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settings.py
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settings.py
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import math
import numpy as np
from numpy import seterr
seterr(all='raise')
# 最大迭代次数
# MAXITER = math.inf
MAXITER = 100000
# 初始时间
t0 = 0
# 传入制导模块的参数
# self: 仿真对象本身
# t: 全局时间
# iter: 迭代次数
ParamsToGuide = ["t", "self"]
# 仿真案例设置
cases = [
{'MissileInitStatus': {"t": 0,
"longitude": np.deg2rad(0),
"latitude": np.deg2rad(50),
"height": 80000,
"velocity": 7000,
"path_angle": np.deg2rad(0),
"heading_angle": np.deg2rad(15)},
'TargetInitStatus': {"longitude": np.deg2rad(165),
"latitude": np.deg2rad(40)},
'MissileEndStatus': {
"velocity": 2000,
"height": 2.5e4,
"s": 5e4}
},
{'MissileInitStatus': {"t": 0,
"longitude": np.deg2rad(0),
"latitude": np.deg2rad(50),
"height": 80000,
"velocity": 7000,
"path_angle": np.deg2rad(0),
"heading_angle": np.deg2rad(60)},
'TargetInitStatus': {"longitude": np.deg2rad(120),
"latitude": np.deg2rad(0)},
'MissileEndStatus': {
"velocity": 2000,
"height": 2.5e4,
"s": 5e4}
},
{'MissileInitStatus': {"t": 0,
"longitude": np.deg2rad(0),
"latitude": np.deg2rad(50),
"height": 80000,
"velocity": 7000,
"path_angle": np.deg2rad(0),
"heading_angle": np.deg2rad(120)},
'TargetInitStatus': {"longitude": np.deg2rad(90),
"latitude": np.deg2rad(-40)},
'MissileEndStatus': {
"velocity": 2000,
"height": 2.5e4,
"s": 5e4}
},
{'MissileInitStatus': {"t": 0,
"longitude": np.deg2rad(0),
"latitude": np.deg2rad(50),
"height": 80000,
"velocity": 7000,
"path_angle": np.deg2rad(0),
"heading_angle": np.deg2rad(180)},
'TargetInitStatus': {"longitude": np.deg2rad(10),
"latitude": np.deg2rad(-50)},
'MissileEndStatus': {
"velocity": 2000,
"height": 2.5e4,
"s": 5e4}
},
{'MissileInitStatus': {"t": 0,
"longitude": np.deg2rad(0),
"latitude": np.deg2rad(50),
"height": 80000,
"velocity": 7000,
"path_angle": np.deg2rad(0),
"heading_angle": np.deg2rad(-140)},
'TargetInitStatus': {"longitude": np.deg2rad(-50),
"latitude": np.deg2rad(-40)},
'MissileEndStatus': {
"velocity": 2000,
"height": 2.5e4,
"s": 5e4}
},
{'MissileInitStatus': {"t": 0,
"longitude": np.deg2rad(0),
"latitude": np.deg2rad(50),
"height": 80000,
"velocity": 7000,
"path_angle": np.deg2rad(0),
"heading_angle": np.deg2rad(-85)},
'TargetInitStatus': {"longitude": np.deg2rad(-90),
"latitude": np.deg2rad(0)},
'MissileEndStatus': {
"velocity": 2000,
"height": 2.5e4,
"s": 5e4}
},
{'MissileInitStatus': {"t": 0,
"longitude": np.deg2rad(0),
"latitude": np.deg2rad(50),
"height": 80000,
"velocity": 7000,
"path_angle": np.deg2rad(0),
"heading_angle": np.deg2rad(-10)},
'TargetInitStatus': {"longitude": np.deg2rad(-165),
"latitude": np.deg2rad(40)},
'MissileEndStatus': {
"velocity": 2000,
"height": 2.5e4,
"s": 5e4}
},
{'MissileInitStatus': {"t": 0,
"longitude": np.deg2rad(0),
"latitude": np.deg2rad(0),
"height": 80000,
"velocity": 7000,
"path_angle": np.deg2rad(0),
"heading_angle": np.deg2rad(89)},
'TargetInitStatus': {"longitude": np.deg2rad(80),
"latitude": np.deg2rad(0)},
'MissileEndStatus': {
"velocity": 2000,
"height": 2.5e4,
"s": 5e4}
},
]
# 测试通过0，1，2，3，4
#
case_num = 2
# 导弹初始化状态
MissileInitStatus = cases[case_num]['MissileInitStatus']
# 导弹终止状态
MissileEndStatus = cases[case_num]['MissileEndStatus']
# 目标初始状态
TargetInitStatus = cases[case_num]['TargetInitStatus']
# 制导相关参数
# 是否考虑最大倾侧角
CONSIDER_SIGMA_MAX = True
# K_GAMMA = 3 # 下降段攻角反馈系数
K_GAMMA_SGP = 3 # 滑翔段TDCT反馈系数
ERR_TOL = 3e-4 # 进入平稳滑翔段时弹道倾角与平稳滑翔弹道倾角的容忍误差
K_SIGMA = -50 # 最大倾侧角中的系数
K_ALPHA = 5 * np.pi / 1E7 / 1.8
# 要从制导参数直接导入到控制参数的值名称↓
CONTROL_PARAM_LIST = ["m", "attack_angle", "bank_angle"]
# 除控制参数和状态外要从制导模块保存的数据
GUIDE_SAVE_PARAM = [
# "sigma_max_L1",
# "sigma_max_Lmax",
# "sigma_max_dHmindE",
# "sigma_max_dHdE",
"sigma_max",
"gamma_sg",
"s_go",
"sgo_ref",
"ref_psi",
"delta_psi",
'q'
# "sigma_aap_aL2",
# "sigma_aap_deltaL2m"
]
# 更新EBR2时最大迭代次数
MAX_EBR2_ITER = 10
# 保存数据
STORE_DATA = f'store/data_saved/simulation_case{case_num}.csv'