Patent WO-2009061347-A1 (WO)
Title: Aircraft based non-dedicated special mission pod mounting apparatus
Inventor: WOODLAND RICHARD L K
IPC: B64C1/20
Filed: 2008-10-15
Abstract: The system and apparatus of the present invention is generally comprised of a non- dedicated, temporarily installed, airborne special mission payload mounting system which is mechanically interfaced to the Air Deployment System (ADS) rails of a host cargo aircraft. Where a host aircraft does not possess ADS rails, an Adaptive ADS rail section typical of those used by the host aircraft, is installed to the existing cargo floor 'D' rings using adjustable cam locks familiar to those skilled in the art of aircraft cargo restraint systems. Where the host aircraft does not have the required cargo 'D' rings installed they are then temporarily installed within the 'D' ring bolt sockets to enable the aircraft to accommodate mounting of the Adaptive ADS rail section plate. Once the ADS rail section and plate are installed, an Adaptive Mounting Plate (AMP) is placed over the ADS rail section and restrained in position by using multiple bolts, and the cargo 'D' rings integral to the ADS rail securing the AMP in position using adjustable cam locks hooked through the ADS rail 'D' rings thereby precluding the requirement for a load transfer (torque) pallet, or dedicated airframe modifications. Once the AMP is secured, an articulated or fixed position strut can be attached to it through the opened side doorway without removing the original door. Once the fixed position or articulated strut is bolted to the AMP, a one piece or segmented two piece pressurized door plug indented along its lower periphery to accommodate the protruding form factor of the fixed position or articulated strut is installed within the vacant doorway above the strut providing an airtight seal and thereby permitting pressurization of the aircraft. In-flight dynamic loads exerted upon the various mission payload pods are transferred through the strut to the interior ADS rail by the AMP and to various cargo 'D' rings located on the aircraft floor by a plurality of removable Load Transfer Braces (LTB) hinged to the inboard side of the AMP which in turn transfers said dynamic loads to a Floor Loads Plate (FLP) secured to multiple cargo tie down 'D' rings on the floor of the host aircraft by means of adjustable cam locks. Said removable load transfer braces being able to rapidly disconnect from the adjustable cam locks, 'D' rings, and FLP for stowage in the vertical position, outboard of the cargo transit envelop as to permit in flight air drop operations. In flight, the articulated strut assembly can be extended below the fuselage to achieve a 360 degree unobstructed field of view (FOV) for a given payload, or retracted into the fuselage to change sensor payloads or re-load jettisonable stores. The preferred embodiment of the present invention can be installed or removed in minutes, does not interfere with crew egress, the aircraft flight performance envelope, or emergency procedures of the host aircraft while installed and further possesses redundant primary drive retraction systems along with a manual retraction system, and payload jettisoning system to preclude any danger in landing the aircraft should there be a problem retracting the various mission payloads.