Numerous papers in the area of parafoil system design have been published over the past 50 years. They cover the following major topics: The future of the Army's air delivery mission includes the use of precision-guided autonomous airdrop methods to resupply troops in the field. High-glide systems, ram-air parafoil-based, allow for a safe standoff delivery as well as wind penetration. This paper addresses the development of a six-degree-offreedom model of a low-aspect ratio controllable parafoil-based delivery system. The model is equally suitable for modeling and simulation and for the design of guidance, navigation and control (GNC) algorithms. This gliding parafoil model was developed in the MATLAB/Simulink ® environment. Apparent mass and inertia effects are included in the model. Initial test cases have been run to check model fidelity.Advanced computational methods for the 3D flow simulation around the parafoil canopy; [1][2][3] Wind-tunnel experiments; [4][5][6][7] Real drop experiments. [8][9][10][11][12][13][14][15][16][17][18]

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Worth, 2 August, 1985. Different escape strategies were tested using the flight performance characteristics of the U. S. Navy's P-3 "Orion" and T-44 "Pegasus" aircraft. The three flight phases investigated were approach to landing , takeoff, and the low altitude ASW mission. Results from the analysis were coupled with the pilot's view-point from which conclusions were drawn. The results of the analysis support a constant-pitch-angle escape procedure. The same procedural steps can be used for both aircraft in any configuration or situation with the difference being the degree ofpitch to employ. The conclusions are in a format for integrating specific microburst escape procedures within the NATOPS programs for the P-3 and T-44 aircraft. iii