Encyclopedia Astronautica
NASA Cleveland


NASA Lewis Research Center, Cleveland, USA.

AKA: NASA.
Location: Cleveland.

More... - Chronology...


Associated Countries
Associated Spacecraft
  • Mars Expedition NASA Lewis 1960 American manned Mars expedition. Study 1960. The first NASA study of a manned Mars expedition outlined an opposition-class, nuclear thermal rocket powered spacecraft that would take seven astronauts to the planet's surface for 40 days. More...

Associated Engines
  • HIVHAC NASA Cleveland electric/xenon rocket engine. 430 mN. Isp=2800s. HIVHAC offered mission benefits compared to the 4000s NEXT engine for deep space missions. More...
  • NASA-173GT NASA Cleveland electric rocket engine. Two-Stage Hybrid Hall/Ion Thruster More...
  • NASA-400M NASA Cleveland electric/krypton rocket engine. 1 N. Isp=4000s. Developed to investigate high-power, high specific impulse Hall thruster operation in 2004. More...
  • NASA-457M NASA Cleveland electric/xenon rocket engine. Isp=2326s. 50 kW Hall thruster developed 2001-on. More...
  • NSTAR NASA Cleveland electric/xenon rocket engine. 92 mN. Isp=3100s. Solar Electric Propulsion Technology Application Readiness program developed this 2.3 kW ion engine as primary propulsion for the Deep Space 1 comet and asteroid rendezvous probe, flew 1998. More...
  • SEPS Hughes, TRW, NASA Cleveland electric/mercury rocket engine. 128 mN Isp=3000s. Solar Electric Propulsion Stage program, started in the early 1970s, a goal to provide a primary ion propulsion system operating at a fixed power for Earth orbital applications. More...
  • Sert II NASA Cleveland electric/mercury rocket engine. 28 mN. Flown in 1970. Isp=4200s. The thruster for the Sert-II test consisted of two electron bombardment engines using mercury propellant. More...
  • Sert-I Mercury NASA Cleveland electric/mercury rocket engine. 28 mN. Developed 1962-1964. Isp=4900s. 10 cm diameter mercury electron bombardment ion engine used on the first successful flight test of ion propulsion on a Scout X-4 launch vehicle. More...

See also
  • Agency Agencies or institutions overseeing design, development, construction, or operation of space-related systems. More...

Associated Programs
  • ATS The Applications Technology Satellite was a project with the purpose of improving other satellites, specifically to enhance the ability of existing and future satellites to provide weather, and communications data and air/sea navigation aids. More...

NASA Cleveland Chronology


1956 November 6 - . Launch Site: Wallops Island. Launch Platform: F2H2. LV Family: Recruit. Launch Vehicle: Recruit.
  • Heat Transfer Re-entry Vehicle test - . Nation: USA. Agency: NASA Cleveland. Apogee: 4.00 km (2.40 mi).

1957 - . Launch Site: Wallops Island. Launch Platform: F2H2. LV Family: Recruit. Launch Vehicle: Recruit T55.
  • Heat Transfer Re-entry Vehicle test - . Nation: USA. Agency: NASA Cleveland. Apogee: 4.00 km (2.40 mi).

1957 August 7 - . Launch Site: Wallops Island. Launch Platform: F2H2. LV Family: Recruit. Launch Vehicle: Recruit T55.
  • Heat Transfer Re-entry Vehicle test - . Nation: USA. Agency: NASA Cleveland. Apogee: 4.00 km (2.40 mi).

1958 January 31 - . Launch Site: Wallops Island. Launch Platform: F2H2. LV Family: Recruit. Launch Vehicle: Recruit T55.
  • Heat Transfer Re-entry Vehicle test - . Nation: USA. Agency: NASA Cleveland. Apogee: 4.00 km (2.40 mi).

1958 March 28 - . Launch Site: Wallops Island. Launch Platform: F2H2. LV Family: Recruit. Launch Vehicle: Recruit T55.
1958 April 7 - . Launch Site: Wallops Island. LV Family: Cajun. Launch Vehicle: Nike Cajun.
  • Hi Ball 1 Balloon test - . Nation: USA. Agency: NASA Cleveland. Apogee: 244 km (151 mi).

1958 April 24 - . Launch Site: Wallops Island. LV Family: Cajun. Launch Vehicle: Nike Cajun.
  • Beacon Test 1 Balloon test - . Nation: USA. Agency: NASA Cleveland. Apogee: 122 km (75 mi).

1958 April 25 - . Launch Site: Wallops Island. LV Family: Cajun. Launch Vehicle: Nike Cajun.
  • Beacon Test 1R Balloon test - . Nation: USA. Agency: NASA Cleveland. Apogee: 73 km (45 mi). Summary: First successful launching and erection in space of a 12-foot inflatable sphere for air density measurements, using a Nike-Cajun booster system, by NACA Langley's PARD at Wallops Island, Va..

1958 May 22 - . 00:57 GMT - . Launch Site: Wallops Island. LV Family: Cajun. Launch Vehicle: Nike Cajun.
  • Hi Ball 2 Balloon test - . Nation: USA. Agency: NASA Cleveland. Apogee: 240 km (140 mi).

1958 May 25 - . Launch Site: Wallops Island. LV Family: Cajun. Launch Vehicle: Nike Cajun.
  • Beacon Test 2 Balloon test - . Nation: USA. Agency: NASA Cleveland. Apogee: 122 km (75 mi).

