juno II AM-19A Cape Canaveral. LC: LC5.
1960 Mar 23 13:35 - Upper stage failed to ignite. Third stage failed to ignite due to loss of radio contact.. Juno II AM-19C Cape Canaveral. LC: LC26B.
1960 Nov 3 5:23 - Juno II AM-19D Cape Canaveral. LC: LC26B.
1961 Feb 25 0:13 - Third Stage failed to ignite.. Juno II AM-19F Cape Canaveral. LC: LC26B.
1961 Apr 27 14:16 - Juno II AM-19E Cape Canaveral. LC: LC26B.
1961 May 24 19:48 - Second Stage failed to ignite.. Juno II AM-19G Cape Canaveral. LC: LC26B.
Bibliography:- McDowell, Jonathan, Jonathan's Space Home Page, Harvard University, 1997-present. Web Address when accessed: http://hea-www.harvard.edu/~jcm/space/space.html.
- Koelle, Heinz Hermann,, Handbook of Astronautical Engineering, McGraw-Hill,New York, 1961.
- Nicholas, Ted G., U.S. Missile Data Book, 1983, Seventh Edition, Data Search Associates, Fountain Valley, California, 1982..
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