Navigation, Guidance and Control For the CICADA Expendable Micro Air Vehicle
نویسندگان
چکیده
The CICADA (Close-in Covert Autonomous Disposable Aircraft) is a new and novel micro air vehicle design based on a monolithic circuit-board/structure. The CICADA is a glider which once dropped from a host vehicle will automatically fly to a preprogrammed recovery waypoint. A key design goal for the guidance and control system was to enable the CICADA to recover from a wide range of initial launch conditions and altitudes. Recording temperature and wind profile data during the decent was also a design objective. This paper will describe the navigation, guidance, flight control, and environmental control developed for this simple yet capable aircraft. Flight test data will be presented showing the performance of the CICADA vehicle from a drop of over 29,000 feet in altitude.
منابع مشابه
Single Seven State Discrete Time Extended Kalman Filter for Micro Air Vehicle
The term Micro Air Vehicles (MAVs) is used for a new type of remotely controlled, semi-autonomous or autonomous aircraft that is significantly smaller than conventional aircrafts. To apply Micro Electro Mechanical Systems (MEMS) inertial sensors for the Guidance, Navigation and Control (GNC) of Micro Air Vehicle (MAV) is an extremely challenging area. The major components of the control system ...
متن کاملLow-cost Image-assisted Inertial Navigation System for a Micro Air Vehicle
The increasing civilian demand for autonomous aerial vehicle platforms in both hobby and professional markets has resulted in an abundance of inexpensive inertial navigation systems and hardware. Many of these systems lack full autonomy, relying on the pilot’s guidance with the assistance of inertial sensors for guidance. Autonomous systems depend heavily on the use of a global positioning sate...
متن کاملIntegrated fuzzy guidance law for high maneuvering targets based on proportional navigation guidance
An integrated fuzzy guidance (IFG) law for a surface to air homing missile is introduced. The introduced approach is a modification of the well-known proportional navigation guidance (PNG) law. The IFG law enables the missile to approach a high maneuvering target while trying to minimize control effort as well as miss-distance in a two-stage flight. In the first stage, while the missile is far ...
متن کاملDesign and Experimental Evaluation of integrated orientation estimation algorithm Autonomous Underwater Vehicle Based on Indirect Complementary Filter
This paper aims is to design an integrated navigation system constituted by low-cost inertial sensors to estimate the orientation of an Autonomous Underwater Vehicle (AUV) during all phases of under water and surface missions. The proposed approach relied on global positioning system, inertial measurement unit (accelerometer & rate gyro), magnetometer and complementary filter technique. Complem...
متن کاملA Comprehensive Approach to Develop a Continuous Fuzzy Guidance Law for Maneuvering Targets
Based on the idea of Continuous Fuzzy Guidance Law (CFGL), a andldquo;three-phase fuzzy guidanceandrdquo; (TFG) law is proposed for the class of surface to air homing missiles. The current approach enables the guidance law to track a maneuvering target from the beginning of the launch phase up to the terminal one while itdynamically attempts to keep miss-distance, flight time and control effort...
متن کامل