利用 C++ 优化火箭发动机性能

#include <iostream>
#include <cmath>
#include <vector>

using namespace std;

class RocketEngine {
public:
  // Constructor
  RocketEngine(double nozzle_shape, double propellant_composition, double combustion_chamber_geometry) {
    this->nozzle_shape = nozzle_shape;
    this->propellant_composition = propellant_composition;
    this->combustion_chamber_geometry = combustion_chamber_geometry;
  }

  // Calculate thrust
  double calculate_thrust() {
    // Implement thrust calculation using relevant equations
  }

  // Calculate specific impulse
  double calculate_specific_impulse() {
    // Implement specific impulse calculation using relevant equations
  }

  // Calculate efficiency
  double calculate_efficiency() {
    // Implement efficiency calculation using relevant equations
  }

  // Getters and setters for parameters
  double get_nozzle_shape() { return nozzle_shape; }
  void set_nozzle_shape(double value) { nozzle_shape = value; }

  double get_propellant_composition() { return propellant_composition; }
  void set_propellant_composition(double value) { propellant_composition = value; }

  double get_combustion_chamber_geometry() { return combustion_chamber_geometry; }
  void set_combustion_chamber_geometry(double value) { combustion_chamber_geometry = value; }

private:
  double nozzle_shape;
  double propellant_composition;
  double combustion_chamber_geometry;
};

int main() {
  // Create a rocket engine with initial parameters
  RocketEngine engine(0.5, 0.7, 0.8);

  // Define optimization algorithm and objective function
  GeneticAlgorithm optimizer;
  double objective_function = [](RocketEngine &engine) { return engine.calculate_thrust() * engine.calculate_specific_impulse(); };

  // Run optimization algorithm
  optimizer.optimize(engine, objective_function);

  // Print optimized parameters and engine performance
  cout << "Optimized nozzle shape: " << engine.get_nozzle_shape() << endl;
  cout << "Optimized propellant composition: " << engine.get_propellant_composition() << endl;
  cout << "Optimized combustion chamber geometry: " << engine.get_combustion_chamber_geometry() << endl;
  cout << "Thrust: " << engine.calculate_thrust() << endl;
  cout << "Specific impulse: " << engine.calculate_specific_impulse() << endl;
  cout << "Efficiency: " << engine.calculate_efficiency() << endl;

  return 0;
}