AIDT 온디바이스 국방 MUM-T 6세대 전투기 능동 공력탄성 날개(AAW) 플러터 억제 서보 엔진

using System;
using System.Runtime.CompilerServices;

namespace ZeliDesk.Defense.AeroelasticWingFlutter
{
    /// <summary>
    /// AAW 날개 굽힘/비틀림 가속도 텔레메트리 상태
    /// </summary>
    public readonly ref struct WingAeroelasticTelemetryState
    {
        public readonly double FlightMachNumber;          // 비행 마하수
        public readonly double DynamicPressureKPa;        // 비행 동압 q_inf [kPa]
        public readonly double WingTipBendingAccelG;      // 날개 끝 굽힘 가속도 [G]
        public readonly double WingTipTorsionRateRadSec;  // 날개 끝 비틀림 각속도 [rad/s]

        [MethodImpl(MethodImplOptions.AggressiveInlining)]
        public WingAeroelasticTelemetryState(double mach, double qKpa, double aBending, double wTorsion)
        {
            FlightMachNumber = mach;
            DynamicPressureKPa = qKpa;
            WingTipBendingAccelG = aBending;
            WingTipTorsionRateRadSec = wTorsion;
        }
    }

    /// <summary>
    /// 전연/후연 능동 플랩 타각 지령
    /// </summary>
    public readonly ref struct AawFlapCommand
    {
        public readonly double LeadingEdgeFlapDeg;        // 전연 플랩 (LECS) 타각 [deg]
        public readonly double TrailingEdgeFlapDeg;       // 후연 플랩 (TECS) 타각 [deg]
        public readonly double DampingRatioZeta;          // 현재 공력탄성 감쇠비
        public readonly bool FlutterSuppressed;           // 플러터 발산 억제 안정 상태

        [MethodImpl(MethodImplOptions.AggressiveInlining)]
        public AawFlapCommand(double leFlap, double teFlap, double zeta, bool stable)
        {
            LeadingEdgeFlapDeg = leFlap;
            TrailingEdgeFlapDeg = teFlap;
            DampingRatioZeta = zeta;
            FlutterSuppressed = stable;
        }
    }

    /// <summary>
    /// 10,000Hz 0-Alloc 능동 공력탄성 날개 플러터 억제 서보 엔진
    /// </summary>
    public sealed class ActiveAeroelasticWingServoEngine
    {
        private const double TransonicDipMachMin = 0.92;
        private const double TransonicDipMachMax = 1.15;
        private double _filteredBending;
        private double _currentLeFlap;
        private double _currentTeFlap;

        public ActiveAeroelasticWingServoEngine()
        {
            _filteredBending = 0.0;
            _currentLeFlap = 0.0;
            _currentTeFlap = 0.0;
        }

        [MethodImpl(MethodImplOptions.AggressiveInlining)]
        public AawFlapCommand UpdateServoLoop(in WingAeroelasticTelemetryState telemetry, double dtSeconds)
        {
            // 1. 천음속 딥 구간 감지 및 게인 스케줄링
            double gainMultiplier = 1.0;
            if (telemetry.FlightMachNumber >= TransonicDipMachMin && telemetry.FlightMachNumber <= TransonicDipMachMax)
            {
                gainMultiplier = 1.85; // 천음속 구간 제어력 증강
            }

            // 2. 날개 굽힘-비틀림 공진 모달 신호 결합
            _filteredBending = (0.85 * _filteredBending) + (0.15 * telemetry.WingTipBendingAccelG);

            // 3. 전연/후연 플랩 역위상 능동 감쇠 지령 (모달 에너지 흡수)
            double leCmd = -(_filteredBending * 0.45 + telemetry.WingTipTorsionRateRadSec * 1.8) * gainMultiplier;
            double teCmd = (_filteredBending * 0.55 - telemetry.WingTipTorsionRateRadSec * 2.2) * gainMultiplier;

            _currentLeFlap = Math.Clamp(leCmd, -12.0, 12.0); // 타각 제한
            _currentTeFlap = Math.Clamp(teCmd, -15.0, 15.0);

            // 4. 모달 감쇠비 추정
            double totalVib = Math.Abs(_filteredBending) + Math.Abs(telemetry.WingTipTorsionRateRadSec);
            double estimatedZeta = Math.Clamp(0.08 - (totalVib * 0.005), 0.01, 0.15);

            bool isStable = estimatedZeta >= 0.03 && Math.Abs(_filteredBending) < 4.0;
            return new AawFlapCommand(_currentLeFlap, _currentTeFlap, estimatedZeta, isStable);
        }
    }
}