Spacecraft entry into the atmosphere of a planet requires protection against the extreme temperatures that result from aerodynamic heating. This is normally achieved through use of a heat shield, which also provides the necessary aerodynamic braking and stability. The shape of the heat shield used varies considerably between spacecraft, and spherical and blunted-cone geometries are often employed. Theblunted-cone' heat shield has been developed through experimental design and computational simulation. Here, we demonstrate that this generic shape can be derived mathematically and yields the maximum stabilizing aerodynamic torque of all possible shapes (1). The derived single shape is universal, depending only on the center-of- mass, and provides invariance in static stability due to minor heat shield damage. The derived universal shape is obtained by requiring the aerodynamic torque be insensitive to small shape changes. Importantly, this heat shield shape gives the maximum stabilizing torque in both the continuum and free molecular (FM) regimes. For continuum flows, the obtained shape is always stable, regardless of the position of the center-of-mass. For FM flows, stability is dependent on the nature of the gas interactions with the surface and the position of the center-of-mass - even though the heat shield shape remains unchanged. This establishes that static stability may not be possible for some vehicle configurations, since the solution gives the shape that yields the maximum torque and this is unstable in some cases. Importantly, the design of practical heat shields involves numerous competing factors, which include the expected heat load and the craft volumetric efficiency, in addition to aerodynamic stability (2, 3). We thus emphasize that the presented results focus on only one component of this multi-objective problem. Nonetheless, the derived shape shows good agreement with the heat shields of previous entry vehicles, a comparison of which shall be given.