초록 ▼

Particular embodiments comprise 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. An Adaptive Mounting Plate (AMP) is placed over an ADS rail section and restrai

Particular embodiments comprise 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. An Adaptive Mounting Plate (AMP) is placed over an ADS rail section and restrained in position. 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.

대표청구항 ▼

1. A mission payload pod mounting apparatus comprising: an adaptive mounting system (AMS) plate that is coupled to the floor of an aircraft via Air Deployment System (ADS) rails, wherein the AMS mounting plate is milled to accommodate one or more restraint and bolt devices specific to the ADS rails,

1. A mission payload pod mounting apparatus comprising: an adaptive mounting system (AMS) plate that is coupled to the floor of an aircraft via Air Deployment System (ADS) rails, wherein the AMS mounting plate is milled to accommodate one or more restraint and bolt devices specific to the ADS rails, wherein the restraint and bolt devices are operable to interface the AMS mounting plate to the ADS rails; anda strut that is coupled to the AMS plate, wherein the strut extends from the interior of the aircraft to the exterior of the aircraft via a pressurized door plug that interfaces to the aircraft. 2. The apparatus of claim 1, wherein the ADS rails comprise an adaptive ADS rail section. 3. The apparatus of claim 2, a payload assembly that interfaces to the strut, wherein the payload assembly comprises one or more of: an electro optical, radar, or RF sensor;a BRU-12 bomb rack;an ejector rack;an integrated EO/IR surveillance and targeting sensor turret;an RF communications pod;an EWSP missile counter measures fairing;an infra-red detection set;laser countermeasures; oran ALE-55 towed decoy. 4. The apparatus of claim 2, wherein the AMS mounting plate is milled from a single block of non-ferrous metal. 5. The apparatus of claim 1, wherein the mission payload pod mounting apparatus is housed within one or more modular cases. 6. The apparatus of claim 1, further comprising one or more removable load transfer braces which interface to the AMS mounting plate and extend inboard from the AMS mounting place to interface to the floor. 7. The apparatus of claim 6, wherein the removable load transfer braces interface to the floor via one or more cargo tie-down rings which interface to the removable load transfer braces and the floor using tension adjustable cargo cam lock clamps. 8. The apparatus of claim 6, wherein the removable load transfer braces interface to the cargo floor via one or more cargo tie-down rings via one or more floor loads plates which interface to the load transfer braces and the tie-down rings. 9. The apparatus of claim 1, wherein the strut is a vertically actuated strut and fairing apparatus. 10. The apparatus of claim 1, wherein the strut is a non-actuated fixed-position strut and fairing apparatus. 11. The apparatus of claim 1, wherein the strut is a rotationally actuated strut which is operable to, in flight, extend a payload assembly from the interior to the exterior of the aircraft and retract the payload assembly from the exterior to the interior of the aircraft, wherein the payload assembly interfaces to the strut. 12. The apparatus of claim 11, wherein the rotationally actuated strut comprises a portion of a shoulder armature assembly that interfaces, via a geared rotating linkage, to a secondary wrist gear assembly that is operable to maintain synchronized vertical orientation of the payload assembly during strut extension and retraction. 13. The apparatus of claims 9, 10, or 11, wherein the strut(s) provide an internal wiring harness and mechanical cable conduit from the interior of the aircraft to the payload assembly. 14. The apparatus of claims 9 or 11, wherein the actuated strut interfaces to a manual hand crank drive assembly that is operable to retract and extend the payload assembly. 15. The apparatus of claim 1, wherein the strut comprises a portion of a shoulder armature assembly that interfaces to one or more electrical drive motors. 16. The apparatus of claim 15, wherein the should armature assembly and the electrical drive motors are covered by a removable armor housing.