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Overview

Flight Termination Systems provide a fully redundant explosive assembly capable of terminating the flight of airborne missiles or launch vehicles when they veer from their targeted path. Systems have been designed and developed to sever structures, to create aerodynamic instability, for motor destruction, or destruction of other major vehicle elements. Flight Termination Systems typically utilize Flexible Confined Detonating Cord Assemblies for initial ignition (via a Safe and Arm Device), manifold assemblies and an output charge, typically Linear Shape Charge Assemblies (LSCA) or bulk charges.

Application

There are numerous applications where Flight Termination Systems are required. Launch vehicles typically require FTS with both command and inadvertent separation initiation capability. Frequently, tactical missile systems under development require FTS systems during range testing, and subsequently may be required during "fly to buy" testing.

Various output charge configurations are used to meet different termination and vehicle configuration requirements.

Longitudinal sections of Linear Shaped Charge are normally used to sever large solid motor cases or large liquid fuel tanks. Subsequent burn through and rupture of the tanks or venting of the solid rocket motor creates termination of thrust. Typically, large coreload LSC is used in these applications.

Dome cutting systems are typically used on smaller vehicles to vent motor cases. Again, Linear Shaped Charge is typically assembled in a ring configuration to sever the dome of the motor casing.

Bulk charges can be used in a similar fashion to the dome cutting system for larger vehicles. Venting of fuel/oxidizer tanks by a bulk charge can create a mass explosion of the fuel tank, resulting in complete destruction of the flight vehicle.

In cases where the vehicle may have sufficient aerodynamic properties to allow significant downrange flight after venting of onboard fuels, it may be necessary to destroy the structure of the vehicle as well. Typically, an LSC assembly can be used to sever a significant structural member (such as a wing or an entire missile fuselage) to create aerodynamic instability and subsequent flight termination.

Additionally, system initiation must typically be accomplished in both command and inadvertent separation (i.e., mechanical) modes. For inadvertent separation conditions, a Lanyard Pull Initiator containing an integral pyrotechnic delay is used to achieve system initiation.

Design Considerations

Flight Termination Systems are typically designed for a specific application and set of requirements. EBA&D has extensive experience with a wide variety of FTS components, systems, and applications on launch vehicle, strategic, and tactical missile systems.

Range safety requirements for FTS components are extremely rigid, given the criticality of the system's function. Typical specification documents in the US include EWR-127- 1 and RCC-319, although individual program requirements may vary somewhat. Redundancy is a common requirement, and FTS are typically initiated using redundant explosive transfer lines, frequently with a block redundant initiation chain.

EBA&D has produced Flight Termination Systems that have been fully demonstrated and qualified for a broad range of applications and functional requirements.

The Devices Described in this section are:

  • Flight-Termination Charges
  • Thrust Termination
  • Bi-Directional Destruct Charge
  • Lanyard Pull Initiators (LPI)