Automatically pitch and yaw responsive aircraft launching system
AssigneeVU Holdings, LLC
InventorsKurt Parsons, Dan Edwards
Life of this patent
Estimating the term…
Abstract
A stacked panel tube bundle for an air cooled steam condenser having two sets of condensing tubes, one set arranged above the other, the first (lower) set of tubes in direct fluid communication with a combined steam delivery/condensate collection manifold at a bottom end and in indirect fluid communication with a non-condensable collection manifold via an L-shaped extension member; the second (upper) set of tubes in direct fluid communication with the non-condensable collection manifold at the top, and in indirect fluid communication with the combined steam delivery/condensate collection manifold via an L-shaped extension member.
Claims18
A launching system for an aerial vehicle, comprising:
- a fixed hub;
- a base including a base plate pivotably mounted to the fixed hub, wherein said base plate is pivotable about a first, generally vertical axis;
- and
- a latch mechanism pivotably mounted to the base plate, wherein said latch mechanism is pivotable about a second axis that is perpendicular to the first axis, said latch mechanism comprising:
- a latch;
- a latch hook configured to engage a pin on an underside of a fuselage of said aerial vehicle;
- a release actuator operatively engaging the latch hook and attached to a fixed location on the launching system, wherein said release actuator is configured to cause the latch hook to open and release said pin upon upward pivoting of said latch mechanism, and
- at least one lift arm pivotably mounted to said base at a pivot connection, and wherein said latch is mounted to said at least one lift arm at an end of said lift arm opposite said pivot connection.
A ground vehicle-mounted launching system for an aerial vehicle, comprising:
- a fixed hub;
- a base including a horizontally pivotable base plate;
- and
- a vertically pivotable latch mechanism pivotably mounted to the base plate, said latch mechanism comprising:
- a latch;
- a latch hook configured to engage a pin on an underside of an aerial vehicle fuselage;
- a release actuator operatively engaging the latch hook and attached to a fixed location on the launching system, wherein said release actuator is configured to cause the latch hook to open and release said pin upon upward pivoting of said latch mechanism, and
- at least one lift arm pivotably mounted to said base at a pivot connection, and wherein said latch is mounted to said at least one lift arm at an end of said lift arm opposite said pivot connection.
Dependencies are inferred from the claim text.