1958 July 15 - . Launch Site: Wallops Island. Launch Platform: B-57A. LV Family: Recruit. Launch Vehicle: Recruit T55.
1958 July 24 - . Launch Site: Wallops Island. Launch Platform: B-57A. LV Family: Recruit. Launch Vehicle: Recruit T55.
1958 September 11 - . Launch Site: Wallops Island. LV Family: Cajun. Launch Vehicle: Nike Cajun.
  • Beacon Test 3 Balloon test - . Nation: USA. Agency: NASA Cleveland. Apogee: 122 km (75 mi).

1958 September 12 - . Launch Site: Wallops Island. Launch Platform: B-57A. LV Family: Recruit. Launch Vehicle: Recruit T55.
1958 October 7 - . Launch Site: Wallops Island. LV Family: Cajun. Launch Vehicle: Nike Cajun.
  • Hi Ball 3 Balloon test - . Nation: USA. Agency: NASA Cleveland. Apogee: 244 km (151 mi).

1963 November 27 - . 19:03 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC36A. LV Family: Atlas. Launch Vehicle: Atlas Centaur. LV Configuration: Atlas Centaur AC-2 / Centaur D 126D.
  • Atlas Centaur 2 - . Payload: Centaur 2B. Mass: 4,620 kg (10,180 lb). Nation: USA. Agency: NASA Cleveland. Class: Moon. Type: Lunar probe. Spacecraft: Surveyor. USAF Sat Cat: 694 . COSPAR: 1963-047A. Apogee: 1,478 km (918 mi). Perigee: 469 km (291 mi). Inclination: 30.4000 deg. Period: 104.60 min. Summary: Launch vehicle test. Launch vehicle put dummy payload into geosynchronous transfer orbit. First successful Centaur (liquid hydrogen-fueled) flight..

1967 April 6 - . 03:23 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC12. LV Family: Atlas. Launch Vehicle: Atlas Agena D SLV-3. LV Configuration: SLV-3 Agena D 5102 (AA21) / Agena D 6152 (AA21). FAILURE: Partial Failure..
  • Research Payload Module 481 - . Payload: Module 481. Nation: USA. Agency: NASA Cleveland. Program: ATS. Decay Date: 1968-06-29 . USAF Sat Cat: 2744 . COSPAR: 1967-031B. Apogee: 10,732 km (6,668 mi). Perigee: 160 km (90 mi). Inclination: 28.4000 deg. Period: 213.28 min.

1970 February 4 - . 02:59 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Delta. Launch Vehicle: Thorad Agena D SLV-2G. LV Configuration: Thorad SLV-2G Agena D 534 (TA12) / Agena D.
  • SERT 2 - . Mass: 1,404 kg (3,095 lb). Nation: USA. Agency: NASA Cleveland. Class: Technology. Type: Ion engine technology satellite. Spacecraft: SERT. USAF Sat Cat: 4327 . COSPAR: 1970-009A. Apogee: 1,046 km (649 mi). Perigee: 1,039 km (645 mi). Inclination: 99.2000 deg. Period: 106.00 min. Space Electric Rocket Test; the ion engines aboard were operated until 1981. The SERT 2 development program started in 1966 and included thruster ground tests of 6742 hours and 5169 hours duration. A prototype version of the SERT 2 spacecraft was ground-tested for a period of 2400 hours with an operating ion engine. In addition to diagnostic equipment and related ion engine hardware, the spacecraft had two identical 15 cm diameter, mercury ion engines. Flight objectives included in-space operation for a period of 6 months, measurement of thrust, and demonstration of electromagnetic compatibility. The thruster maximum power level was 0.85 kW, and this provided operation at a 28 mN thrust level at 4200 s specific impulse. Flight data were obtained from 1970 to 1981 with an ion engine operating intermittently in one of three different modes, namely, HV ion extraction, discharge chamber operation only, or just neutralizer operation. Major results were that two mercury engines thrusted for periods of 3781 hours and 2011 hours. Test duration was limited due to shorts in the ion optical system. Thrust measured in space and on the ground agreed within the measurement uncertainties. Up to 300 thruster restarts were demonstrated. One power-processing unit accumulated nearly 17,900 hours during the course of the mission. Additionally, the ion propulsion system was electromagnetically compatible with all other spacecraft systems.

1993 September 12 - . 11:45 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39B. LV Family: Shuttle. Launch Vehicle: Shuttle. LV Configuration: Space Shuttle STS-51.
  • ACTS - . Payload: Discovery F17 / ACTS [TOS-21H] / Orfeus-SPAS 01. Mass: 2,767 kg (6,100 lb). Nation: USA. Agency: NASA Cleveland. Class: Communications. Type: Civilian communications satellite. Spacecraft: ACTS. USAF Sat Cat: 22796 . COSPAR: 1993-058B. Apogee: 35,806 km (22,248 mi). Perigee: 35,767 km (22,224 mi). Inclination: 3.2000 deg. Period: 1,436.10 min. NASA experimental communications; Advanced Communications Technology Satellite; deployed from STS-51 9/12/93; 100 deg W. Positioned in geosynchronous orbit at 100 deg W in 1993-1999 105 deg W in 2000. As of 5 September 2001 located at 105.36 deg W drifting at 0.007 deg W per day. As of 2007 Mar 10 located at 105.14W drifting at 0.004W degrees per day.

1997 October 15 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. LV Family: Titan. Launch Vehicle: Titan Centaur 401B. LV Configuration: Titan 401B B-33 /Centaur (45E-13).
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