Explorer 13

Last updated

Explorer 13
Explorer-13.jpg
Explorer 13 satellite
NamesS-55A
NASA S-55A
Mission type Micrometeoroid research
Operator NASA
Harvard designation1961 χ1
COSPAR ID 1961-022A
SATCAT no. 00180
Mission duration2.5 days (achieved)
Spacecraft properties
SpacecraftExplorer XIII
Spacecraft typeScience Explorer
Bus S-55
Manufacturer Goddard Space Flight Center
Launch mass86 kg (190 lb)
Dimensions61 × 1.92 cm (24.02 × 0.76 in) cylinder
Power Solar cells and nickel-cadmium batteries
Start of mission
Launch date25 August 1961, 18:29:44 GMT [1]
Rocket Scout X-1 (ST-6)
Launch site Wallops Flight Facility, LA-3
Contractor Vought
Entered service25 August 1961
End of mission
Last contact28 August 1961
Decay date28 August 1961
Orbital parameters
Reference system Geocentric orbit
Regime Low Earth orbit
Perigee altitude 125 km (78 mi)
Apogee altitude 1,164 km (723 mi)
Inclination 37.7°
Period 97.5 minutes
Instruments
 

Explorer 13, (also called S-55A), was a NASA satellite launched as part of the Explorer program on 25 August 1961, at 18:29:44 GMT, [1] from Wallops Flight Facility (WFF), Virginia. [2]

Contents

Mission

The objectives of the flight were to test vehicle performance and guidance and to investigate the nature and effects of micrometeoroids on the spacecraft systems. The scientific instrumentation consisted of cadmium sulfide-cell, wire-grid, piezoelectric, pressurized-cell, and foil-type micrometeoroid detectors. [2]

Spacecraft

The spacecraft was a 61 × 192 cm (24 × 76 in) cylinder. Weighing 86 kg (190 lb), including its fourth stage and transition section, its objective was to test the performance of a Scout launch vehicle and its guidance system and to investigate the nature and effects of space flight on micrometeoroids. Its payload was a 61 × 192 cm (24 × 76 in) cylinder, almost covered by five types of micometeoroid impact detectors, two transmitters, solar cells and nickel-cadmium batteries. [2]

Instruments

Cadmium Sulfide Cell Micrometeorite Detector

Two cadmium sulfide (CdS) cell detectors mounted 180° apart on the fore-end of the spacecraft shell were used to detect micrometeoroid particles too fine to damage heavy metallic hardware, but presumably present in sufficient numbers to damage sensitive surfaces. Each cell sensor consisted of a mirrorized ellipsoidal flask with two optical foci. A sheet of aluminized mylar film was stretched across one of the focal planes, while the cadmium-sulfide cell was mounted in the other. The total effective area exposed to penetration was 20.0-cm2. When a micrometeoroid penetrated the opaque aluminized film, the rays from the Sun would either fall on the cell or be reflected on it from the mirrorized walls. The cells were calibrated on the ground prior to the flight and the sensitivity was such that a particle about 25 microns in diameter could be detected. The glass flask detector represented a volume of air that had to be evacuated as the satellite left the atmosphere. For this purpose a vent hole was provided in the rear of the flask. Preliminary ground tests indicated that the aluminized mylar film would not be torn by the expanding air, but postflight analysis and tests indicated that the film was ruptured during launch, admitting large amounts of sunlight and making the experiments inoperative. Improper flask venting is assumed to be the probable cause of experiment failure. [3]

