Abstract: A wing for an aircraft includes, but is not limited to, a wing body having a wingtip, a leading-edge, and a trailing edge. The wingtip comprises an outboard-most portion of the wing body. The leading-edge is disposed along a forward portion of the wing body and is configured to cause a vortex to extend off the trailing edge at a location inboard of the wingtip when the aircraft is flown sub-sonically at a predetermined angle of attack. The trailing edge is disposed along an aft portion of the wing body and has an aft-most region disposed inboard of the wingtip at a position that corresponds with the location where the vortex extends off the trailing edge.

Abstract: A system for identifying and determining predictions of an entity of interest (EOT) includes a processor configured to receive real-time FMV data of an area of interest (AOI); a memory operatively coupled to the processor and storing a machine learning algorithm for identifying the EOT in the AOI; a database for use in classifying the EOT and determining predictions associated with the EOT; and a translator operatively coupled to the processor and configured to cause the processor to operationally communicate with the machine learning algorithm. The processor may be further configured to correlate a stored video data with the current video data and cause the database to store the correlated video data with its associated EOT. The processor may be configured to determine predictions associated with the EOT by identifying trends in the correlated video data.

Abstract: A propulsion system for an aircraft includes (1) an engine configured to generate a mass flow, (2) a nozzle having a pathway having a throat and a trailing edge, one of the throat and the trailing edge configured to enlarge and contract, (3) a heat source disposed in the nozzle, (4) a first pressure sensor to sense the static pressure of the mass flow at the nozzle exit, (5) a second pressure sensor to sense the ambient pressure proximate the aircraft, and a (6) controller. The controller is coupled with the first and second pressure sensors, the heat source, and the throat or the trailing edge (whichever is configured to enlarge and contract). The controller receives the static and ambient pressures and when there is a disparity, the controller controls at least one of the heat source, the throat, and the trailing edge in a manner that reduces the disparity.

Abstract: A wing for an aircraft includes, but is not limited to, a wing body having a wingtip, a leading-edge, and a trailing edge. The wingtip comprises an outboard-most portion of the wing body. The leading-edge is disposed along a forward portion of the wing body and is configured to cause a vortex to extend off the trailing edge at a location inboard of the wingtip when the aircraft is flown sub-sonically at a predetermined angle of attack. The trailing edge is disposed along an aft portion of the wing body and has an aft-most region disposed inboard of the wingtip at a position that corresponds with the location where the vortex extends off the trailing edge.

Abstract: Method and arrangement for reducing the effects of a sonic boom created by an aerospace vehicle when said vehicle is flown at supersonic speed. The method includes providing the aerospace vehicle with a first spike extending from the nose thereof substantially in the direction of normal flight of the aerospace vehicle, the first spike having a second section aft of a first section that is aft of a leading end portion, the first and second sections having a second transition region therebetween and each of the sections having different cross-sectional areas, the leading end portion of the first spike tapering toward a predetermined cross-section with a first transition region between the predetermined cross-section and the first section. The first transition region is configured so as to reduce the coalescence of shock waves produced by the first spike during normal supersonic flight of the aerospace vehicle.

Abstract: Method and arrangement for reducing the effects of a sonic boom created by an aerospace vehicle when said vehicle is flown at supersonic speed. The method includes providing the aerospace vehicle with a first spike extending from the nose thereof substantially in the direction of normal flight of the aerospace vehicle, the first spike having a second section aft of a first section that is aft of a leading end portion, the first and second sections having a second transition region therebetween and each of the sections having different cross-sectional areas, the leading end portion of the first spike tapering toward a predetermined cross-section with a first transition region between the predetermined cross-section and the first section. The first transition region is configured so as to reduce the coalescence of shock waves produced by the first spike during normal supersonic flight of the aerospace vehicle.

Abstract: This invention relates to a lockable container having a locking mechanism that secures a lid of the container to a receptacle of the container. The receptacle comprises a base, a top with a main receptacle opening, and a side wall extending around and between the base and top and having a recess suitable to receive a padlock and having a locking mechanism aperture smaller than the padlock. The lid is mountable to the receptacle and configured to cover at least a portion of the receptacle opening when in a closed position. The locking mechanism comprises a lock engagement member attached to the bottom of the lid such that when the lid is in the closed position, at least a portion of the lock engagement member extends through the locking mechanism aperture and into the recess, and is securable in place with the padlock located in the recess.

Abstract: This invention relates to a lockable container comprising an open-faced receptacle with a locking mechanism aperture, at least one lid covering at least a portion of the open face of the receptacle, and a locking mechanism for engaging with a padlock and securing the lid in a partially opened position over the receptacle open face. The locking mechanism has a receptacle engagement portion that is moveable into a receptacle engagement position, and when in such position, a lid engagement portion attached to the receptacle engagement portion receives the partially opened lid, and a lock engagement portion attached to the lid engagement portion is moveable into the receptacle and through the locking mechanism aperture, and out of the receptacle, where it is engageable with a padlock.

Abstract: A lockable container comprising an open-faced receptacle with a locking mechanism aperture, at least one lid covering at least a portion of the open face of the receptacle, and a locking mechanism for engaging with a padlock and securing the lid over the receptacle open face. The locking mechanism has a receptacle engagement portion that is moveable into a receptacle engagement position, and when in such position, a lid engagement portion attached to the receptacle engagement portion is moved over and into close proximity to the lid, and a lock engagement portion attached to the lid engagement portion is moveable into the receptacle and through the locking mechanism aperture, and out of the receptacle, where it is engageable with a padlock.

Abstract: This invention relates to a lockable container comprising an open-faced receptacle with a locking mechanism aperture, at least one lid covering at least a portion of the open face of the receptacle, and a locking mechanism for engaging with a padlock and securing the lid over the receptacle open face. The locking mechanism has a receptacle engagement portion that is moveable into a receptacle engagement position, and when in such position, a lid engagement portion attached to the receptacle engagement portion is moved over and into close proximity to the lid, and a lock engagement portion attached to the lid engagement portion is moveable into the receptacle and through the locking mechanism aperture, and out of the receptacle, where it is engageable with a padlock.