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ACE3/extensions/advanced_ballistics/AdvancedBallistics.cpp
ulteq be482ea097 Advanced Ballistics - Drag model revamp & Spin drift correction (#5566) 
* Advanced Ballistics - Drag model revamp
- Moved away from using the drag tables from the GNU exterior ballistics library
- The drag functions are now based off this data from JBM Ballistics: http://www.jbmballistics.com/ballistics/downloads/text/
- The differences are minor, but some players might still appreciate the additional authenticity

* The Mach number is now calculated in relation to the air temperature.

* Improved speed of sound calculation accuracy.

* Advanced Ballistics - DLL update

* Advanced Ballistics - Added drag function reference (JBM Ballistics)

* Advanced Ballistics - Fixed calculation error in the spin drift simulation
- The error was introduced with this PR (https://github.com/acemod/ACE3/pull/4708)

* More descriptive variable names

* Minor performance optimizations

* Fixed some minor issues

* DLL rebuild

* Utilize new 'toFixed' script command
- Small performance improvement

* Fixed a typo

* Use correct reference speed for the drag compensation

* Updated all 'airFriction' values to match the new drag model

* 'Default' atmosphere now equals the ICAO standard atmosphere

* Update reference humidity to meet the ICAO standard
2017-10-06 13:05:20 -05:00

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#include "shared.hpp"
#include <stdlib.h>
#include <string>
#include <vector>
#include <unordered_map>
#include <random>
#include <cmath>
#define DELTA_T 0.02f
#define GRAVITY 9.80665f
#define DEGREES(X) (X * 180 / M_PI)
#define ABSOLUTE_ZERO_IN_CELSIUS -273.15f
#define KELVIN(t) (t - ABSOLUTE_ZERO_IN_CELSIUS)
#define CELSIUS(t) (t + ABSOLUTE_ZERO_IN_CELSIUS)
#define EARTH_ANGULAR_SPEED 0.00007292f
#define UNIVERSAL_GAS_CONSTANT 8.314f
#define WATER_VAPOR_MOLAR_MASS 0.018016f
#define DRY_AIR_MOLAR_MASS 0.028964f
#define SPECIFIC_GAS_CONSTANT_DRY_AIR 287.058f
#define STD_AIR_DENSITY_ICAO 1.22498f
#define STD_AIR_DENSITY_ASM 1.20885f
#define BC_CONVERSION_FACTOR 0.00068418f
#define SPEED_OF_SOUND(t) (331.3 * std::sqrt(1 + t / 273.15f))
#define SPEED_OF_SOUND_AT_15C 340.275
struct Bullet {
double airFriction;
double caliber;
double bulletLength;
double bulletMass;
std::vector<double> ballisticCoefficients;
std::vector<double> velocityBoundaries;
char* atmosphereModel;
int dragModel;
std::vector<double> muzzleVelocities;
std::vector<double> barrelLengths;
double stabilityFactor;
double twistDirection;
double transonicStabilityCoef;
double muzzleVelocity;
double bulletSpeed;
std::vector<double> origin;
double latitude;
double temperature;
double altitude;
double humidity;
double overcast;
double startTime;
double lastFrame;
double bcDegradation;
unsigned randSeed;
std::default_random_engine randGenerator;
};
struct Map {
std::vector<int> gridHeights;
std::vector<int> gridBuildingNums;
std::vector<int> gridSurfaceIsWater;
int mapSize;
int mapGrids;
};
std::vector<Bullet> bulletDatabase;
std::unordered_map<std::string, Map> mapDatabase;
std::string worldName = "";
Map* map = &mapDatabase[""];
double calculateRoughnessLength(double posX, double posY) {
// Source: http://es.ucsc.edu/~jnoble/wind/extrap/index.html
double roughness_lengths[10] = {0.0002, 0.0005, 0.0024, 0.03, 0.055, 0.1, 0.2, 0.4, 0.8, 1.6};
int gridX = (int)floor(posX / 50);
int gridY = (int)floor(posY / 50);
int gridCell = gridX * map->mapGrids + gridY;
if (gridCell >= 0 && (std::size_t)gridCell < map->gridHeights.size() && (std::size_t)gridCell < map->gridBuildingNums.size()) {
int nearBuildings = map->gridBuildingNums[gridCell];
int surfaceIsWater = map->gridSurfaceIsWater[gridCell];
if (nearBuildings == 0 && surfaceIsWater == 1) {
return 0.0005;
}
if (nearBuildings >= 10) {
return 1.6;
}
return roughness_lengths[2 + std::min(nearBuildings, 6)];
}
return 0.0024;
}
double calculateAirDensity(double temperature, double pressure, double relativeHumidity) {
pressure = pressure * 100;
if (relativeHumidity > 0) {
// 610.78 gives pressure in Pa - https://en.wikipedia.org/wiki/Density_of_air
double _pSat = 610.78 * pow(10, ((7.5 * temperature) / (temperature + 237.3)));
