NASA Flight Termination System (FTS) Design Requirements


FTS Design

- FTS must render each power stage and / or any other propulsion system, including any that are part of a payload, non-propulsive
- If flight analysis determines the public is not endangered, an FTS may not be required

Good FTS Design Features include:
- Redundancy
- Physical separation of redundant strings
- Independence from other vehicle systems
- Inadvertent separation destruct system when solid rocket motors used
- Both engine shutdown and destruct capability on liquid fueled vehicles
- Feathers that allow complete and thorough (end-to-end) testing
Test Requirements for approval of FTS
- Component level: Qualification, acceptance and lot testing
- System level: Pre-launch confidence tests and end-to-end verification
- Typical components of an Airbourne FTS

NASA Flight Termination System Design Requirements

FTS Ground Systems consist of redundant UHF transmitters capable of sending command destruct signals
FTS reliability goal: 0.999 @ 95% confidence
Considerations during design – all these directly influence Ec
Reliability – Hardware / software failure rates and redundancy | Propellants – Affects blast and toxic analyses and ground hazards | Trajectories – Affects “at risk” population | Range selection – Affects ground, sea and air hazard zones