Guidance and Control of a Fin-Stabilized Projectile Based on Flight Dynamics with Reduced Sensor and Actuator Requirements
Abstract
Successfully guiding a projectile launched from a gun is an extremely challenging task. Striking a balance between performance and affordability requires innovative solutions. This effort introduces a unique guidance and control strategy, which enables precision and trajectory shaping with reduced sensor and actuator needs. The derivation of this guidance and control algorithm is based on flight dynamics. Flight experiments were conducted to verify that the algorithm guided the projectile to the target and demonstrate rapid application to different airframes. Features of the algorithm, such as expected precision, maneuver conservation, and trajectory shaping, were investigated through modeling and simulation. Position bias errors drove the precision; errors due to the guidance and control algorithm were on the order of 0.1 m. An analysis was conducted on the lateral acceleration available from the airframe, lateral acceleration required for this algorithm, and lateral acceleration required for classic proportional navigation. For control authority-limited munitions, proportional navigation was unable to intercept the target point while the current guidance algorithm successfully hit the target. Steepening the angle-of-fall to vertical is possible with this algorithm provided the airframe possesses the necessary maneuverability.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 2011
- Accession Number
- ADA539868
Entities
People
- Frank E. Fresconi
Organizations
- United States Army Research Laboratory