double vaporPressure = relativeHumidity * _pSat;
double partialPressure = pressure - vaporPressure;
return (partialPressure * DRY_AIR_MOLAR_MASS + vaporPressure * WATER_VAPOR_MOLAR_MASS) / (UNIVERSAL_GAS_CONSTANT * KELVIN(temperature));
} else {
return pressure / (SPECIFIC_GAS_CONSTANT_DRY_AIR * KELVIN(temperature));
}
}
double calculateAtmosphericCorrection(double ballisticCoefficient, double temperature, double pressure, double relativeHumidity, const char *atmosphereModel) {
double airDensity = calculateAirDensity(temperature, pressure, relativeHumidity);
if (!strcmp(atmosphereModel, "ICAO")) {
return (STD_AIR_DENSITY_ICAO / airDensity) * ballisticCoefficient;
} else {
return (STD_AIR_DENSITY_ASM / airDensity) * ballisticCoefficient;
}
}
// Drag Functions from: http://www.jbmballistics.com/ballistics/downloads/text/
const std::vector<double> dragCoefficientsG1 = { 0.2629, 0.2558, 0.2487, 0.2413, 0.2344, 0.2278, 0.2214, 0.2155, 0.2104, 0.2061, 0.2032, 0.2020, 0.2034, 0.2165, 0.2230, 0.2313, 0.2417, 0.2546, 0.2706, 0.2901, 0.3136, 0.3415, 0.3734, 0.4084, 0.4448, 0.4805, 0.5136, 0.5427, 0.5677, 0.5883, 0.6053, 0.6191, 0.6393, 0.6518, 0.6589, 0.6621, 0.6625, 0.6607, 0.6573, 0.6528, 0.6474, 0.6413, 0.6347, 0.6280, 0.6210, 0.6141, 0.6072, 0.6003, 0.5934, 0.5867, 0.5804, 0.5743, 0.5685, 0.5630, 0.5577, 0.5527, 0.5481, 0.5438, 0.5397, 0.5325, 0.5264, 0.5211, 0.5168, 0.5133, 0.5105, 0.5084, 0.5067, 0.5054, 0.5040, 0.5030, 0.5022, 0.5016, 0.5010, 0.5006, 0.4998, 0.4995, 0.4992, 0.4990, 0.4988 };
const std::vector<double> machNumbersG1 = { 0.00, 0.05, 0.10, 0.15, 0.20, 0.25, 0.30, 0.35, 0.40, 0.45, 0.50, 0.55, 0.60, 0.70, 0.725, 0.75, 0.775, 0.80, 0.825, 0.85, 0.875, 0.90, 0.925, 0.95, 0.975, 1.0, 1.025, 1.05, 1.075, 1.10, 1.125, 1.15, 1.20, 1.25, 1.30, 1.35, 1.40, 1.45, 1.50, 1.55, 1.60, 1.65, 1.70, 1.75, 1.80, 1.85, 1.90, 1.95, 2.00, 2.05, 2.10, 2.15, 2.20, 2.25, 2.30, 2.35, 2.40, 2.45, 2.50, 2.60, 2.70, 2.80, 2.90, 3.00, 3.10, 3.20, 3.30, 3.40, 3.50, 3.60, 3.70, 3.80, 3.90, 4.00, 4.20, 4.40, 4.60, 4.80, 5.00 };
const std::vector<double> dragCoefficientsG2 = { 0.2303, 0.2298, 0.2287, 0.2271, 0.2251, 0.2227, 0.2196, 0.2156, 0.2107, 0.2048, 0.1980, 0.1905, 0.1828, 0.1758, 0.1702, 0.1669, 0.1664, 0.1667, 0.1682, 0.1711, 0.1761, 0.1831, 0.2004, 0.2589, 0.3492, 0.3983, 0.4075, 0.4103, 0.4114, 0.4106, 0.4089, 0.4068, 0.4046, 0.4021, 0.3966, 0.3904, 0.3835, 0.3759, 0.3678, 0.3594, 0.3512, 0.3432, 0.3356, 0.3282, 0.3213, 0.3149, 0.3089, 0.3033, 0.2982, 0.2933, 0.2889, 0.2846, 0.2806, 0.2768, 0.2731, 0.2696, 0.2663, 0.2632, 0.2602, 0.2572, 0.2543, 0.2515, 0.2487, 0.2460, 0.2433, 0.2408, 0.2382, 0.2357, 0.2333, 0.2309, 0.2262, 0.2217, 0.2173, 0.2132, 0.2091, 0.2052, 0.2014, 0.1978, 0.1944, 0.1912, 0.1851, 0.1794, 0.1741, 0.1693, 0.1648 };
const std::vector<double> machNumbersG2 = { 0.00, 0.05, 0.10, 0.15, 0.20, 0.25, 0.30, 0.35, 0.40, 0.45, 0.50, 0.55, 0.60, 0.65, 0.70, 0.75, 0.775, 0.80, 0.825, 0.85, 0.875, 0.90, 0.925, 0.95, 0.975, 1.0, 1.025, 1.05, 1.075, 1.10, 1.125, 1.15, 1.175, 1.20, 1.25, 1.30, 1.35, 1.40, 1.45, 1.50, 1.55, 1.60, 1.65, 1.70, 1.75, 1.80, 1.85, 1.90, 1.95, 2.00, 2.05, 2.10, 2.15, 2.20, 2.25, 2.30, 2.35, 2.40, 2.45, 2.50, 2.55, 2.60, 2.65, 2.70, 2.75, 2.80, 2.85, 2.90, 2.95, 3.00, 3.10, 3.20, 3.30, 3.40, 3.50, 3.60, 3.70, 3.80, 3.90, 4.00, 4.20, 4.40, 4.60, 4.80, 5.00 };
const std::vector<double> dragCoefficientsG5 = { 0.1710, 0.1719, 0.1727, 0.1732, 0.1734, 0.1730, 0.1718, 0.1696, 0.1668, 0.1637, 0.1603, 0.1566, 0.1529, 0.1497, 0.1473, 0.1463, 0.1489, 0.1583, 0.1672, 0.1815, 0.2051, 0.2413, 0.2884, 0.3379, 0.3785, 0.4032, 0.4147, 0.4201, 0.4278, 0.4338, 0.4373, 0.4392, 0.4403, 0.4406, 0.4401, 0.4386, 0.4362, 0.4328, 0.4286, 0.4237, 0.4182, 0.4121, 0.4057, 0.3991, 0.3926, 0.3861, 0.3800, 0.3741, 0.3684, 0.3630, 0.3578, 0.3529, 0.3481, 0.3435, 0.3391, 0.3349, 0.3269, 0.3194, 0.3125, 0.3060, 0.2999, 0.2942, 0.2889, 0.2838, 0.2790, 0.2745, 0.2703, 0.2662, 0.2624, 0.2588, 0.2553, 0.2488, 0.2429, 0.2376, 0.2326, 0.2280 };
