Explorer 3

Summary

Explorer 3
Explorer1.jpg
Photograph of the nearly identical Explorer 1 satellite
Names1958 Gamma
Mission typeEarth science
OperatorU.S. Army (Ordnance)
Harvard designation1958 Gamma
COSPAR ID1958-003A
SATCAT no.00006
Mission duration93 days (achieved)
120 days (planned)
Spacecraft properties
Spacecraft typeExplorer
BusExplorer 1
ManufacturerJet Propulsion Laboratory
Launch mass14.1 kg (31 lb)
Dimensions203 cm (80 in) length
15.2 cm (6.0 in) diameter
Power60 watts
Start of mission
Launch date26 March 1958, 17:38:01 GMT
RocketJuno I (RS-24)
Launch siteAtlantic Missile Range, LC-5
ContractorArmy Ballistic Missile Agency (ABMA)
End of mission
Last contact27 June 1958
Decay date27 June 1958
Orbital parameters
Reference systemGeocentric orbit [1]
RegimeMedium Earth orbit
Perigee altitude186 km (116 mi)
Apogee altitude2,799 km (1,739 mi)
Inclination33.38°
Period115.70 minutes
Instruments
Cosmic Ray counter
Micrometeorite detector
 

Explorer 3 (Harvard designation 1958 Gamma) was an American artificial satellite launched into medium Earth orbit in 1958. It was the second successful launch in the Explorers Program, and was nearly identical to the first U.S. satellite Explorer 1 in its design and mission.

Background

The U.S. Earth satellite program began in 1954 as a joint U.S. Army and U.S. Navy proposal, called Project Orbiter, to put a scientific satellite into orbit during the International Geophysical Year (IGY). The proposal, using a U.S. Army Redstone missile, was rejected in 1955 by the Eisenhower administration in favor of the U.S. Navy's Project Vanguard, using a booster advertised as more civilian in nature.[2][3] Following the launch of the Soviet satellite Sputnik 1 on 4 October 1957, the initial Project Orbiter program was revived as the Explorer program to catch up with the Soviet Union.[4]

Launch

The satellite was launched from Cape Canaveral Missile Test Center of the Atlantic Missile Range (AMR), in Florida at 17:38:01 GMT on 26 March 1958 by the Juno I launch vehicle.[5] The Juno I had its origins in the United States Army's Project Orbiter in 1954. The project was canceled in 1955 when the decision was made to proceed with Project Vanguard.

Following the launch of the Soviet Sputnik 1 on 4 October 1957, Army Ballistic Missile Agency (ABMA) was directed to proceed with the launching of a satellite using the Jupiter-C which had already been flight-tested in nose-cone re-entry tests for the Jupiter IRBM (intermediate-range ballistic missile). Working closely together, ABMA and JPL completed the job of modifying the Jupiter-C to the Juno I and building the Explorer I in 84 days.

Spacecraft

Explorer 3 Tape Recorder

Explorer 3 was launched in conjunction with the International Geophysical Year (IGY) by the U.S. Army (Ordnance) into an eccentric orbit. The objective of this spacecraft was a continuation of experiments started with Explorer 1. The payload consisted of a cosmic ray counter (a Geiger-Müller tube) and a micrometeorite detector (a wire grid array and acoustic detector). The Explorer 3 spacecraft was spin-stabilized and had an on-board tape recorder to provide a complete radiation history for each orbit. It was discovered soon after launch that the satellite was in a tumbling motion with a period of about 7 seconds. Explorer 3 decayed from orbit on 27 June 1958, after 93 days of operation.

Mission results

The discovery of the Van Allen radiation belt by the Explorer satellites was considered to be one of the outstanding discoveries of the International Geophysical Year (IGY).

Explorer 3 was placed in an orbit with a perigee of 186 kilometers and an apogee of 2799 kilometers having a period of 115.70 minutes, and inclination of 33.38°.[1] Its total weight was 14.1 kilograms, of which 8.4 kg was instrumentation. The instrument section at the front end of the satellite and the empty scaled-down fourth-stage rocket casing orbited as a single unit, spinning around its long axis at 750 revolutions per minute. Data from these instruments was transmitted to the ground by a 60 milliwatt transmitter operating on 108.03 MHz and a 10 milliwatt transmitter operating on 108.00 MHz.

Transmitting antennas consisted of two fiberglass slot antennas in the body of the satellite itself. The four flexible whip antennas of Explorer 1 were removed from the design.[6] The external skin of the instrument section was painted in alternate strips of white and dark green to provide passive temperature control of the satellite. The proportions of the light and dark strips were determined by studies of shadow-sunlight intervals based on firing time, trajectory, orbit, and orbital inclination.

Electrical power was provided by Mallory type RM Mercury batteries that made up approximately 40% of the payload weight. These provided power that operated the high power transmitter for 31 days and the low-power transmitter for 105 days. Because of the limited space available and the requirements for low weight, the Explorer 3 instrumentation was designed and built with simplicity and high reliability in mind. It was completely successful.

Explorer 3 decayed from orbit on 27 June 1958, after 93 days of operation.

A replica of the spacecraft is currently located in the Smithsonian Institution's National Air and Space Museum, Milestones of Flight Gallery.

See also

References

  1. ^ a b "Trajectory: Explorer-3 1958-003A". NASA. 14 May 2020. Retrieved 15 February 2021. This article incorporates text from this source, which is in the public domain.
  2. ^ Matt Bille and Erika Lishock, The First Space Race: Launching the World's First Satellites, Texas A&M University Press, 2004, Chapter 5
  3. ^ "Project Vanguard — Why It Failed to Live Up to Its Name". Time (magazine). 21 October 1957. Retrieved 12 February 2008.
  4. ^ "Sputnik and the Dawn of the Space Age". NASA History. NASA. Retrieved 13 February 2008. This article incorporates text from this source, which is in the public domain.
  5. ^ "About the Mission". JPL. NASA. Retrieved 24 June 2017. This article incorporates text from this source, which is in the public domain.
  6. ^ Pilkington, W. C. (5 September 1958). "Vehicle Motions as Inferred from Radio-signal- Strength Records". NASA. Retrieved 18 October 2018. This article incorporates text from this source, which is in the public domain.

External links