Sensor Test for Orion Relative Navigation Risk Mitigation - DTO 703 (STORRM) - 01.09.14
Science Objectives for Everyone Sensor Test for Orion Relative Navigation Risk Mitigation - DTO 703 (STORRM) tests the Vision Navigation Sensor, Star Tracker, and Docking Camera planned for Orion both during shuttle approach to and departure from the ISS. This test determines how well the navigation system performs during the mission.
Science Results for Everyone Information Pending
Ball Aerospace Technology Corporation, Boulder, CO, United States
Sponsoring Space Agency
National Aeronautics and Space Administration (NASA)
Human Exploration and Operations Mission Directorate (HEOMD)
ISS Expedition Duration:
Previous ISS Missions
This is the first mission to use the Vision Navigation Sensor part of STORRM. The Star Tracker has flown in previous missions, although not in this configuration.
- The Vision Navigation Sensor is a new development and has never flown in space. It is critical to test this hardware prior to attempting a Crew Exploration Vehicle (CEV) rendezvous and docking with the ISS, as the navigation sensors have historically experienced problems on orbit that were not discovered during ground testing.
- Understanding the Vision Navigation Sensor?s on-orbit performance is critical for validating ground simulation models and properly characterizing sensor performance. Testing these sensors in space provides data in critical areas that cannot be tested or proven on the ground.
- STORRM will collect and store raw image and telemetry data from the Vision Navigation Sensor, Star Tracker and the Docking Camera to focus on testing the range, range rate, bearing, and attitude that are many orders of magnitude larger on orbit than can be tested on the ground.
Sensor Test for Orion Relative Navigation Risk Mitigation - DTO 703 (STORRM) hardware will be hard mounted in two locations. The Vision Navigation Sensor and Docking Camera will be mounted on the existing unused Trajectory Control System (TCS) on the Orbiter Docking System (ODS) Truss. The Star Tracker and data interface controller will be mounted on an Orbiter sidewall carrier in the orbiter Payload. The Star Tracker has not yet flown in this configuration and STORRM will allow data to test the new centroiding (center of mass) algorithm software. Data will be collected during rendezvous, departure, flyover and re-rendezvous with the ISS. A Payload General Support Computer (PGSC) will provide experiment control, data processing, and limited data recording.
STORRM demonstrates and characterizes on-orbit performance of new navigation system technology prior to the first Orion mission to ISS.
Results allow for improved math models and design of future hardware.
One crewmember sets up for operations, activates and deactivates the system. This crewmember is required to view data in real time to determine whether all three sensors are performing nominally during rendezvous, approach, docking, undocking, flyover, and rendezvous. If required, the crewmember executes procedures or sends manual commands to the DTO avionics for corrective actions. Crew action is required to activate data recording systems during approach/docking and during undocking and rendezvous. The PGSC is operated by a crewmember using a custom software interface. External power is controlled and applied via Standard Switch Panel or similar. Ground personnel has the capability to downlink data and uplink files to the PGSC when necessary.
Upon initial approach and docking to ISS, one crewmember applies heater power to sensors in the Payload Bay (PLB) once PLB doors are opened. The crewmember then sets up the PGSC, initializes software and applies power to the sensors. At this point operation and data acquisition commences. Monitoring the PGSC occurs at periodic intervals in order to verify sensor performance, and possibly send troubleshooting commands. After docking, power is removed from the sensors and operations and data acquisition cease. Prior to undocking, power is applied to the sensors and operation and data acquisition commence. Monitoring the PGSC occurs at periodic intervals in order to verify sensor performance, and possibly send troubleshooting commands. After rendezvous power is once again removed from the sensors and operation and data acquisition ceases. The PGSC is stowed. Heater power to the sensors and avionics in the PLB is removed once the PLB doors close.
The Space Shuttle Orbiter Trajectory Control Sensor (TCS) interference testing is complete (Photo right and below). The testing consisted of four reflective elements that are being considered for use on the STORRM DTO (DTO 703). The purpose of the testing was to ensure that the reflective elements, which are required for the DTO, did not interfere or cause any unwarranted operation of the Shuttle TCS. The laser and detector for the TCS are designed for the visible spectrum as compared to the STORRM Vision Navigation System designed for the near infra-red spectrum. Preliminary results eliminate the concern that the DTO reflective elements will interfere with TCS operations. DTO 703 will collect data from the Vision Navigation Sensor and Docking Camera during Orbiter Operations. The Reflective Elements will launch of STS-132 (May 14, 2010) and be installed via IVA on the PMA-2 docking target following Shuttle docking. The STORRM Sensor Enclosure, which will launch on STS-134 (July 29, 2010), will be mounted on the Orbiter Docking System (ODS) Truss and the Avionics Enclosure Assembly will be mounted on the Payload Bay 3 sidewall. Data will be sent to a laptop in the crew cabin.
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