const std::vector<double> machNumbersG5 = { 0.00, 0.05, 0.10, 0.15, 0.20, 0.25, 0.30, 0.35, 0.40, 0.45, 0.50, 0.55, 0.60, 0.65, 0.70, 0.75, 0.80, 0.85, 0.875, 0.90, 0.925, 0.95, 0.975, 1.0, 1.025, 1.05, 1.075, 1.10, 1.15, 1.20, 1.25, 1.30, 1.35, 1.40, 1.45, 1.50, 1.55, 1.60, 1.65, 1.70, 1.75, 1.80, 1.85, 1.90, 1.95, 2.00, 2.05, 2.10, 2.15, 2.20, 2.25, 2.30, 2.35, 2.40, 2.45, 2.50, 2.60, 2.70, 2.80, 2.90, 3.00, 3.10, 3.20, 3.30, 3.40, 3.50, 3.60, 3.70, 3.80, 3.90, 4.00, 4.20, 4.40, 4.60, 4.80, 5.00 };
const std::vector<double> dragCoefficientsG6 = { 0.2617, 0.2553, 0.2491, 0.2432, 0.2376, 0.2324, 0.2278, 0.2238, 0.2205, 0.2177, 0.2155, 0.2138, 0.2126, 0.2121, 0.2122, 0.2132, 0.2154, 0.2194, 0.2229, 0.2297, 0.2449, 0.2732, 0.3141, 0.3597, 0.3994, 0.4261, 0.4402, 0.4465, 0.4490, 0.4497, 0.4494, 0.4482, 0.4464, 0.4441, 0.4390, 0.4336, 0.4279, 0.4221, 0.4162, 0.4102, 0.4042, 0.3981, 0.3919, 0.3855, 0.3788, 0.3721, 0.3652, 0.3583, 0.3515, 0.3447, 0.3381, 0.3314, 0.3249, 0.3185, 0.3122, 0.3060, 0.3000, 0.2941, 0.2883, 0.2772, 0.2668, 0.2574, 0.2487, 0.2407, 0.2333, 0.2265, 0.2202, 0.2144, 0.2089, 0.2039, 0.1991, 0.1947, 0.1905, 0.1866, 0.1794, 0.1730, 0.1673, 0.1621, 0.1574 };
const std::vector<double> machNumbersG6 = { 0.00, 0.05, 0.10, 0.15, 0.20, 0.25, 0.30, 0.35, 0.40, 0.45, 0.50, 0.55, 0.60, 0.65, 0.70, 0.75, 0.80, 0.85, 0.875, 0.90, 0.925, 0.95, 0.975, 1.0, 1.025, 1.05, 1.075, 1.10, 1.125, 1.15, 1.175, 1.20, 1.225, 1.25, 1.30, 1.35, 1.40, 1.45, 1.50, 1.55, 1.60, 1.65, 1.70, 1.75, 1.80, 1.85, 1.90, 1.95, 2.00, 2.05, 2.10, 2.15, 2.20, 2.25, 2.30, 2.35, 2.40, 2.45, 2.50, 2.60, 2.70, 2.80, 2.90, 3.00, 3.10, 3.20, 3.30, 3.40, 3.50, 3.60, 3.70, 3.80, 3.90, 4.00, 4.20, 4.40, 4.60, 4.80, 5.00 };
const std::vector<double> dragCoefficientsG7 = { 0.1198, 0.1197, 0.1196, 0.1194, 0.1193, 0.1194, 0.1194, 0.1194, 0.1193, 0.1193, 0.1194, 0.1193, 0.1194, 0.1197, 0.1202, 0.1207, 0.1215, 0.1226, 0.1242, 0.1266, 0.1306, 0.1368, 0.1464, 0.1660, 0.2054, 0.2993, 0.3803, 0.4015, 0.4043, 0.4034, 0.4014, 0.3987, 0.3955, 0.3884, 0.3810, 0.3732, 0.3657, 0.3580, 0.3440, 0.3376, 0.3315, 0.3260, 0.3209, 0.3160, 0.3117, 0.3078, 0.3042, 0.3010, 0.2980, 0.2951, 0.2922, 0.2892, 0.2864, 0.2835, 0.2807, 0.2779, 0.2752, 0.2725, 0.2697, 0.2670, 0.2643, 0.2615, 0.2588, 0.2561, 0.2533, 0.2506, 0.2479, 0.2451, 0.2424, 0.2368, 0.2313, 0.2258, 0.2205, 0.2154, 0.2106, 0.2060, 0.2017, 0.1975, 0.1935, 0.1861, 0.1793, 0.1730, 0.1672, 0.1618 };
const std::vector<double> machNumbersG7 = { 0.0, 0.05, 0.10, 0.15, 0.20, 0.25, 0.30, 0.35, 0.40, 0.45, 0.50, 0.55, 0.60, 0.65, 0.70, 0.725, 0.75, 0.775, 0.80, 0.825, 0.85, 0.875, 0.90, 0.925, 0.95, 0.975, 1.0, 1.025, 1.05, 1.075, 1.10, 1.125, 1.15, 1.20, 1.25, 1.30, 1.35, 1.40, 1.50, 1.55, 1.60, 1.65, 1.70, 1.75, 1.80, 1.85, 1.90, 1.95, 2.00, 2.05, 2.10, 2.15, 2.20, 2.25, 2.30, 2.35, 2.40, 2.45, 2.50, 2.55, 2.60, 2.65, 2.70, 2.75, 2.80, 2.85, 2.90, 2.95, 3.00, 3.10, 3.20, 3.30, 3.40, 3.50, 3.60, 3.70, 3.80, 3.90, 4.00, 4.20, 4.40, 4.60, 4.80, 5.00 };
const std::vector<double> dragCoefficientsG8 = { 0.2105, 0.2105, 0.2104, 0.2104, 0.2103, 0.2103, 0.2103, 0.2103, 0.2103, 0.2102, 0.2102, 0.2102, 0.2102, 0.2102, 0.2103, 0.2103, 0.2104, 0.2104, 0.2105, 0.2106, 0.2109, 0.2183, 0.2571, 0.3358, 0.4068, 0.4378, 0.4476, 0.4493, 0.4477, 0.4450, 0.4419, 0.4353, 0.4283, 0.4208, 0.4133, 0.4059, 0.3986, 0.3915, 0.3845, 0.3777, 0.3710, 0.3645, 0.3581, 0.3519, 0.3458, 0.3400, 0.3343, 0.3288, 0.3234, 0.3182, 0.3131, 0.3081, 0.3032, 0.2983, 0.2937, 0.2891, 0.2845, 0.2802, 0.2720, 0.2642, 0.2569, 0.2499, 0.2432, 0.2368, 0.2308, 0.2251, 0.2197, 0.2147, 0.2101, 0.2058, 0.2019, 0.1983, 0.1950, 0.1890, 0.1837, 0.1791, 0.1750, 0.1713 };
const std::vector<double> machNumbersG8 = { 0.00, 0.05, 0.10, 0.15, 0.20, 0.25, 0.30, 0.35, 0.40, 0.45, 0.50, 0.55, 0.60, 0.65, 0.70, 0.75, 0.80, 0.825, 0.85, 0.875, 0.90, 0.925, 0.95, 0.975, 1.0, 1.025, 1.05, 1.075, 1.10, 1.125, 1.15, 1.20, 1.25, 1.30, 1.35, 1.40, 1.45, 1.50, 1.55, 1.60, 1.65, 1.70, 1.75, 1.80, 1.85, 1.90, 1.95, 2.00, 2.05, 2.10, 2.15, 2.20, 2.25, 2.30, 2.35, 2.40, 2.45, 2.50, 2.60, 2.70, 2.80, 2.90, 3.00, 3.10, 3.20, 3.30, 3.40, 3.50, 3.60, 3.70, 3.80, 3.90, 4.00, 4.20, 4.40, 4.60, 4.80, 5.00 };
const std::vector<std::vector<double>> dragCoefficients = { {}, dragCoefficientsG1, dragCoefficientsG2, {}, {}, dragCoefficientsG5, dragCoefficientsG6, dragCoefficientsG7, dragCoefficientsG8, {} };
const std::vector<std::vector<double>> machNumbers = { {}, machNumbersG1, machNumbersG2, {},{}, machNumbersG5, machNumbersG6, machNumbersG7, machNumbersG8,{} };
