Juno 2 Juno 2 - COSPAR 1959-Iota

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

Manufacturer: Von Braun. Launches: 10. Failures: 6. Success Rate: 40.00% pct. First Launch Date: 6 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. Associated Spacecraft: Beacon 1, P-14, Pioneer 3-4, S-1, S-15, S-30, S-46. 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. Family: Jupiter. Country: USA.

  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.

• Model: Juno II (3). Family: Jupiter. Country: USA.

  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.

• 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: Out of Production.

• 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: Out of Production.

• 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: Out of Production.

• 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: Out of Production.

• Jupiter IRBM proposed. Nation: USA.

  Huntsville proposes Jupiter 1500 miles range/2500 lb payload. AF proposes Thor. Both authorized. Jupiter also ship-launch capable. References: 86 .

• Thor and Jupiter projects approved. Nation: USA.

  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. References: 17 .

• Jupiter test stand completed. Nation: USA.

  Largest U.S. test stand for rocket motors was completed at Redstone Arsenal, slated for Jupiter IRBM. References: 17 .

• Jupiter loses Navy support. Nation: USA.

  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. References: 17 .

• DoD assigns long range missiles to Air Force. Nation: USA.

  Secretary of Defence Wilson rules that Army could not develop missiles over 200 mile range. Jupiter assigned to AF. References: 86 .

• Jupiter put into operation service. Nation: USA.

  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. References: 17 .

• Pioneer 3 Nation: USA. Program: Pioneer. Mass: 6 kg. Class: Planetary. Type: Lunar. Spacecraft: Pioneer 3-4. Agency: NASA. COSPAR: 1958-Theta-1. USAF Sat Cat: 111. Decay Date: 7 December 1958.

  Failed to reach moon; provided radiation data. Pioneer III, the third U.S.-IGY intended lunar probe under the direction of NASA with the Army acting as executive agent, was launched from the Atlantic Missile Range by a Juno II rocket. The primary objective, to place the 12.95 pound scientific payload in the vicinity of the moon, failed. Pioneer III reached an altitude of approximately 70,000 miles and revealed that the earth's radiation belt comprised at least two distinct bands. References: 1 , 2 , 5 , 6 , 16 .

• Pioneer 4 Nation: USA. Program: Pioneer. Mass: 6 kg. Class: Planetary. Type: Lunar. Spacecraft: Pioneer 3-4. Agency: NASA. COSPAR: 1959-Nu-1. USAF Sat Cat: 113.

  The fourth U.S.-IGY lunar probe effort, Pioneer IV, a joint project of the Army Ballistic Missile Agency and Jet Propulsion Laboratory under the direction of NASA, was launched by a Juno II rocket from the Atlantic Missile Range. Intended to impact on the lunar surface, Pioneer IV achieved earth-moon trajectory, passing within 60,200 km of the moon before going into permanent orbit around the sun. References: 1 , 2 , 5 , 6 , 16 .

• Jupiter biological test results. Nation: USA.

  Army announced that sea urchin eggs fertilized before Jupiter nose cone flight continued to grow normally. References: 17 .

• Jupiter deleted as Mercury launch vehicle. Nation: USA. Program: Mercury.

  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. References: 17 .

• Explorer S-1 Nation: USA. Program: Explorer. Payload: S-1. Mass: 41 kg. Class: Earth. Type: Magnetosphere. Spacecraft: S-1. Agency: NASA. COSPAR. Decay Date: 16 July 1959. References: 5 , 126 .

• Beacon 2 Nation: USA. Mass: 5 kg. Class: Technology. Spacecraft: Beacon 1. Agency: U.S. Navy. COSPAR. Decay Date: 14 August 1959. References: 5 , 126 .

• Explorer 7 Nation: USA. Program: Explorer. Payload: S-1A. Mass: 42 kg. Class: Earth. Type: Magnetosphere. Spacecraft: S-1. Agency: NASA. Perigee: 523 km. Apogee: 857 km. Inclination: 50.3 deg. Period: 98.6 min. COSPAR: 1959-Iota-1. USAF Sat Cat: 22.

  Spacecraft engaged in research and exploration of the upper atmosphere or outer space. Returned magnetic field and solar flare data. References: 1 , 2 , 5 , 6 .

• Explorer S-46 Nation: USA. Program: Explorer. Payload: S-46. Mass: 16 kg. Class: Earth. Type: Magnetosphere. Spacecraft: S-46. Agency: NASA. COSPAR. Decay Date: 23 March 1960. References: 5 , 126 .

• Explorer 8 Nation: USA. Program: Explorer. Payload: S-30. Mass: 41 kg. Class: Earth. Type: Ionosphere. Spacecraft: S-30. Agency: NASA. Perigee: 394 km. Apogee: 1,331 km. Inclination: 49.9 deg. Period: 102.2 min. COSPAR: 1960-Xi-1. USAF Sat Cat: 60.

  Ionospheric research. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). References: 1 , 2 , 5 , 6 .

• Explorer Nation: USA. Program: Explorer. Payload: S-45. Mass: 34 kg. Class: Solar. Spacecraft: P-14. Agency: NASA. COSPAR. Decay Date: 24 February 1961. References: 5 , 126 .

• Explorer 11 Nation: USA. Program: Explorer. Payload: S-15. Mass: 37 kg. Class: Solar. Spacecraft: S-15. Agency: NASA. Perigee: 480 km. Apogee: 1,458 km. Inclination: 28.8 deg. Period: 104.5 min. COSPAR: 1961-Nu-1. USAF Sat Cat: 107.

  Gamma ray data. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). References: 1 , 2 , 5 , 6 .

• Explorer S-45A Nation: USA. Program: Explorer. Payload: S-45A. Mass: 33 kg. Class: Solar. Spacecraft: P-14. Agency: NASA. COSPAR. Decay Date: 24 May 1961. References: 5 , 126 .

• McDowell, Jonathan, Jonathan's Space Home Page, Harvard University, 1997-present. Web Address when accessed: http://www.planet4589.org/jsr.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..