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Explorer: HETE 2


The HETE-2 (High Energy Transient Explorer 2) is designed to detect cosmic gamma-ray bursts (GRBs) and help determine their origin and nature. It is a reflight of the HETE 1 mission, which was lost due to a launch vehicle separation failure.

Contrary to HETE 1, MIT built the satellite bus alos in-house.

The satellite has three instruments:

  • a set of wide-field gamma-ray (6 - 400 keV spectrometers (FREGATE);
  • a wide-field X-ray (2 - 25 keV monitor (WXM), and
  • a set of soft X-ray (0.5 - 10 keV cameras (SXC).

These instruments cover a solid angle of 1.5-2 steradians and will be used to make simultaneous, broad-band observations in the various listed energy ranges. The goal of the mission is to continuously scan the sky and identify occurences of GRBs, establish precise locations and transmit coordinates in near real time (< 10 seconds). The instruments will also be used to establish relative GRB rates and intensities in the soft X-ray, mid X-ray, and gamma-ray bands, perform spectroscopy of gamma-ray bursts in the energy range 1-400 keV. measure the intensities, time histories, and spectra of soft gamma-ray repeater bursts, X-ray bursts, and black hole X-ray transients.

The spacecraft is basically a rectangular cube, roughly one meter by half a meter by half a meter, with four solar panel petals protruding from the bottom. The bottom section of the spacecraft holds the power, communications, and attitude control and the upper section the science instruments. Power is supplied by the solar panels, which are made of honeycomb aluminum with a silicon substrate, each supplying 42 W. There are 6 battery packs, each containing 24 1.5 V NiCd cells, each with 1.2 A-hr capacity. Communication is via S-band uplink (2.092 GHz) and downlink (2.272 GHz) using 5 dual-patch antennas. A VHF downlink (137.9622 MHz) will be used for the real-time burst alerts via a whip antenna mounted on one of the solar panels. Attitude control is achieved by a momentum wheel and three orthogonal magnetic torque coils, controlled by inputs from two magnetometers, twelve sun sensors, and an optical camera.

The spacecraft will always be pointed in the anti-solar direction and all bursts detected will be at least 120 degrees from the Sun. The field of view will be centered roughly on the ecliptic. Over the course of a year approximately 60% of the sky will be surveyed. When GRB's are detected, summary burst data are sent immediately to listen-only equatorial ground stations and are forwarded to observers via the GRB coordinates network within less than 10 seconds of burst detection. The planned operating life is 18 months with probable mission extensions for an additional 6 months or more.

Nation: USA
Type / Application: Gamma ray astronomy
Operator: NASA
Contractors: MIT
Equipment: FREGATE, WXM, SXC
Propulsion: None
Power: 4 deployable fixed solar arrays, batteries
Lifetime: 1.5 years (planned), 7.5 years (achieved)
Mass: 124 kg
Orbit: 598 km × 641 km, 1.9 (#2)
Satellite COSPAR Date LS Launch Vehicle Remarks
HETE 2 (Explorer 79) 2000-061A 09.10.2000 Kw, L-1011, RW06/24 Pegasus-H
Further HETE missions:
Further Explorer Missions of Opportunity (MoO) and International Missions (Int):

Missions of Opportunity: International Missions: Explorer Program

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