The TSX-5 satellite
AIR FORCE FACT SHEET
Posted: June 6, 2000
The TSX-5 spacecraft orbit will be elliptical with a 410 km (221 Nmi) periapsis and 1750 km (994 Nmi) apoapsis. Orbit inclination is 69 degrees with a TBD descending node. TSX-5 will be launched in April 2000 aboard an Orbital Science Corporation Pegasus XL launch vehicle. The TSX-5 space vehicle flight configuration is shown in the figure below, TSX-5 Space Vehicle. Four major physical attributes dominate the space vehicle external configuration: the spacecraft or core module, the separation system, the STRV-2 Experiment Module (EM), and the fixed geometry solar arrays.
The spacecraft primary structure is a nominal 37.5 inch (0.95 m) point-to-point 12-sided structure which provides the required strength to carry launch and handling loads. This all aluminum structure consists of a honeycomb core plate with sheet metal panels mounted to milled longerons or stringrers. The 32.40 inch (0.82 m) long STRV-2 payload is mounted to the top of the spacecraft structure. A 38.00 inch (0.97 m) diameter marman ring and V-band separation system which attaches the space vehicle to the launch vehicle, transfers launch loads between the space vehicle and launch vehicle, and permits space vehicle separation from the launch vehicle following orbit insertion. The separation system is composed of a marman band/attach ring assembly, externally mounted pyrotechnic bolt cutters, separation springs, and electrical separation connectors. The total in-flight space vehicle weight is nominally 550 lbs (249.5 kg).
Space vehicle subsystems and payloads are designed for a six (6) month mission life with a one (1) year goal, and reliability exceeding 90%. The spacecraft subsystems include an electrical power subsystem (EPS), a command and data handling subsystem (C&DH), a communications subsystem (COMMS), and an attitude determination and control subsystem (ADACS). Subsystem electronic components and the CEASE experiment are mounted internal to the spacecraft on the -X or wake oriented Core Plate.
Space Test Research Vehicle-2
Additional objectives of the STRV-2 experiments Space Active Modular Materials Experiment System SAMMES, Vibration, Isolation, Suppression and Steering System VISS, All Composite Experiment Spacecraft Structure ACESS , and the Engineering Test Bed (ETB) (which includes the Meteroid & Debris Impact Monitor and the Meteorid Impact Sensor) include characterization of the space environment (radiation, micrometeoroid and debris) at altitudes relevant to Brilliant Eyes, vibration isolation and suppression, assessment of contamination transport and effects aboard a low-cost satellite, and demonstration of a modular architecture for autonomous command, control and data handling. The minimum success criteria for STRV-2 include collection of IR background data for phenomenological analysis, demonstration of laser communication downlink, demonstration of vibration isolation and suppression technology, and collecting six months data on the space environment and its effects on candidate components.
Compact Environmental Anomaly Sensor
TSX-5 is expected to be the first flight of CEASE, and thus is primarily a proof of concept flight to ensure that the instrument functions as designed. Therefore, for TSX-5, CEASE's minimum success criteria is to deliver a fully integrated and tested CEASE instrument package for rapid spacecraft integration, and obtain background data for six months on the space environment and its effects on candidate components. In addition, it is desired that CEASE collect data for as long as possible on-orbit, preferably until the end of spacecraft life.
Flight data file
Vehicle: Pegasus XL
Launch date: June 6, 2000
Launch window: 1257-1355 GMT (8:57-9:55 a.m. EDT)
Launch site: Over Pacific Ocean
Launch preview - Our story describing the launch and TSX-5 satellite's mission.
Launch timeline - Chart with times and descriptions of events to occur during the launch.
Pegasus XL vehicle data - Overview of the rocket that will launch TSX-5 into space.
MISSION STATUS CENTER