Session
Technical Session III: Advanced Sensor Concepts
Abstract
Scheduled for a June 2001 launch, the Microwave Anisotropy Probe’s (MAP) mission is to study in detail the cosmic microwave background radiation temperature fluctuations of the universe. The cosmic microwave background is the remnant afterglow of the Big Bang, and the tiny temperature differences from place to place on the sky provides a wealth of information about the basic nature of our universe. The observatory consists of dual back-to-back Gregorian optics and dual differential pseudo-correlation microwave radiometers. MAP will scan the sky over a 22 to 90 Ghz spectrum during a 26 month mission at L2. To achieve the necessary dimensional stability and stringent total weight limits, the Thermal Reflector System (TRS) consists of dual primary and secondary lightweight composite reflectors mounted to a lightweight but rigid composite truss structure. Design features include the use of lightweight graphite spread fabric and honeycomb core for the reflector shells and stiffening structure, and a bonded mortise and tenon truss structure using two complementary composite materials. Qualification of the TRS included in-situ photogrammetry measurements while at 40K and 370K, sine burst and sine sweep dynamic loading, and acoustic excitation. Materials employed, coupon test data, design and construction, and qualification testing will be discussed.
Thermal Reflector System Design and Testing for the Microwave Anisotropy Probe
Scheduled for a June 2001 launch, the Microwave Anisotropy Probe’s (MAP) mission is to study in detail the cosmic microwave background radiation temperature fluctuations of the universe. The cosmic microwave background is the remnant afterglow of the Big Bang, and the tiny temperature differences from place to place on the sky provides a wealth of information about the basic nature of our universe. The observatory consists of dual back-to-back Gregorian optics and dual differential pseudo-correlation microwave radiometers. MAP will scan the sky over a 22 to 90 Ghz spectrum during a 26 month mission at L2. To achieve the necessary dimensional stability and stringent total weight limits, the Thermal Reflector System (TRS) consists of dual primary and secondary lightweight composite reflectors mounted to a lightweight but rigid composite truss structure. Design features include the use of lightweight graphite spread fabric and honeycomb core for the reflector shells and stiffening structure, and a bonded mortise and tenon truss structure using two complementary composite materials. Qualification of the TRS included in-situ photogrammetry measurements while at 40K and 370K, sine burst and sine sweep dynamic loading, and acoustic excitation. Materials employed, coupon test data, design and construction, and qualification testing will be discussed.
