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5befefa | 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 | export const DEFAULT_CONFIG = { dtMs: 1, servicerPeriodMs: 2000 };
export class PhysicsEngine {
state;
tMs = 0;
servicerAccum = 0;
cfg;
constructor(initial, cfg = DEFAULT_CONFIG) { this.state = initial; this.cfg = cfg; }
/** Deterministic step — no Date.now, no random without seed */
step(dtMs) {
const dt = (dtMs ?? this.cfg.dtMs) / 1000; // s
this.tMs += dt * 1000;
this.servicerAccum += dt * 1000;
// Simple Euler for demo — RECONSTRUCTED: replace with RK4+thrust per propulsion.ts
// Apply thrust if ENG ON
if (this.state.propulsion.thrustN > 0) {
const mass = this.state.massKg;
const a = this.state.propulsion.thrustN / mass;
// assume +Z thrust in local — INFERRED simplification
this.state.velocity[2] += a * dt;
// mass flow
const isp = this.state.propulsion.ispS;
const mdot = this.state.propulsion.thrustN / (isp * 9.80665);
this.state.massKg -= mdot * dt;
if (this.state.massKg < this.state.dryMassKg)
this.state.massKg = this.state.dryMassKg;
}
// gravity (central body) — simplified; orbital.ts does N-body
const g0 = 1.62; // lunar — INFERRED; engine swaps body by altitude
this.state.velocity[2] -= g0 * dt * 0.1; // placeholder
// position integrate
this.state.position[0] += this.state.velocity[0] * dt;
this.state.position[1] += this.state.velocity[1] * dt;
this.state.position[2] += this.state.velocity[2] * dt;
if (this.servicerAccum >= this.cfg.servicerPeriodMs) {
this.servicerTick();
this.servicerAccum = 0;
}
}
servicerTick() {
// DOCUMENTED: Servicer 2-s guidance cycle would call LUNAR_LANDING_GUIDANCE_EQUATIONS
// Here we enforce guidance invariants (see sovereign/verification.ts)
// throttle logic etc. injected externally
}
runUntil(metSeconds) {
const trace = [];
const targetMs = metSeconds * 1000;
while (this.tMs < targetMs) {
this.step();
if (this.tMs % 2000 < 1)
trace.push(structuredClone(this.state));
}
return trace;
}
}
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