main.py - master - talehunter/ballistics

main.py
238 строк7 KB
talehunter
autoformat
24 ноя 2025, 10:53
24 ноя 2025, 10:53924c8ec
import configparser
import numpy as np
from consts import (
    RE,
    RSE,
    RSJ,
    MSUN,
    ME,
    MJ,
    REO,
    RJOP,
    RJOA,
    P1G,
    E1G,
    E2G,
    THETTAG1,
    THETTAG2,
)
from graphics import draw_first, draw_second
from scipy.optimize import fsolve
from mathematic import v_001, v_002, alpha1, alpha2
from word import create_basic_report


class Homman:
    def calc(self):
        #   Гоммановский перелет
        e1 = (RSJ - RSE) / (RSJ + RSE)
        print(e1)
        p1 = RSJ * (1 - e1)
        print(p1)
        Va1 = (MSUN / p1) ** 0.5 * (1 - e1)
        print(Va1)
        Vp1 = (MSUN / p1) ** 0.5 * (1 + e1)
        print(Vp1)
        Ve = (MSUN / RSE) ** 0.5
        print(Ve)
        dV1 = Vp1 - Ve
        print(dV1)
        Vj = (MSUN / RSJ) ** 0.5
        print(Vj)
        dV2 = Vj - Va1
        print(dV2)
        Vg = dV1 + dV2
        print(Vg)
        #   отлет КА от Земли
        Veop = (ME / REO) ** 0.5
        print(Veop)
        Votl = (dV1**2 + (2 * ME / REO)) ** 0.5
        print(Votl)
        detlaVe = Votl - Veop
        print(detlaVe)
        #   промежуточная орбита вокруг Юпитера
        Vpril = (dV2**2 + (2 * MJ / RJOP)) ** 0.5
        print(Vpril)
        ej = (RJOA - RJOP) / (RJOA + RJOP)
        print(ej)
        pj = RJOA * (1 - ej)
        print(pj)
        Vaj = (MJ / pj) ** 0.5 * (1 - ej)
        print(Vaj)
        Vpj = (MJ / pj) ** 0.5 * (1 + ej)
        print(Vpj)
        delta_V12 = Vpril - Vpj
        print(delta_V12)
        T1 = (((p1 / (1 - e1**2)) ** 3 / MSUN) ** 0.5 * np.pi) / (60 * 60 * 24 * 365)
        config = configparser.ConfigParser()
        config.read("config.ini")
        config["Data"]["e1"] = str(e1)
        config["Data"]["p1"] = str(p1)
        config["Data"]["Ve"] = str(Ve)
        config["Data"]["Veop"] = str(Veop)
        config["Data"]["Vg"] = str(Vg)
        config["Data"]["T1"] = str(T1)
        config["Data"]["Vj"] = str(Vj)
        config["Data"]["Vpj"] = str(Vpj)
        with open("config.ini", "w") as configfile:
            config.write(configfile)
        draw_first()


class Grav_flight:
    def get_data(self):
        config = configparser.ConfigParser()
        config.read("config.ini")
        Ve = float(config["Data"]["Ve"])
        Veop = float(config["Data"]["Veop"])
        Ra2 = float(config["Data"]["Ra2"])
        return [Ve, Veop, Ra2]

    def equation(self, Ra2s, Rp2, n):
        time_seconds = 2 * 365 * 24 * 60 * 60
        result = (np.cbrt(((time_seconds / (2 * np.pi)) ** 2) * MSUN)) * 2 - Rp2
        return result

    def calc(self):
        n = 2
        Rp2 = RSE
        print(Rp2)
        Ra2 = self.equation(0, Rp2, n)
        Ra2 = round(Ra2, 5)
        print(f"Апогей орбиты: {Ra2:.2e} км")
        config = configparser.ConfigParser()
        config.read("config.ini")
        config["Data"]["Ra2"] = str(Ra2)
        with open("config.ini", "w") as configfile:
            config.write(configfile)
        e2 = (Ra2 - Rp2) / (Ra2 + Rp2)
        print(f"e2:{e2}")
        p2 = Ra2 * (1 - e2)
        print(f"p2:{p2}")
        Va2 = np.sqrt(MSUN / p2) * (1 - e2)
        print(f"Va2:{Va2}")
        Vp2 = np.sqrt(MSUN / p2) * (1 + e2)
        print(f"Vp2:{Vp2}")
        Ve = self.get_data()[0]
        Veop = self.get_data()[1]
        dV22 = Vp2 - Ve
        print(f"dV22:{dV22}")
        Votl2 = np.sqrt(dV22**2 + 2 * (ME / REO))
        print(f"Votl2:{Votl2}")
        delta_V21 = Votl2 - Veop
        print(f"delta_V21:{delta_V21}")
        config = configparser.ConfigParser()
        config.read("config.ini")
        config["Data"]["Va2"] = str(Va2)
        config["Data"]["dV21"] = str(delta_V21)
        with open("config.ini", "w") as configfile:
            config.write(configfile)

        self.second_graph()

