卫星位置计算类输入的参数是:卫星号C01,卫星观测时刻[583周, 191194.8743073459周内秒]。卫星位置计算类从存储星历的数据数组中搜索对应星历(备注:使用的Rinex文件为下发的N文件),计算卫星位置坐标,在控制台输出计算得到的卫星位置坐标(参考结果-32348377.088,27042006.235,509548.303)。c++头文件,主函数,测试函数
时间: 2024-03-12 22:48:02 浏览: 135
以下是一个简单的卫星位置计算类的C++实现,包括头文件、主函数和测试函数:
头文件 SatellitePosition.h:
```c++
#ifndef SATELLITEPOSITION_H
#define SATELLITEPOSITION_H
#include <vector>
class SatellitePosition {
public:
SatellitePosition(const std::string& filename);
std::vector<double> getPosition(int satelliteNumber, double observationTime);
private:
std::vector<std::vector<double>> ephemerisData;
};
#endif // SATELLITEPOSITION_H
```
实现文件 SatellitePosition.cpp:
```c++
#include "SatellitePosition.h"
#include <fstream>
#include <sstream>
#include <cmath>
SatellitePosition::SatellitePosition(const std::string& filename) {
std::ifstream in(filename);
if (!in.is_open()) {
throw std::runtime_error("Failed to open file.");
}
std::string line;
while (std::getline(in, line)) {
if (line.find("END OF HEADER") != std::string::npos) {
break;
}
}
while (std::getline(in, line)) {
std::stringstream ss(line);
int satelliteNumber;
double epochTime;
ss >> satelliteNumber >> epochTime;
if (satelliteNumber == 0) {
continue;
}
std::vector<double> data;
double value;
while (ss >> value) {
data.push_back(value);
}
ephemerisData.push_back({satelliteNumber, epochTime, data});
}
}
std::vector<double> SatellitePosition::getPosition(int satelliteNumber, double observationTime) {
std::vector<double> position;
for (const auto& data : ephemerisData) {
if (data[0] == satelliteNumber) {
double t0 = data[1];
double dt = observationTime - t0;
if (dt < 0) {
continue;
}
double tk = dt / 3600.0;
const auto& ephemeris = data[2];
double a = ephemeris[0];
double e = ephemeris[1];
double i0 = ephemeris[2];
double omega = ephemeris[3];
double omegaDot = ephemeris[4];
double M0 = ephemeris[5];
double n0 = std::sqrt(3.986005e14 / (a * a * a));
double n = n0 + ephemeris[11];
double Mk = M0 + n * tk;
double Ek = Mk + e * std::sin(Mk);
double vk = std::atan2(std::sqrt(1.0 - e * e) * std::sin(Ek), std::cos(Ek) - e);
double phik = i0 + ephemeris[6] * std::cos(vk);
double lambdak = omega + (omegaDot - 7.2921151467e-5) * tk - 1.5e-9 * tk * tk;
position.push_back(a * (std::cos(Ek) - e));
position.push_back(a * std::sqrt(1.0 - e * e) * std::sin(Ek));
position.push_back(0);
double cos_phik = std::cos(phik);
double sin_phik = std::sin(phik);
double cos_lambdak = std::cos(lambdak);
double sin_lambdak = std::sin(lambdak);
position.push_back(-sin_phik * cos_lambdak);
position.push_back(-sin_phik * sin_lambdak);
position.push_back(cos_phik);
break;
}
}
return position;
}
```
主函数 main.cpp:
```c++
#include "SatellitePosition.h"
#include <iostream>
int main() {
SatellitePosition sp("N.txt");
auto position = sp.getPosition(1, 583 * 604800 + 191194.8743073459);
std::cout << position[0] << ", " << position[1] << ", " << position[2] << std::endl;
return 0;
}
```
测试函数 test.cpp:
```c++
#include "SatellitePosition.h"
#include <iostream>
#include <cassert>
void test() {
SatellitePosition sp("N.txt");
auto position = sp.getPosition(1, 583 * 604800 + 191194.8743073459);
assert(std::abs(position[0] + 32348377.088) < 1e-3);
assert(std::abs(position[1] - 27042006.235) < 1e-3);
assert(std::abs(position[2] - 509548.303) < 1e-3);
}
int main() {
test();
return 0;
}
```
其中,N.txt是Rinex文件,包含卫星的星历数据。在主函数中,首先创建了一个SatellitePosition对象,将Rinex文件作为参数传入。然后调用getPosition函数,传入卫星号和观测时刻,即可得到卫星的位置坐标。在测试函数中,通过断言来判断计算结果是否与参考结果相符。