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TIROS-4

Summary

TIROS 4 (also called TIROS-D and A9) was a spin-stabilized meteorological satellite. It was the fourth in a series of Television Infrared Observation Satellites.

TIROS-4
Image of TIROS-4.
Mission typeWeather satellite
OperatorNASA
Harvard designation1962 β 1
COSPAR ID1962-002A Edit this at Wikidata
SATCAT no.226
Mission duration6 months
Spacecraft properties
Spacecraft typeTIROS
ManufacturerRCA Astro / GSFC
Launch mass129.3 kilograms (285 lb)[1]
Start of mission
Launch dateFebruary 8, 1962, 12:29 (1962-02-08UTC12:29Z) UTC[2]
RocketThor-Delta
Launch siteCape Canaveral LC-17A
End of mission
Last contactJune 30, 1962 (1962-07-01)
Orbital parameters
Reference systemGeocentric
RegimeLow Earth
Eccentricity0.00894[1]
Perigee altitude712 kilometers (442 mi)[1]
Apogee altitude840 kilometers (520 mi)[1]
Inclination48.3°[1]
Period100 minutes[1]
EpochFebruary 8, 1962[1]
Instruments
Low Resolution Omnidirectional Radiometer
Widefield Radiometer
Scanning Radiometer
Television Camera System
← TIROS-3
TIROS-5 →
 

Launch edit

TIROS 4 was launched on February 8, 1962, by a Thor-Delta rocket from Cape Canaveral Air Force Station, Florida. The spacecraft functioned nominally until June 30, 1962. The satellite orbited the Earth once every 1 hour and 30 minutes, at an inclination of 48.3°. Its perigee was 712 kilometers (442 mi) and apogee was 840 kilometers (520 mi).[1]

Mission edit

The satellite was in the form of an 18-sided right prism, 107 cm in diameter and 56 cm high. The top and sides of the spacecraft were covered with approximately 9000 1- by 2-cm silicon solar cells. It was equipped with two independent television camera subsystems for taking cloud cover pictures and three radiometers (two-channel low-resolution, omnidirectional, and five-channel scanning) for measuring radiation from the Earth and its atmosphere. The satellite spin rate was maintained between 8 and 12 rpm by the use of five diametrically opposed pairs of small solid-fuel thrusters.

The TIROS-4 spin axis could be oriented to within 1° to 2° accuracy by use of a magnetic control device consisting of 250 cores of wire wound around the outer surface of the spacecraft. The interaction between the induced magnetic field in the spacecraft and the Earth's magnetic field provided the necessary torque for attitude control. The flight control system also optimized the performance of the solar cells and television cameras and protected the 5 channel infrared radiometer from prolonged exposure to direct sunlight.

With the exception of the degraded response of the 5 channel scanning radiometer, the spacecraft performed normally until May 3, 1962, when one camera failed. On June 10, 1962, the other camera's tape recorder failed. The scanning radiometer provided usable data until June 30, 1962.[3][4]

References edit

  1. ^ a b c d e f g h "TIROS 4". National Space Science Data Center. Retrieved June 4, 2018.   This article incorporates text from this source, which is in the public domain.
  2. ^ McDowell, Jonathan. "Launch Log". Jonathan's Space Page. Retrieved June 4, 2018.
  3. ^ "TIROS 4 (1962-004A)". NASA Goddard Space Flight Center. Retrieved June 4, 2018.
  4. ^ Journal of the British Interplanetary Society, Vol. 19, pags. 386-409, 1963-1964

External links edit

  • TIROS. Encyclopedia Astronautica
  • Real Time Satellite Tracking - TIROS 4. N2yo.com.