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TIROS 10

NSSDCA/COSPAR ID: 1965-051A

Description

TIROS 10 (Television and InfraRed Observation Satellite) was a sun-synchronous meteorological spacecraft designed to develop improved capabilities for obtaining and using TV cloudcover pictures from satellites and operated as an interim operational satellite. The spin-stabilized spacecraft was in the form of an 18-sided right prism, 107 cm across opposite corners and 56 cm high, with a reinforced baseplate carrying most of the subsystems and a cover assembly (hat). Electrial power was supplied to the spacecraft by approximately 9000 1- by 2-cm silicon solar cells that were mounted on the cover assembly and by 21 nickel-cadmium batteries. A single monopole antenna for reception of ground commands extended from the top of the cover assembly. A pair of crossed-dipole telemetry antennas (235 MHz) projected down and diagonally out from the baseplate. Mounted around the edge of the baseplate were five diametrically opposed pairs of small solid-fuel thrusters that maintained the satellite spin rate between 8 and 12 rpm. Proper attitude was maintained to within a 1- to 2-deg accuracy by use of a magnetic control device consisting of 250 coils of wire wound around the outer surface of the spacecraft. The interaction by the induced magnetic field in the spacecraft and the earth's magnetic field provided the torque necessary for attitude control. The satellite spin axis could thus be varied while the satellite remained in the conventional TIROS 'axial' mode. The satellite was equipped with two identical wide-angle TV cameras with 1.27-cm vidicon for taking earth cloudcover pictures. The pictures could be transmitted directly to either of two ground receiving stations or stored in a tape recorder on board for subsequent playback if the spacecraft was beyond the communication range of the station. The satellite was launched into a near-polar orbit and successfully provided TV coverage of the entire daylight portion of the globe. The TV system operated normally until September 30, 1965, and sporadically through July 31, 1966, when the spacecraft was deactivated.

Alternate Names

  • OT 1
  • 01430

Facts in Brief

Launch Date: 1965-07-02
Launch Vehicle: Delta
Launch Site: Cape Canaveral, United States
Mass: 127.0 kg

Funding Agency

  • NASA-Office of Space Science Applications (United States)

Discipline

  • Earth Science

Additional Information

Questions or comments about this spacecraft can be directed to: Coordinated Request and User Support Office.

 

Personnel

NameRoleOriginal AffiliationE-mail
Mr. R. M. RadosProject ManagerNASA Goddard Space Flight Center 
Dr. Morris TepperProgram ScientistNASA Goddard Space Flight Center 
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