Copper Wire Micrometeroite Detector

Forty-six copper wire card detectors, consisting of windings of fine wire mounted to 3.68 cm × 17.78 cm (1.45 in × 7.00 in) rectangular cards, were used to detect particle impacts. Fourteen of the cards had wire 50 microns thick, and 32 cards had wire 75 microns thick. The total exposed effective area was 0.11 m2. The cards were mounted in quadrants on a fiberglass support on the end of the spacecraft cylinder opposite the end on which the antennas were mounted. A break in the wire of a card would change its resistance, and this would be reported via telemetry to the transmitter. Temperatures at the wire card surfaces were expected to extend from minus 10 °C (50 °F) to a maximum of 60 °C (140 °F), an amount sufficient to change the residence of the card. To compensate for this, a 100-ohm resistor was wired in parallel with a 300-phm fixed resistor and installed in series with each 50 microns card and with each pair of 75 microns cards. The particle size required to break a wire was estimated to be one-half the size of the wire. During the 2.5 days in which the satellite remained in orbit, no meteoroid hits were recorded. [4]

Impact Detection

The purposes of the experiment were to extend micrometeoroid measurements to a low population range where few data exist and to correlate with and augment the data amassed by previous satellite experiments using similar techniques. The detector had three threshold levels of momentum sensitivity (0.01, 0.1, and 1.0 gm-cm/sec) and consisted of two different physical configurations of detecting surfaces. The first configuration, which was used for high and low sensitivity detection, consisted of a pair of impact-sensitive stainless steel plates mounted on the conical portion of the satellite forward shell. The plates, which had a total geometric area of 0.142 m2, each had an attached transducer, as well as signal conditioning, impact-event counting, and count-storage circuitry. The second detector configuration was composed of 20 of the 0.013-cm thick pressurized-cell penetration detectors that were sensitized for impact detection. The cells, which had a total area of 0.186 m2, were used for intermediate impact detection. The short orbital lifetime of the spacecraft (2.5 days) permitted only 10 interrogations of the satellite recorder. The measured impact flux rates were substantially higher than those obtained by earlier meteoroid experiments and probably contained false counts due to aerodynamic mechanical perturbances and temperature effects on impact-sensing transducer elements resulting from the low initial perigee. Hence, the data must be considered as inconclusive. [5]

Pressurized Cell Micrometeorite Detector

The pressurized cells, which were the primary sensors of Explorer 13, occupied the major portion of the sensitive area. One hundred and sixty beryllium copper cells of five thicknesses were mounted around the periphery of the spacecraft in five circular rows, each row containing 32 cells. The cells were pressurized prior to launch with helium gas to about 10 psi over atmospheric pressure. By means of a pressure-activated switch on each cell, the pressure loss caused by a micrometeoroid impact could be detected and telemetered. No attempt was made to monitor the pressure leak rate. The number of cells of each thickness were as follows—sixty 0.0025 cm (0.00098 in), forty 0.0038 cm (0.0015 in), twenty 0.0076 cm (0.0030 in), twenty 0.064 cm (0.025 in), and twenty 0.130 cm (0.051 in). The penetration area of each detector was about 140-cm2, so that 2.25 m2 of area were exposed for the experiment. Because of the semicircular cross section of the pressurized cells, however, the effective area for micrometeoroid capture was smaller than the exposed area. A large injection-angle error caused the spacecraft's orbital lifetime to be only 2.5 days, but information from the experiment was telemetered and recorded for 29 passes. There were no switch openings of the pressurized cell detectors during this time. Pressurized cell temperatures, which were shown to vary between 56 °C (133 °F) and 27 °C (81 °F), were monitored throughout the flight. There was no indication of any malfunctioning of the 160 pressurized-cell detectors during the launch and orbital lifetime of the vehicle. [6]

Launch

Explorer 13 was injected into a geocentric orbit of moderate eccentricity using a Scout X-1 launch vehicle. The orbit was lower than planned, and the spacecraft reentered in the atmosphere on 28 August 1961, after only slightly more than 2 days in orbit. No penetrations were recorded by this satellite during experiment operations. This aided in determination of useful flux limits for subsequent experiment design. [2]

See also

Related Research Articles

Lunar Orbiter program Series of five uncrewed lunar orbiter missions

The Lunar Orbiter program was a series of five uncrewed lunar orbiter missions launched by the United States from 1966 through 1967. Intended to help select Apollo landing sites by mapping the Moon's surface, they provided the first photographs from lunar orbit and photographed both the Moon and Earth.