double calculateRetard(int DragFunction, double DragCoefficient, double Velocity, double Mach) {
int idx = std::max(0, std::min(DragFunction, 9));
double m = Velocity / Mach;
for (int i = 0; i < machNumbers[idx].size(); i++) {
if (machNumbers[idx][i] >= m) {
int previousIdx = std::max(0, i - 1);
double previousDragCoefficient = dragCoefficients[idx][previousIdx];
double previousMachNumber = machNumbers[idx][previousIdx];
double cd = previousDragCoefficient + (dragCoefficients[idx][i] - previousDragCoefficient) * (m - previousMachNumber) / (machNumbers[idx][i] - previousMachNumber);
return BC_CONVERSION_FACTOR * (cd / DragCoefficient) * std::pow(Velocity, 2);
}
}
return 0.0;
}
double calculateVanillaZeroAngle(double zeroRange, double muzzleVelocity, double airFriction, double boreHeight) {
double zeroAngle = 0.0f;
for (int i = 0; i < 10; i++) {
double lx = 0.0f;
double ly = 0.0f;
double px = 0.0f;
double py = -boreHeight / 100.0f;
double gx = std::sin(zeroAngle) * -GRAVITY;
double gy = std::cos(zeroAngle) * -GRAVITY;
double vx = std::cos(zeroAngle) * muzzleVelocity;
double vy = std::sin(zeroAngle) * muzzleVelocity;
double tof = 0.0f;
double v = 0.0f;
while (tof < 8.0f && px < zeroRange) {
lx = px;
ly = py;
v = std::sqrt(vx*vx + vy*vy);
double ax = vx * v * airFriction;
double ay = vy * v * airFriction;
ax += gx;
ay += gy;
px += vx * DELTA_T * 0.5;
py += vy * DELTA_T * 0.5;
vx += ax * DELTA_T;
vy += ay * DELTA_T;
px += vx * DELTA_T * 0.5;
py += vy * DELTA_T * 0.5;
tof += DELTA_T;
}
double y = ly + (zeroRange - lx) * (py - ly) / (px - lx);
double offset = -std::atan(y / zeroRange);
zeroAngle += offset;
if (std::abs(offset) < 0.0001f) {
break;
}
}
return zeroAngle;
}
double calculateZeroAngle(double zeroRange, double muzzleVelocity, double boreHeight, double temperature, double pressure, double humidity, double ballisticCoefficient, int dragModel, char* atmosphereModel) {
double zeroAngle = 0.0f;
ballisticCoefficient = calculateAtmosphericCorrection(ballisticCoefficient, temperature, pressure, humidity, atmosphereModel);
for (int i = 0; i < 10; i++) {
double lx = 0.0f;
double ly = 0.0f;
double px = 0.0f;
double py = -boreHeight / 100.0f;
double gx = std::sin(zeroAngle) * -GRAVITY;
double gy = std::cos(zeroAngle) * -GRAVITY;
double vx = std::cos(zeroAngle) * muzzleVelocity;
double vy = std::sin(zeroAngle) * muzzleVelocity;
double tof = 0.0f;
double v = 0.0f;
while (tof < 8.0f && px < zeroRange) {
lx = px;
ly = py;
v = std::sqrt(vx*vx + vy*vy);
double retard = calculateRetard(dragModel, ballisticCoefficient, v, SPEED_OF_SOUND_AT_15C);
double ax = vx / v * -retard;
double ay = vy / v * -retard;
ax += gx;
ay += gy;
px += vx * DELTA_T * 0.5;
py += vy * DELTA_T * 0.5;
vx += ax * DELTA_T;
vy += ay * DELTA_T;
px += vx * DELTA_T * 0.5;
py += vy * DELTA_T * 0.5;
tof += DELTA_T;
}
double y = ly + (zeroRange - lx) * (py - ly) / (px - lx);
double offset = -std::atan(y / zeroRange);
zeroAngle += offset;
if (std::abs(offset) < 0.0001f) {
break;
}
}
return zeroAngle;
}
extern "C"
{
EXPORT void __stdcall RVExtensionVersion(char *output, int outputSize);
EXPORT void __stdcall RVExtension(char *output, int outputSize, const char *function);
}
void __stdcall RVExtensionVersion(char *output, int outputSize)
{
strncpy_s(output, outputSize, ACE_FULL_VERSION_STR, _TRUNCATE);
}
void __stdcall RVExtension(char *output, int outputSize, const char *function)
{
ZERO_OUTPUT();
std::stringstream outputStr;
if (!strcmp(function, "version")) {
strncpy_s(output, outputSize, ACE_FULL_VERSION_STR, _TRUNCATE);
EXTENSION_RETURN();
}
char* input = _strdup(function);
char* token = NULL;
char* next_token = NULL;
char* mode = strtok_s(input, ":", &next_token);
if (!strcmp(mode, "retard")) {
double ballisticCoefficient = 1.0;
int dragModel = 1;
double velocity = 0.0;
double temperature = 15.0;
double retard = 0.0;
dragModel = strtol(strtok_s(NULL, ":", &next_token), NULL, 10);
ballisticCoefficient = strtod(strtok_s(NULL, ":", &next_token), NULL);
velocity = strtod(strtok_s(NULL, ":", &next_token), NULL);
temperature = strtod(strtok_s(NULL, ":", &next_token), NULL);
retard = calculateRetard(dragModel, ballisticCoefficient, velocity, SPEED_OF_SOUND(temperature));
