초록 ▼

The present invention relates to a forebody flow control system and more particularly to aircraft or missile flow control system for enhanced maneuverability and stabilization at high angles of attack. The present invention further relates to a method of operating the flow control system. In one emb

The present invention relates to a forebody flow control system and more particularly to aircraft or missile flow control system for enhanced maneuverability and stabilization at high angles of attack. The present invention further relates to a method of operating the flow control system. In one embodiment, the present invention includes a missile or aircraft comprising an afterbody and a forebody; at least one deployable flow effector on the missile or aircraft forebody; at least one sensors each having a signal, the at least one sensor being positioned to detect flow separation on the missile or aircraft forebody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one deployable flow effector based on at least in part the signal of the at least one sensor.

대표청구항 ▼

The present invention relates to a forebody flow control system and more particularly to aircraft or missile flow control system for enhanced maneuverability and stabilization at high angles of attack. The present invention further relates to a method of operating the flow control system. In one emb

The present invention relates to a forebody flow control system and more particularly to aircraft or missile flow control system for enhanced maneuverability and stabilization at high angles of attack. The present invention further relates to a method of operating the flow control system. In one embodiment, the present invention includes a missile or aircraft comprising an afterbody and a forebody; at least one deployable flow effector on the missile or aircraft forebody; at least one sensors each having a signal, the at least one sensor being positioned to detect flow separation on the missile or aircraft forebody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one deployable flow effector based on at least in part the signal of the at least one sensor. one of the load tapes, and pulls the load tape toward an inside of the gasbag to deform the gasbag when the gasbag is in the fully inflated state, so that the volume of the gasbag changes. 3. A balloon according to claim 2, wherein each of the spindle-shaped gores has opposite first and second ends, and the gasbag includes a first section having the first ends of the gores and a second section having the second ends of the gores, and the set of the load tapes includes two pulling parts which are pulled toward the inside of the gasbag by the volume changing mechanism, and the two pulling parts are fitted to the first and second sections, respectively, and the volume changing mechanism pulls the pulling parts to change a distance between the first and second sections. 4. A balloon according to claim 3, wherein the volume changing mechanism includes: a pulling rope attached to one of the two pulling parts, and a rope-length regulation mechanism which is attached to the other pulling part and changes a length of the pulling rope, and the pulling rope extends between the one pulling part and the rope-length regulation mechanism, and the rope-length regulation mechanism changes the length of the pulling rope to change a distance between the two pulling parts. 5. A balloon according to claim 2, wherein at least one of the load tapes includes a pulling part which is pulled toward the inside of the gasbag by the volume changing mechanism, and the pulling part of the load tape is fitted to the gore adjacent to the load tape at a longitudinal middle part of the gore. 6. A balloon according to claim 5, wherein the volume changing mechanism includes: at least one pulling rope attached to at least one of the load tapes at the pulling part, respectively, and a rope-length regulation mechanism which is arranged in the inside of the gasbag and changes a length of the pulling rope, and the pulling rope extends between the pulling part and the rope-length regulation mechanism, and the rope-length regulation mechanism changes the length of the pulling rope to change a distance between the pulling part and the rope-length regulation mechanism. 7. A balloon according to claim 5, wherein each of at least two of the load tapes includes the pulling part, and the volume changing mechanism includes: a pulling rope attached to and passing through each of the pulling parts, and a rope-length regulation mechanism which changes a length of the pulling rope to change a distance between adjacent pulling parts.