초록 ▼

A forebody flow control system and more particularly an aircraft or missile flow control system for enhanced maneuverability and stabilization utilizes various types of sensors and various types of activatable flow effectors to maneuver the aircraft or missile with the help of a control system. A me

A forebody flow control system and more particularly an aircraft or missile flow control system for enhanced maneuverability and stabilization utilizes various types of sensors and various types of activatable flow effectors to maneuver the aircraft or missile with the help of a control system. A method of operating the flow control system is also disclosed.

대표청구항 ▼

1. A flow control system for a missile or aircraft forebody comprising a. at least one activatable micro-vortex generator;b. at least one sensor generating a signal, the at least one sensor being used to maneuver the missile or aircraft;c. an inertial measurement unit having an output; andd. a close

1. A flow control system for a missile or aircraft forebody comprising a. at least one activatable micro-vortex generator;b. at least one sensor generating a signal, the at least one sensor being used to maneuver the missile or aircraft;c. an inertial measurement unit having an output; andd. a closed loop control system;wherein the closed loop control system is used for activating and deactivating the at least one micro-vortex generator based at least in part on the signal of the at least one sensor and the output of the inertial measurement unit. 2. The flow control system in claim 1, comprising at least four activatable micro-vortex generators. 3. The flow control system in claim 1, comprising at least six activatable micro-vortex generators wherein the at least six activatable micro-vortex generators are positioned and separated substantially equidistantly about a center of the forebody of the missile or aircraft. 4. The flow control system in claim 1, wherein the micro-vortex generator is capable of being activated and deactivated at frequencies of at least 1 Hz. 5. The flow control system in claim 1, wherein the micro-vortex generator is capable of being activated and deactivated at frequencies of at least 20 Hz. 6. The flow control system in claim 5, wherein the closed loop control system activates and deactivates the at least one micro-vortex generator to create additional side forces on the missile or aircraft forebody. 7. The flow control system in claim 1, wherein the closed loop control system activates and deactivates the at least one micro-vortex generator to create commanded side forces on the missile or aircraft forebody. 8. A method of stabilization for a missile or aircraft forebody comprising the steps of a. estimating or determining a need to stabilize a missile or an aircraft based at least in part on a signal from at least one sensor used to stabilize the missile or aircraft; the missile or aircraft forebody further comprising at least one activatable micro-vortex generator and a closed loop control system for controlling the at least one micro-vortex generator;b. activating the at least one micro-vortex generator to create commanded side forces by oscillation of the at least one micro-vortex generator with the closed loop controller based on at least in part the signal of the at least sensor;c. re-estimating or determining the side forces required to stabilize the missile or aircraft based at least in part on a signal from the at least one sensor; andd. deactivating the at least one micro-vortex generator in response to reduced need for commanded side forces. 9. The method of stabilization in claim 8, wherein the at least one micro-vortex generator is activated by oscillating the at least one micro-vortex generator. 10. The method of stabilization in claim 8, wherein the least one activatable micro-vortex generator comprises at least six activatable micro-vortex generators wherein the at least six activatable micro-vortex generators are positioned and separated substantially equidistantly about a center of the forebody of the missile or aircraft. 11. The method of stabilization in claim 8, wherein the forebody of the missile or aircraft is designed with asymmetries in the forebody. 12. The method of stabilization in claim 8, wherein the aircraft or missile is a munition fired with artillery. 13. The method of stabilization in claim 8, wherein the at least one micro-vortex generator is a deployable micro-vortex generator.