Aircraft and missile afterbody flow control device and method of controlling flow
Number of patents in Portfolio can not be more than 2000
United States of America Patent
Stats
-
May 2, 2017
Issued Date -
N/A
app pub date -
Apr 27, 2012
filing date -
Jan 3, 2003
priority date (Note) -
In Force
status (Latency Note)
Importance
Abstract
An afterbody flow control system is used for aircraft or missile flow control to provide enhanced maneuverability and stabilization. A method of operating the flow control system is also described. The missile or aircraft comprises an afterbody and a forebody; at least one activatable flow effector on the missile or aircraft afterbody; at least one sensor having a signal, the at least one sensor being positioned to detect forces or flow conditions on the missile or aircraft afterbody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one activatable flow effector based on at least in part the signal of the at least one sensor.
First Claim
Family
International Classification(s)
Cited Art Landscape
Patent Citation Ranking
Advertisement
Advertisement
Advertisement
Recipient Email Address
Recipient Email Address
Comment
Recipient Email Address
Add to Portfolio(s)
To add this patent to one, or more, of your portfolios, simply click the add button.
This Patent is in these Portfolios:
Add to additional portfolios:
Last Refreshed On:
Changes done successfully