// int n = sprintf(output, "%f", retard);
outputStr << retard;
strncpy_s(output, outputSize, outputStr.str().c_str(), _TRUNCATE);
EXTENSION_RETURN();
} else if (!strcmp(mode, "atmosphericCorrection")) {
double ballisticCoefficient = 1.0;
double temperature = 15.0;
double pressure = 1013.25;
double humidity = 0.0;
char* atmosphereModel;
ballisticCoefficient = strtod(strtok_s(NULL, ":", &next_token), NULL);
temperature = strtod(strtok_s(NULL, ":", &next_token), NULL);
pressure = strtod(strtok_s(NULL, ":", &next_token), NULL);
humidity = strtod(strtok_s(NULL, ":", &next_token), NULL);
atmosphereModel = strtok_s(NULL, ":", &next_token);
ballisticCoefficient = calculateAtmosphericCorrection(ballisticCoefficient, temperature, pressure, humidity, atmosphereModel);
//int n = sprintf(output, "%f", ballisticCoefficient);
outputStr << ballisticCoefficient;
strncpy_s(output, outputSize, outputStr.str().c_str(), _TRUNCATE);
EXTENSION_RETURN();
} else if (!strcmp(mode, "new")) {
unsigned int index = 0;
double airFriction = 0.0;
char* ballisticCoefficientArray;
char* ballisticCoefficient;
std::vector<double> ballisticCoefficients;
char* velocityBoundaryArray;
char* velocityBoundary;
std::vector<double> velocityBoundaries;
char* atmosphereModel;
int dragModel = 1;
double stabilityFactor = 1.5;
int twistDirection = 1;
double transonicStabilityCoef = 1;
double muzzleVelocity = 850;
char* originArray;
char* originEntry;
std::vector<double> origin;
double latitude = 0.0;
double temperature = 0.0;
double altitude = 0.0;
double humidity = 0.0;
double overcast = 0.0;
double tickTime = 0.0;
index = strtol(strtok_s(NULL, ":", &next_token), NULL, 10);
airFriction = strtod(strtok_s(NULL, ":", &next_token), NULL);
ballisticCoefficientArray = strtok_s(NULL, ":", &next_token);
ballisticCoefficientArray++;
ballisticCoefficientArray[strlen(ballisticCoefficientArray) - 1] = 0;
ballisticCoefficient = strtok_s(ballisticCoefficientArray, ",", &token);
while (ballisticCoefficient != NULL) {
ballisticCoefficients.push_back(strtod(ballisticCoefficient, NULL));
ballisticCoefficient = strtok_s(NULL, ",", &token);
}
velocityBoundaryArray = strtok_s(NULL, ":", &next_token);
velocityBoundaryArray++;
velocityBoundaryArray[strlen(velocityBoundaryArray) - 1] = 0;
velocityBoundary = strtok_s(velocityBoundaryArray, ",", &token);
while (velocityBoundary != NULL) {
velocityBoundaries.push_back(strtod(velocityBoundary, NULL));
velocityBoundary = strtok_s(NULL, ",", &token);
}
atmosphereModel = strtok_s(NULL, ":", &next_token);
dragModel = strtol(strtok_s(NULL, ":", &next_token), NULL, 10);
stabilityFactor = strtod(strtok_s(NULL, ":", &next_token), NULL);
twistDirection = strtol(strtok_s(NULL, ":", &next_token), NULL, 10);
muzzleVelocity = strtod(strtok_s(NULL, ":", &next_token), NULL);
transonicStabilityCoef = strtod(strtok_s(NULL, ":", &next_token), NULL);
originArray = strtok_s(NULL, ":", &next_token);
originArray++;
originArray[strlen(originArray) - 1] = 0;
originEntry = strtok_s(originArray, ",", &token);
while (originEntry != NULL) {
origin.push_back(strtod(originEntry, NULL));
originEntry = strtok_s(NULL, ",", &token);
}
latitude = strtod(strtok_s(NULL, ":", &next_token), NULL);
temperature = strtod(strtok_s(NULL, ":", &next_token), NULL);
altitude = strtod(strtok_s(NULL, ":", &next_token), NULL);
humidity = strtod(strtok_s(NULL, ":", &next_token), NULL);
overcast = strtod(strtok_s(NULL, ":", &next_token), NULL);
tickTime = strtod(strtok_s(NULL, ":", &next_token), NULL);
while (index >= bulletDatabase.size()) {
Bullet bullet;
bulletDatabase.push_back(bullet);
}
bulletDatabase[index].airFriction = airFriction;
bulletDatabase[index].ballisticCoefficients = ballisticCoefficients;
bulletDatabase[index].velocityBoundaries = velocityBoundaries;
bulletDatabase[index].atmosphereModel = atmosphereModel;
bulletDatabase[index].dragModel = dragModel;
bulletDatabase[index].stabilityFactor = stabilityFactor;
bulletDatabase[index].twistDirection = twistDirection;
bulletDatabase[index].transonicStabilityCoef = transonicStabilityCoef;
bulletDatabase[index].muzzleVelocity = muzzleVelocity;
bulletDatabase[index].bulletSpeed = muzzleVelocity;
bulletDatabase[index].origin = origin;
bulletDatabase[index].latitude = latitude / 180 * M_PI;
