Abstract: Systems and methods for model based vehicle navigation are provided. In one embodiment, a navigation system: a strapdown navigation processor; a propagator-estimator filter, the navigation processor configured to input inertial sensor data and navigation corrections from the filter to generate a navigation solution comprising a vehicle velocity estimate and a vehicle attitude estimate; a vehicle physics model configured to perform calculations utilizing dynamics equations for a rigid body. The model inputs 1) vehicle state estimates from the navigation solution and 2) platform inputs indicative of forces acting on a vehicle platform. The model outputs a set of three orthogonal predicted translational acceleration measurements based on the inputs.

Abstract: Model based inertial navigation for a spinning projectile is provided.

Abstract: Model based inertial navigation for a spinning projectile is provided.

Abstract: Systems and methods for model based vehicle navigation are provided. In one embodiment, a navigation system: a strapdown navigation processor; a propagator-estimator filter, the navigation processor configured to input inertial sensor data and navigation corrections from the filter to generate a navigation solution comprising a vehicle velocity estimate and a vehicle attitude estimate; a vehicle physics model configured to perform calculations utilizing dynamics equations for a rigid body. The model inputs 1) vehicle state estimates from the navigation solution and 2) platform inputs indicative of forces acting on a vehicle platform. The model outputs a set of three orthogonal predicted translational acceleration measurements based on the inputs.

Abstract: A method and an apparatus for controlling aircraft rudder movement are disclosed. The system including a yaw damping control portion integrated with a directional compensation rudder control portion, such that the system may simultaneously provide yaw damping control and directional compensation.

Abstract: An aircraft display system positions a synthetic runway which is properly aligned with a target runway even during crosswind approaches. The relative position of the target runway is computed in a manner which reduces the accumulated error associated with previous systems. The lateral deviation rate of the aircraft relative to the extended centerline of the target runway is computed from data provided by various aircraft navigation and sensor systems. A track error angle representative of the difference between the extended centerline of the runway and the ground track of the aircraft is computed from the lateral deviation rate and ground speed. Runway bearing relative to ground track is computed from the track error angle and lateral deviation angle. Compensating runway bearing relative to ground track with drift angle yields a runway bearing relative to aircraft heading which is useful for positioning a synthetic runway on a display.

Abstract: An aircraft display communicates three dimensional lateral information to a pilot of the aircraft. An extended course centerline symbol and lateral deviation marks indicate lateral deviation from a desired course along with approximate altitude and distance-to-go information to the pilot. The course centerline extends toward a vanishing point near the horizon line of the display. The centerline symbol swings laterally across the display responsive to changes in lateral deviation of the aircraft such that an intuitive perspective view is provided to the pilot. Lateral deviation marks provide precise lateral deviation information to the pilot. The display is adaptable to all phases of flight, but is particularly useful during the approach phase of flight. The preferred embodiment is on a head-up display for instrument flight conditions.