Abstract
For the wingtip-connected combined UAV considered here, the proposed constraint-based assessment demonstrates that the clearance margin changes sign between the sampled 5° and 6° angles of attack, thereby bracketing the clearance transition within this interval. This study presents a deterministic, constraint-based assessment framework for the separation of wingtip-connected combined unmanned aerial vehicles (UAVs). The previously developed torque-driven compliant interface is treated as the existing physical platform rather than as a new mechanism contribution. Structural-strength, roll-control, and collision-clearance requirements are formulated as individual limit-state margins and linked by a non-compensatory minimum operator, so that failure of one quantified constraint cannot be offset by favorable performance in another. Previously reported aerodynamic, finite-element, multibody-dynamics, and ground-test records are reanalyzed as case-study inputs; they are not presented as independent validation of the complete classifier. The verified stress contours show that parametric refinement reduces the maximum equivalent von Mises stress from 17.2 MPa to 10.4 MPa (39.5%). Ground measurements acquired at 1000 Hz yield R2 = 0.96 for a descriptive sinusoidal fit, supporting response smoothness but not proving the complete low-impact safety hypothesis. The framework therefore provides a traceable requirement-checking route; with the presently retained records, its demonstrated implementation is a clearance-decision template rather than a numerically complete three-channel safety index.