bulletDatabase[index].temperature = temperature;
bulletDatabase[index].altitude = altitude;
bulletDatabase[index].humidity = humidity;
bulletDatabase[index].overcast = overcast;
bulletDatabase[index].startTime = tickTime;
bulletDatabase[index].lastFrame = tickTime;
bulletDatabase[index].bcDegradation = 1.0;
bulletDatabase[index].randSeed = 0;
strncpy_s(output, outputSize, "", _TRUNCATE);
EXTENSION_RETURN();
} else if (!strcmp(mode, "simulate")) {
// simulate:0:[-0.109985,542.529,-3.98301]:[3751.57,5332.23,214.252]:[0.598153,2.38829,0]:28.6:0:0.481542:0:215.16
unsigned int index = 0;
char* velocityArray;
double velocity[3] = { 0.0, 0.0, 0.0 };
char* positionArray;
double position[3] = { 0.0, 0.0, 0.0 };
char* windArray;
double wind[3];
double heightAGL = 0.0;
double tickTime = 0.0;
index = strtol(strtok_s(NULL, ":", &next_token), NULL, 10);
velocityArray = strtok_s(NULL, ":", &next_token);
velocityArray++;
velocityArray[strlen(velocityArray) - 1] = 0;
velocity[0] = strtod(strtok_s(velocityArray, ",", &token), NULL);
velocity[1] = strtod(strtok_s(NULL, ",", &token), NULL);
velocity[2] = strtod(strtok_s(NULL, ",", &token), NULL);
positionArray = strtok_s(NULL, ":", &next_token);
positionArray++;
positionArray[strlen(positionArray) - 1] = 0;
position[0] = strtod(strtok_s(positionArray, ",", &token), NULL);
position[1] = strtod(strtok_s(NULL, ",", &token), NULL);
position[2] = strtod(strtok_s(NULL, ",", &token), NULL);
windArray = strtok_s(NULL, ":", &next_token);
windArray++;
windArray[strlen(windArray) - 1] = 0;
wind[0] = strtod(strtok_s(windArray, ",", &token), NULL);
wind[1] = strtod(strtok_s(NULL, ",", &token), NULL);
wind[2] = strtod(strtok_s(NULL, ",", &token), NULL);
heightAGL = strtod(strtok_s(NULL, ":", &next_token), NULL);
tickTime = strtod(strtok_s(NULL, ":", &next_token), NULL);
if (bulletDatabase[index].randSeed == 0) {
int angle = (int)round(atan2(velocity[0], velocity[1]) * 360 / M_PI);
bulletDatabase[index].randSeed = (unsigned)(720 + angle) % 720;
bulletDatabase[index].randSeed *= 3;
bulletDatabase[index].randSeed += (unsigned)round(abs(velocity[2]) / 2);
bulletDatabase[index].randSeed *= 3;
bulletDatabase[index].randSeed += (unsigned)round(abs(bulletDatabase[index].origin[0] / 2));
bulletDatabase[index].randSeed *= 3;
bulletDatabase[index].randSeed += (unsigned)round(abs(bulletDatabase[index].origin[1] / 2));
bulletDatabase[index].randSeed *= 3;
bulletDatabase[index].randSeed += (unsigned)abs(bulletDatabase[index].temperature) * 10;
bulletDatabase[index].randSeed *= 3;
bulletDatabase[index].randSeed += (unsigned)abs(bulletDatabase[index].humidity) * 10;
bulletDatabase[index].randGenerator.seed(bulletDatabase[index].randSeed);
}
double ballisticCoefficient = 1.0;
double dragRef = 0.0;
double drag = 0.0;
double accelRef[3] = { 0.0, 0.0, 0.0 };
double accel[3] = { 0.0, 0.0, 0.0 };
double TOF = tickTime - bulletDatabase[index].startTime;
double deltaT = tickTime - bulletDatabase[index].lastFrame;
double trueVelocity[3] = { 0.0, 0.0, 0.0 };
double trueSpeed = 0.0;
double temperature = bulletDatabase[index].temperature - 0.0065 * position[2];
double pressure = (1013.25 - 10 * bulletDatabase[index].overcast) * pow(1 - (0.0065 * (bulletDatabase[index].altitude + position[2])) / (KELVIN(temperature) + 0.0065 * bulletDatabase[index].altitude), 5.255754495);
double windSpeed = 0.0;
double windAttenuation = 1.0;
double velocityOffset[3] = { 0.0, 0.0, 0.0 };
bulletDatabase[index].lastFrame = tickTime;
windSpeed = sqrt(pow(wind[0], 2) + pow(wind[1], 2) + pow(wind[2], 2));
if (windSpeed > 0.1) {
double windSourceTerrain[3];
windSourceTerrain[0] = position[0] - wind[0] / windSpeed * 100;
windSourceTerrain[1] = position[1] - wind[1] / windSpeed * 100;
windSourceTerrain[2] = position[2] - wind[2] / windSpeed * 100;
int gridX = (int)floor(windSourceTerrain[0] / 50);
int gridY = (int)floor(windSourceTerrain[1] / 50);
int gridCell = gridX * map->mapGrids + gridY;
if (gridCell >= 0 && (std::size_t)gridCell < map->gridHeights.size() && (std::size_t)gridCell < map->gridBuildingNums.size()) {
double gridHeight = map->gridHeights[gridCell];
if (gridHeight > position[2]) {
double angle = atan((gridHeight - position[2]) / 100);
windAttenuation *= pow(abs(cos(angle)), 2);
