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Tactical ballistic missiles (TBM) target may experience severe spiral maneuvers as they reenter the earth's atmosphere due to a configurational asymmetry. To hit these targets, the interceptor must possess extremely fast maneuver response characteristics. Before 10 secs to go optimal integrated guidance and control (OIGC) is slightly better than a conventional autopilot. From 2 to 10 secs OIGC is much better than a conventional autopilot in closing up trajectories. However, with 2 secs to go, OIGC uses up full authority and with the aerodynamic surfaces alone may not catch the tactical ballistic missile target. Therefore, there is a need for thrusters. In this paper, a blending mechanism of optimal integrated guidance and control (OIGC) and fuzzy logic controlled thruster is developed for a skid-to-turn missile to improve the missile interception performance. OIGC is an innovative approach to designing guidance and control laws.

This paper will report US Navy submarine philosophy and test experience with the emergency atmosphere control system. A vital aspect of emergency recovery within contained environments is the ability to maintain life while directing escape or awaiting rescue. Emergency atmosphere control differs from primary life support in several key areas. The primary atmosphere control system provides a habitable atmosphere so that the crew can live comfortably and work efficiently in an enclosed environment. Additionally the primary atmosphere control system controls chronic and acute toxicants to minimize both short and long term health consequences. For long duration missions, primary atmosphere control is generally regenerative and may include redundant components for reliability. The emergency life support system replaces the primary system in the event of a catastrophic failure.

In this paper, an intelligent autonomous deck landing system is designed for an Unmanned Air Vehicle (UAV). First, the design specifications and requirements are identified for the design of UAV flight control and landing systems. Then the longitudinal models of the UAV are established for the design of an autonomous UAV landing system. The system is designed using fuzzy logic, which is able to provide longitudinal stability and to improve the tracking performance. Simulation results show that the developed landing control system has very good robustness against aerodynamic uncertainty, and good fault tolerance against actuator failures. This indicates that the intelligent landing system has the ability to stabilize a damaged aircraft without knowledge of the types of fault or system parameters. Wind disturbances are also investigated by using the turbulence model for the ship-landing environment.