Vanguard 3

Vanguard 3 is a scientific satellite that was launched into Earth orbit by the Vanguard SLV-7 on 18 September 1959, the third successful Vanguard launch out of eleven attempts. Vanguard rocket: Vanguard Satellite Launch Vehicle-7 (SLV-7) was an unused Vanguard TV-4BU rocket, updated to the final production Satellite Launch Vehicle (SLV).

Explorer 2 was an American unmanned space mission within the Explorer program. Intended to be a repetition of the previous Explorer 1 mission, which placed a satellite into medium Earth orbit, the spacecraft was unable to reach orbit due to a failure in the launch vehicle during launch.

Explorer 35 NASA satellite of the Explorer program

Explorer 35,, was a spin-stabilized spacecraft built by NASA as part of the Explorer program. Designed for the study of the interplanetary plasma, magnetic field, energetic particles, and solar X-rays, from lunar orbit.

Explorer 11 NASA satellite of the Explorer program

Explorer 11 was a NASA satellite that carried the first space-borne gamma-ray telescope. This marked the beginning of space gamma-ray astronomy. Launched on 27 April 1961 by a Juno II, the satellite returned data until 17 November 1961, when power supply problems ended the science mission. During the spacecraft's seven-month lifespan it detected twenty-two events from gamma-rays and approximately 22,000 events from cosmic radiation.

Explorer 7 NASA satellite of the Explorer program

Explorer 7 was a NASA satellite launched on 13 October 1959, at 15:30:04 GMT, by a Juno II launch vehicle from Cape Canaveral Air Force Station (CCAFS) to an orbit of 573 × 1,073 km (356 × 667 mi) and inclination of 50.27°. It was designed to measure solar X-ray and Lyman-alpha flux, trapped energetic particles, and heavy primary cosmic rays. Secondary objectives included collecting data on micrometeoroid penetration, molecular sputtering and studying the Earth-atmosphere heat balance.

Pegasus (satellite)

The Pegasus Project was a NASA initiative to study the frequency of micrometeorite impacts on spacecraft by means of a constellation of three satellites launched in 1965. All three Pegasus satellites were launched by Saturn I rockets, and remained connected with their upper stages.

Explorer 33 NASA satellite of the Explorer program

Explorer 33, also known as IMP-D and AIMP-1, was a spacecraft in the Explorer program launched by NASA on 1 July 1966 on a mission of scientific exploration. It was the fourth satellite launched as part of the Interplanetary Monitoring Platform series, and the first of two "Anchored IMP" spacecraft to study the environment around Earth at lunar distances, aiding the Apollo program. It marked a departure in design from its predecessors, IMP-A through IMP-C. Explorer 35 was the companion spacecraft to Explorer 33 in the Anchored IMP program, but Explorer 34 (IMP-F) was the next spacecraft to fly, launching about two months before AIMP-E, both in 1967.

Small Astronomy Satellite 2

The Small Astronomy Satellite 2, also known also as SAS-2, SAS B or Explorer 48, was a NASA gamma ray telescope. It was launched on 15 November 1972 into the low Earth orbit with a periapsis of 443 km and an apoapsis of 632 km. It completed its observations on 8 June 1973.

Pegasus 2

Pegasus 2 or Pegasus II, known before launch as Pegasus B was an American satellite which was launched in 1965 to study micrometeoroid impacts in Low Earth orbit. It was the second of three Pegasus satellites to be launched, following the launch of Pegasus 1 three months earlier. The Pegasus spacecraft were manufactured by Fairchild Hiller, and operated by NASA.

Pegasus 3 American satellite

Pegasus 3 or III, also known as Pegasus C before launch, was an American satellite which was launched in 1965 to study micrometeoroid impacts in Low Earth orbit. It was the last of three Pegasus satellites to be launched, the previous two having been launched earlier the same year. It was manufactured by Fairchild Hiller, and operated by NASA.