}
}
}
if (windSpeed > 0.1) {
double windSourceObstacles[3];
windSourceObstacles[0] = position[0] - wind[0] / windSpeed * 25;
windSourceObstacles[1] = position[1] - wind[1] / windSpeed * 25;
windSourceObstacles[2] = position[2] - wind[2] / windSpeed * 25;
if (heightAGL > 0 && heightAGL < 20) {
double roughnessLength = calculateRoughnessLength(windSourceObstacles[0], windSourceObstacles[1]);
windAttenuation *= abs(log(heightAGL / roughnessLength) / log(20 / roughnessLength));
}
}
if (windAttenuation < 1) {
wind[0] *= windAttenuation;
wind[1] *= windAttenuation;
wind[2] *= windAttenuation;
windSpeed = sqrt(pow(wind[0], 2) + pow(wind[1], 2) + pow(wind[2], 2));
}
trueVelocity[0] = velocity[0] - wind[0];
trueVelocity[1] = velocity[1] - wind[1];
trueVelocity[2] = velocity[2] - wind[2];
trueSpeed = sqrt(pow(trueVelocity[0], 2) + pow(trueVelocity[1], 2) + pow(trueVelocity[2], 2));
if (bulletDatabase[index].transonicStabilityCoef < 1.0f && trueSpeed - 60 < SPEED_OF_SOUND(temperature) && trueSpeed > SPEED_OF_SOUND(temperature)) {
std::uniform_real_distribution<double> distribution(-10.0, 10.0);
double coef = 1.0f - bulletDatabase[index].transonicStabilityCoef;
trueVelocity[0] += distribution(bulletDatabase[index].randGenerator) * coef;
trueVelocity[1] += distribution(bulletDatabase[index].randGenerator) * coef;
trueVelocity[2] += distribution(bulletDatabase[index].randGenerator) * coef;
double speed = sqrt(pow(trueVelocity[0], 2) + pow(trueVelocity[1], 2) + pow(trueVelocity[2], 2));
trueVelocity[0] *= trueSpeed / speed;
trueVelocity[1] *= trueSpeed / speed;
trueVelocity[2] *= trueSpeed / speed;
bulletDatabase[index].bcDegradation *= pow(0.993, coef);
};
if (bulletDatabase[index].ballisticCoefficients.size() == bulletDatabase[index].velocityBoundaries.size() + 1) {
dragRef = deltaT * bulletDatabase[index].airFriction * bulletDatabase[index].bulletSpeed * bulletDatabase[index].bulletSpeed;
accelRef[0] = (velocity[0] / bulletDatabase[index].bulletSpeed) * dragRef;
accelRef[1] = (velocity[1] / bulletDatabase[index].bulletSpeed) * dragRef;
accelRef[2] = (velocity[2] / bulletDatabase[index].bulletSpeed) * dragRef;
velocityOffset[0] -= accelRef[0];
velocityOffset[1] -= accelRef[1];
velocityOffset[2] -= accelRef[2];
ballisticCoefficient = bulletDatabase[index].ballisticCoefficients[0];
for (int i = (int)bulletDatabase[index].velocityBoundaries.size() - 1; i >= 0; i = i - 1) {
if (trueSpeed < bulletDatabase[index].velocityBoundaries[i]) {
ballisticCoefficient = bulletDatabase[index].ballisticCoefficients[i + 1];
break;
}
}
ballisticCoefficient = calculateAtmosphericCorrection(ballisticCoefficient, temperature, pressure, bulletDatabase[index].humidity, bulletDatabase[index].atmosphereModel);
ballisticCoefficient *= bulletDatabase[index].bcDegradation;
drag = deltaT * calculateRetard(bulletDatabase[index].dragModel, ballisticCoefficient, trueSpeed, SPEED_OF_SOUND(temperature));
accel[0] = (trueVelocity[0] / trueSpeed) * drag;
accel[1] = (trueVelocity[1] / trueSpeed) * drag;
accel[2] = (trueVelocity[2] / trueSpeed) * drag;
velocityOffset[0] -= accel[0];
velocityOffset[1] -= accel[1];
velocityOffset[2] -= accel[2];
} else {
double airDensity = calculateAirDensity(temperature, pressure, bulletDatabase[index].humidity);
double airFriction = bulletDatabase[index].airFriction * airDensity / STD_AIR_DENSITY_ICAO;
if (airFriction != bulletDatabase[index].airFriction || windSpeed > 0) {
dragRef = deltaT * bulletDatabase[index].airFriction * bulletDatabase[index].bulletSpeed * bulletDatabase[index].bulletSpeed;
accelRef[0] = (velocity[0] / bulletDatabase[index].bulletSpeed) * dragRef;
accelRef[1] = (velocity[1] / bulletDatabase[index].bulletSpeed) * dragRef;
accelRef[2] = (velocity[2] / bulletDatabase[index].bulletSpeed) * dragRef;
velocityOffset[0] -= accelRef[0];
velocityOffset[1] -= accelRef[1];
velocityOffset[2] -= accelRef[2];
drag = deltaT * airFriction * trueSpeed * trueSpeed;
accel[0] = (trueVelocity[0] / trueSpeed) * drag;
accel[1] = (trueVelocity[1] / trueSpeed) * drag;
accel[2] = (trueVelocity[2] / trueSpeed) * drag;
velocityOffset[0] += accel[0];
velocityOffset[1] += accel[1];
velocityOffset[2] += accel[2];
}
}
if (TOF > 0) {
double bulletDir = atan2(velocity[0], velocity[1]);