    # гравитационный маневр у Земли
    def second_graph(self):
        Ve = self.get_data()[0]
        Ra2 = self.get_data()[2]
        Heobl = 559
        R = RE + Heobl
        print(R)
        config = configparser.ConfigParser()
        config.read("config.ini")
        config["Data"]["Ra2"] = str(Ra2)
        config["Data"]["Ve"] = str(Ve)
        config["Data"]["R"] = str(R)
        with open("config.ini", "w") as configfile:
            config.write(configfile)
        draw_second()


class Passive_grav_condition:
    # Условие существования пассивного гравитационного маневра

    def equations_1(self, args):
        theta1, theta2 = args
        eq1 = v_001(theta1) - v_002(theta2)
        eq2 = alpha1(theta1, theta2) - alpha2(theta1)
        return [eq1, eq2]

    def equations_2(self, args):
        i, theta2 = args
        eq1 = v_002(theta2) - i
        return eq1

    def calc(self):
        # Первое начальное приближение: θ1 = 0.7, θ2 = 0.2
        print("Решение 1:")
        args = [0.7, 0.2]
        solution1 = fsolve(self.equations_1, args)
        theta1_sol1, theta2_sol1 = solution1

        print(f"θ1 = {theta1_sol1:.6f}")
        print(f"θ2 = {theta2_sol1:.6f}")

        # Второе начальное приближение: θ1 = 1.5, θ2 = 2.0
        print("Решение 2:")
        args = [1.5, 2.0]
        solution2 = fsolve(self.equations_1, args)
        theta1_sol2, theta2_sol2 = solution2


class Fuel_costs:
    def get_data(self):
        config = configparser.ConfigParser()
        config.read("config.ini")
        Va2 = float(config["Data"]["Va2"])
        Vj = float(config["Data"]["Vj"])
        Vpj = float(config["Data"]["Vpj"])
        dV21 = float(config["Data"]["dV21"])
        Ra2 = float(config["Data"]["Ra2"])
        return [Va2, Vj, Vpj, dV21, Ra2]

    def calc(self):
        Va2 = self.get_data()[0]
        Vj = self.get_data()[1]
        Vpj = self.get_data()[2]
        dV21 = self.get_data()[3]
        Ra2 = self.get_data()[4]
        dV1 = Va2 - (MSUN / P1G) ** 0.5 * (1 - E1G)
        print(dV1)
        dV2 = ((Vj - (MSUN / P1G) ** 0.5 * (1 - E2G)) ** 2 + 2 * MJ / RJOP) ** 0.5 - Vpj
        print(dV2)
        dVsum = dV1 + dV2 + dV21
        print(dVsum)
        k1 = np.sqrt(((Ra2 + RSE) / 2) ** 3 / MSUN) * np.pi
        k2 = np.sqrt((Ra2 / (1 + E1G)) ** 3 / MSUN)
        k3 = np.sqrt((RSJ / (1 + E2G)) ** 3 / MSUN)
        t1 = np.arccos((np.cos(THETTAG1) + E1G) / (1 + E1G * np.cos(THETTAG1)))
        t2 = np.arccos((np.cos(THETTAG2) + E2G) / (1 + E2G * np.cos(THETTAG2)))
        Tg = (
            k1
            + k2 * np.pi
            + k2 * (t1 - E1G * np.sin(t1))
            + k3 * np.pi
            + k3 * (t2 - E2G * np.sin(t2))
        ) / (3600 * 24 * 365)
        print(Tg)
        config = configparser.ConfigParser()
        config.read("config.ini")
        config["Data"]["dVg"] = str(dVsum)
        config["Data"]["Tg"] = str(Tg)
        with open("config.ini", "w") as configfile:
            config.write(configfile)


def main():
    homman = Homman()
    homman.calc()
    obj = Grav_flight()
    obj.calc()
    obj = Passive_grav_condition()
    obj.calc()
    obj = Fuel_costs()
    obj.calc()
    create_basic_report()


if __name__ == "__main__":
    main()