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NASA-LLIS-1609
Lessons Learned - Fin Actuator System/Logic Circuit Separation from High Current
Year: 2005
Abstract: Abstract:
Following the recommendations from the X43A Flight 1 MIB, the Pegasus actuator system was redesigned to accommodate the need for greater hinge torque. The analog-based legacy actuator system was redesigned for digital drive of the power output stage to the actuators, an additional actuator was incorporated to provide the necessary torque including margins, and the power supply was increased to provide the required 80+ amps, instead of the previous 40 amp capability.
Multiple failures during qualification testing, and the subsequent technical investigations, proved the lack of understanding between the ideal circuit operation and the impact of system implementation. Low-inductance ground and power planes/paths within (sub)systems are essential for proper operation.
Following the recommendations from the X43A Flight 1 MIB, the Pegasus actuator system was redesigned to accommodate the need for greater hinge torque. The analog-based legacy actuator system was redesigned for digital drive of the power output stage to the actuators, an additional actuator was incorporated to provide the necessary torque including margins, and the power supply was increased to provide the required 80+ amps, instead of the previous 40 amp capability.
Multiple failures during qualification testing, and the subsequent technical investigations, proved the lack of understanding between the ideal circuit operation and the impact of system implementation. Low-inductance ground and power planes/paths within (sub)systems are essential for proper operation.
Subject: Accident Investigation
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:31:27Z | |
| date available | 2017-09-04T18:31:27Z | |
| date copyright | 06/02/2005 | |
| date issued | 2005 | |
| identifier other | IYXCQCAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;query=author:%22NAVY%20-%206159DD6E273C9FCD0Facil/handle/yse/213690 | |
| description abstract | Abstract: Following the recommendations from the X43A Flight 1 MIB, the Pegasus actuator system was redesigned to accommodate the need for greater hinge torque. The analog-based legacy actuator system was redesigned for digital drive of the power output stage to the actuators, an additional actuator was incorporated to provide the necessary torque including margins, and the power supply was increased to provide the required 80+ amps, instead of the previous 40 amp capability. Multiple failures during qualification testing, and the subsequent technical investigations, proved the lack of understanding between the ideal circuit operation and the impact of system implementation. Low-inductance ground and power planes/paths within (sub)systems are essential for proper operation. | |
| language | English | |
| title | NASA-LLIS-1609 | num |
| title | Lessons Learned - Fin Actuator System/Logic Circuit Separation from High Current | en |
| type | standard | |
| page | 3 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;2005 | |
| contenttype | fulltext | |
| subject keywords | Accident Investigation | |
| subject keywords | Flight Equipment | |
| subject keywords | Hardware | |
| subject keywords | Safety & Mission Assurance | |
| subject keywords | Test & Verification |