double driftAccel = bulletDatabase[index].twistDirection * (0.0482251 * (bulletDatabase[index].stabilityFactor + 1.2)) / pow(TOF, 0.17);
double driftVelocity = 0.0581025 *(bulletDatabase[index].stabilityFactor + 1.2) * pow(TOF, 0.83);
double dragCorrection = (driftVelocity / trueSpeed) * drag;
velocityOffset[0] += sin(bulletDir + M_PI / 2) * (driftAccel * deltaT + dragCorrection);
velocityOffset[1] += cos(bulletDir + M_PI / 2) * (driftAccel * deltaT + dragCorrection);
}
double lat = bulletDatabase[index].latitude;
accel[0] = 2 * EARTH_ANGULAR_SPEED * +(velocity[1] * sin(lat) - velocity[2] * cos(lat));
accel[1] = 2 * EARTH_ANGULAR_SPEED * -(velocity[0] * sin(lat));
accel[2] = 2 * EARTH_ANGULAR_SPEED * +(velocity[0] * cos(lat));
velocityOffset[0] += accel[0] * deltaT;
velocityOffset[1] += accel[1] * deltaT;
velocityOffset[2] += accel[2] * deltaT;
velocity[0] += velocityOffset[0];
velocity[1] += velocityOffset[1];
velocity[2] += velocityOffset[2];
bulletDatabase[index].bulletSpeed = sqrt(pow(velocity[0], 2) + pow(velocity[1], 2) + pow(velocity[2], 2));
outputStr << "[" << velocityOffset[0] << "," << velocityOffset[1] << "," << velocityOffset[2] << "]";
strncpy_s(output, outputSize, outputStr.str().c_str(), _TRUNCATE);
EXTENSION_RETURN();
} else if (!strcmp(mode, "set")) {
int height = 0;
int numObjects = 0;
int surfaceIsWater = 0;
height = strtol(strtok_s(NULL, ":", &next_token), NULL, 10);
numObjects = strtol(strtok_s(NULL, ":", &next_token), NULL, 10);
surfaceIsWater = strtol(strtok_s(NULL, ":", &next_token), NULL, 10);
map->gridHeights.push_back(height);
map->gridBuildingNums.push_back(numObjects);
map->gridSurfaceIsWater.push_back(surfaceIsWater);
strncpy_s(output, outputSize, outputStr.str().c_str(), _TRUNCATE);
EXTENSION_RETURN();
} else if (!strcmp(mode, "init")) {
int mapSize = 0;
int mapGrids = 0;
unsigned int gridCells = 0;
worldName = strtok_s(NULL, ":", &next_token);
mapSize = strtol(strtok_s(NULL, ":", &next_token), NULL, 10);
mapGrids = (int)ceil((double)mapSize / 50.0) + 1;
gridCells = mapGrids * mapGrids;
map = &mapDatabase[worldName];
if (map->gridHeights.size() == gridCells) {
outputStr << "Terrain already initialized";
strncpy_s(output, outputSize, outputStr.str().c_str(), _TRUNCATE);
EXTENSION_RETURN();
}
map->mapSize = mapSize;
map->mapGrids = mapGrids;
map->gridHeights.clear();
map->gridBuildingNums.clear();
map->gridSurfaceIsWater.clear();
map->gridHeights.reserve(gridCells);
map->gridBuildingNums.reserve(gridCells);
map->gridSurfaceIsWater.reserve(gridCells);
strncpy_s(output, outputSize, outputStr.str().c_str(), _TRUNCATE);
EXTENSION_RETURN();
} else if (!strcmp(mode, "zeroAngleVanilla")) {
double zeroRange = strtod(strtok_s(NULL, ":", &next_token), NULL);
double initSpeed = strtod(strtok_s(NULL, ":", &next_token), NULL);
double airFriction = strtod(strtok_s(NULL, ":", &next_token), NULL);
double boreHeight = strtod(strtok_s(NULL, ":", &next_token), NULL);
double zeroAngle = calculateVanillaZeroAngle(zeroRange, initSpeed, airFriction, boreHeight);
outputStr << DEGREES(zeroAngle);
strncpy_s(output, outputSize, outputStr.str().c_str(), _TRUNCATE);
EXTENSION_RETURN();
} else if (!strcmp(mode, "zeroAngle")) {
double zeroRange = strtod(strtok_s(NULL, ":", &next_token), NULL);
double muzzleVelocity = strtod(strtok_s(NULL, ":", &next_token), NULL);
double boreHeight = strtod(strtok_s(NULL, ":", &next_token), NULL);
double temperature = strtod(strtok_s(NULL, ":", &next_token), NULL);
double pressure = strtod(strtok_s(NULL, ":", &next_token), NULL);
double humidity = strtod(strtok_s(NULL, ":", &next_token), NULL);
double ballisticCoefficient = strtod(strtok_s(NULL, ":", &next_token), NULL);
int dragModel = strtol(strtok_s(NULL, ":", &next_token), NULL, 10);
char* atmosphereModel = strtok_s(NULL, ":", &next_token);
double zeroAngle = calculateZeroAngle(zeroRange, muzzleVelocity, boreHeight, temperature, pressure, humidity, ballisticCoefficient, dragModel, atmosphereModel);
outputStr << DEGREES(zeroAngle);
strncpy_s(output, outputSize, outputStr.str().c_str(), _TRUNCATE);
EXTENSION_RETURN();
}
strncpy_s(output, outputSize, outputStr.str().c_str(), _TRUNCATE);
EXTENSION_RETURN();
}
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