Badr-B

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Orbital elements
Badr-B
Image:Badr-B.jpg
Organisation	SUPARCO
Mission type	Earth Observation Satellite
Satellite of	Earth
Launch date	December 10, 2001, 17:19 UT
Carrier Rocket	Zenit-2
NSSDC ID	2001-056C
Mass	68.0 kg
Regime	Sun-synchronous orbit
Eccentricity	0.0018975332
Inclination	99.7°
Orbital period	105.0 minutes
Apoapsis	1,014.0 kilometres (630 mi)
Periapsis	986.0 kilometres (613 mi)

Badr-B was the name of Pakistan's second satellite that was launched on the 10th December, 2001 from Baikonur Cosmodrome, Kazakhstan^[1].

Pakistan’s second satellite BADR-B was launched on 10 Dec 2001 at 9:19 am from Baikonur Cosmodrome, Kazakhstan. The Zenit-2 rocket carried it into a 1018 km sun-synchronous circular orbit.

Badr-B was a small size Earth Observation Satellite designed by Space Innovations Limited (SIL) of the United Kingdom. Badr-B was a gravity gradient stabilised satellite. Although it was designed and manufactured by SIL, the satellite integration was performed in Pakistan by SUPARCO. Most of the equipment used in the satellite was acquired in Pakistan to stimulate the local software industry.

BADAR-B conducted four major on-board experiments:

   * Earth imaging
   * Use of radiation dosimeter
   * Data storage and forwarding
   * Charged battery experiment

Project Objectives

   * Developing low cost satellites and creating necessary infrastructure for future development of larger satellites
   * Acquisition of know-how and capability in the fields of satellite attitude control and stabilisation
   * Acquire know-how and technology for earth imaging by use of CCD sensors
   * Encourage and stimulate interest of the country’s academic and scientific community in the peaceful uses of space
   * Forging of closer links with counterpart agencies/organisations in other countries

Specifications

   * Satellite Dimension: 510mm x 510mm x 465mm
   * Satellite Mass: ~70kg
   * Lifetime: More than 2 years
   * Communication: Gravity gradient
   * Thermal control: Passive
   * Payloads: CCD cameras, Compact Dosimeter, End of Charge Detector and Store & Forward Experiment (SAFE)
   * Ground Segment: Telemetry, Tracking & Command Station (TT & C) and Mission Control Centre (MCC)

Configuration

The satellite structure was made of space qualified aluminum T-6 alloy. Gallium Arsenide (GaAs) solar arrays were used to provide power during the sunlit periods and Nickel Cadmium (NiCd) batteries during the eclipse periods. Earth pointing single axis stabilization was achieved by use of a 6 m gravity gradient boom with a trip mass of 4kg.