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// SPDX-License-Identifier: AGPL-3.0-only
//! Entry heating, electro-optical radiometry and launch-ascent losses: three
//! MODELLED trade-study tools that sit one step above the closed-form corridor,
//! coverage and launch-window kinds ([`crate::reentry`], [`crate::eo_payload`],
//! [`crate::launch`]) without changing any of their outputs.
//!
//! * [`entry_heating`] — the `entry-heating` scenario: a 3-DoF point-mass entry over
//! a rotating spherical Earth or Mars (ballistic or lifting, constant bank), RK4,
//! with the stagnation-point convective-heating relation of NASA TR R-376 (1971),
//! the integrated heat load, peak deceleration and dynamic pressure, and the
//! NACA Report 1381 (1958) ballistic closed form as an internal check.
//! * [`eo_radiometry`] — the `eo-radiometry` scenario: an imager signal-to-noise
//! budget from a Lambertian scene, the system MTF at Nyquist (diffraction ×
//! detector × smear × jitter), the relative edge response, `Q = λF#/p` and a
//! NIIRS estimate from the General Image Quality Equation version 4.
//! * [`ascent`] — the `ascent-losses` scenario: a 2-D gravity-turn ascent of a
//! multi-stage vehicle through the US Standard Atmosphere 1976, integrating the
//! gravity, drag, steering and back-pressure losses and checking the
//! ideal-Δv-minus-losses identity.
//!
//! See `docs/ENTRY-EO-ASCENT.md` for the equations, inputs, outputs and scope.
/// Classical fourth-order Runge–Kutta step of `y' = f(y)` (autonomous) with step `h`.
pub