Explorer 12 NASA satellite of the Explorer program

Explorer 12, also called EPE-A or Energetic Particles Explorer-A and as S3), was a NASA satellite built to measure the solar wind, cosmic rays, and the Earth's magnetic field. It was the first of the S-3 series of spacecraft, which also included Explorer 12, 14, 15, and 26. It was launched on 16 August 1961, aboard a Thor-Delta launch vehicle. It ceased transmitting on 6 December 1961 due to power failure.

Explorer S-46 (satellite) NASA satellite of the Explorer program

Explorer S-46 was a NASA satellite with a mass of 41 kg (90 lb). It was the last of the original series of Explorer satellites built, designed, and operated by the Jet Propulsion Laboratory and Army Ballistic Missile Agency (ABMA).

Explorer S-55 (satellite) NASA satellite of the Explorer program

Explorer S-55 was an American satellite launched by NASA on 30 June 1961, as part of the Explorer program. Explorer S-55, was launched using a Scout X-1 launch vehicle from the Wallops Flight Facility (WFF). Its mission was to evaluate the launch vehicle, and investigate micrometeoroid impact and penetration. The mission failed because the third stage failed to ignite and the spacecraft did not achieve orbit.

Explorer 16 NASA satellite of the Explorer program

Explorer 16, also called S-55B, was a NASA satellite launched as part of the Explorer program. Explorer 16 was launched on 16 December 1962, at 14:33:04 GMT, from Wallops Flight Facility, Virginia, with a Scout X-3.

Explorer 23 NASA satellite of the Explorer program

Explorer 23 was the last of three S-55 NASA micrometeoroid satellites launched as part of the Explorer program. Its purpose was to obtain data on the near-earth meteoroid environment, thus providing an accurate estimate of the probability of penetration in spacecraft structures by meteoroids and allowing a more confident definition of the penetration flux-material thickness relation to be derived.

Explorer 25 NASA satellite of the Explorer program

Explorer 25, was a NASA magnetically aligned satellite launched simultaneously with Explorer 24 (AD-B) using a Scout X-4 launch vehicle. This was NASA's first dual-satellite launch. The satellite's primary mission was to make measurements of the influx of energetic particles into the atmosphere of Earth and to study atmospheric heating and the increase in scale height which have been correlated with geomagnetic activity. Studies of the natural and artificial trapped Van Allen radiation belts were also conducted. A biaxial fluxgate magnetometer was used to monitor the orientation of the spacecraft with respect to the local magnetic field.

Explorer 45 NASA satellite of the Explorer program

Explorer 45 was a NASA satellite launched as part of Explorer program. Explorer 45 was the only one to be released from the program Small Scientific Satellite.

Explorer 46 NASA satellite of the Explorer program

Explorer 46,, was a NASA satellite launched as part of Explorer program.

Explorer 48 NASA satellite of the Explorer program

Explorer 48 was a satellite launched specifically for the purpose of X-ray astronomy of the NASA. It was also known as the SAS-B, SAS-2.

References

  1. 1 2 "Launch Log". Jonathan's Space Report. 21 July 2021. Retrieved 6 November 2021.
  2. 1 2 3 4 "Display: Explorer 13 (S-55A)". NASA. 28 October 2021. Retrieved 5 November 2021.PD-icon.svgThis article incorporates text from this source, which is in the public domain .
  3. "Experiment: Cadmium Sulfide Cell Micrometeorite Detector". NASA. 28 October 2021. Retrieved 5 November 2021.PD-icon.svgThis article incorporates text from this source, which is in the public domain .
  4. "Experiment: Copper Wire Micrometeroite Detector". NASA. 28 October 2021. Retrieved 5 November 2021.PD-icon.svgThis article incorporates text from this source, which is in the public domain .
  5. "Experiment: Impact Detection". NASA. 28 October 2021. Retrieved 5 November 2021.PD-icon.svgThis article incorporates text from this source, which is in the public domain .
  6. "Experiment: Pressurized Cell Micrometeorite Detector". NASA. 28 October 2021. Retrieved 5 November 2021.PD-icon.svgThis article incorporates text from this source, which is in the public domain .