//窗体加载时初始化
private void Form_Main_Load(object sender, EventArgs e)
{
int curveWidth = this.panel_mainCurve.Width;
int curveHeight = this.panel_mainCurve.Height;
//初始化自定义数据
eh = new ExcelHelper();
ca = new CAircraft();
cen = new CAtmosphere();
stopReason = "还未完成程序计算";
//SetAllTimerInterval(DEVMODEINTER);
ucHT = new Controllers.UserControlHT(curveWidth, curveHeight);
ucMT = new Controllers.UserControlMT(curveWidth, curveHeight);
ucHL = new Controllers.UserControlHL(curveWidth,curveHeight);
ucHM = new Controllers.UserControlHM(curveWidth, curveHeight);
FlightProfileLatterUnable();
//控制按钮初始化
this.btn_stop.Enabled = false;
this.btn_pause.Enabled = false;
this.btn_continue.Enabled = false;
realT = 0;
//飞机姿态初始
ucPW = new UserControlPlaneWpf();
this.elementHost_planeState.Child = ucPW;
//设置初始参数标志
gasSign = false;
engineSign = false;
paraSign = false;
rocketSign = false;
//文件保存路径的前缀
fileSavePathPre = Application.StartupPath+"\\DataSave";
if (!Directory.Exists(fileSavePathPre))
{
Directory.CreateDirectory(fileSavePathPre);
}
fileSavePath = fileSavePathPre;
DataSavePah = fileSavePathPre;
CurveSavePath = fileSavePathPre;
//火箭初始化
rocketPerT = 5000;
rocketI = 300;
rockNum = 0;
}
//计算模式计算
private void CalModeRun(double tTime, double qhTime)
{
//计算大气参数
this.cen = new CAtmosphere();
bool state0 = true;//滑行阶段
bool state1 = false;//飞行阶段
while (state0)
{
//计算大气参数
cen.Ae_qc = PlaneCal.CalQc(cen.Ae_rou, ca.A_V);
//读入发动机数据
double t, qh;
if (eh.CalZs(ca.A_engine1, ca.A_H, ca.A_Ma, out t, out qh))
{
ca.A_T = t * ca.A_engNum * tTime;
qh = qh * qhTime;
//更新数据
UpdateFaceControl();
Application.DoEvents();
//读取CY和CD
double CY, CD;
if (eh.CalZs(ca.A_gasCharac, ca.A_Ma, ca.A_alpha, out CD, out CY))
{
double G = PlaneCal.CalG(ca.A_m);
double Y = PlaneCal.CalY(cen.Ae_qc, ca.A_S, CY);
double D = PlaneCal.CalD(cen.Ae_qc, ca.A_S, CD) + ca.A_f * (G - Y);
double Fx = PlaneCal.CalFx(ca.A_T, 0, 0, D, Y);
double ax = PlaneCal.Calax(Fx, ca.A_m);
double vx1 = ca.A_V;
ca.A_V = PlaneCal.CalVx2(vx1, ax, DETT);
ca.A_Ma = ca.A_V / cen.Ae_a;
cen.Ae_qc = PlaneCal.CalQc(cen.Ae_rou, ca.A_V);
double detL = PlaneCal.CalDetL(vx1, DETT, ax);
double detM = PlaneCal.CalDetM(qh, DETT, t, ca.A_engNum);
ca.A_m -= detM;
ca.A_l += detL;
realT += DETT;
if (ca.A_l > ONEDISMAX)
{
state0 = false;
if (1 == tTime)
{
//改为全加力状态
InitCaPara(0, 0, 0, 0, 0, 0, ca.A_initM, FVALUE);
ClearCtolExtTBData();
realT = 0;
UpdateTBoxDataInfo("地面滑行阶段（全加力状态）" + Environment.NewLine);
//MessageBox.Show("改为全加力状态");
CalModeRun(TTIMES, QHTIMES);
}
else
{
stopReason = "起飞失败！全加力状态下滑行距离超过1000米";
AfterCalFail();
}
break;
}
else if (ca.A_V >= ONESPEEDLEVEL)
{
//MessageBox.Show("更改仰角");
ca.A_alpha = ONEALPHAMAX;
//cen.Ae_qc = PlaneCal.CalQc(cen.Ae_rou, ca.A_V);
//读入发动机数据
if (eh.CalZs(ca.A_engine1, 0, ca.A_Ma, out t, out qh))
{
ca.A_T = t * ca.A_engNum * tTime;
qh = qh * qhTime;
//更新数据
UpdateFaceControl();
Application.DoEvents();
//读取CY和CD
double Fz;
if (eh.CalZs(ca.A_gasCharac, ca.A_Ma, ca.A_alpha, out CD, out CY))
{
G = PlaneCal.CalG(ca.A_m);
Y = PlaneCal.CalY(cen.Ae_qc, ca.A_S, CY);
Fz = PlaneCal.CalFz(ca.A_T, ca.A_alpha, 0, 0, Y, G);
//UpdateTBoxDataInfo("===Fz:" + Fz + Environment.NewLine);
if (Fz > 0)
{
//进入下一阶段
state0 = false;
state1 = true;
//MessageBox.Show("进入飞行阶段");
break;
}
else
{
//计算运动过程
D = PlaneCal.CalD(cen.Ae_qc, ca.A_S, CD) + ca.A_f * (-1 * Fz);
Fx = PlaneCal.CalFx(ca.A_T, ca.A_alpha, ca.A_sigma, D, Y);
ax = PlaneCal.Calax(Fx, ca.A_m);
vx1 = PlaneCal.CalVx1(ca.A_V, ca.A_sigma);
ca.A_V = PlaneCal.CalVx2(vx1, ax, DETT);
ca.A_Ma = ca.A_V / cen.Ae_a;
cen.Ae_qc = PlaneCal.CalQc(cen.Ae_rou, ca.A_V);
detL = PlaneCal.CalDetL(vx1, DETT, ax);
detM = PlaneCal.CalDetM(qh, DETT, t, ca.A_engNum);
ca.A_m -= detM;
ca.A_l += detL;
realT += DETT;
if (ca.A_l > ONEDISMAX)
{
state0 = false;
if (1 == tTime)
{
//改为全加力状态
InitCaPara(0, 0, 0, 0, 0, 0, ca.A_initM, FVALUE);
ClearCtolExtTBData();
realT = 0;
UpdateTBoxDataInfo("地面滑行阶段（全加力状态）" + Environment.NewLine);
//MessageBox.Show("改为全加力状态");
CalModeRun(TTIMES, QHTIMES);
}
else
{
stopReason = "起飞失败！全加力状态下滑行距离超过1000米";
AfterCalFail();
}
break;
}
else
{
if (eh.CalZs(ca.A_engine1, 0, ca.A_Ma, out t, out qh))
{
ca.A_T = t * ca.A_engNum * tTime;
qh = qh * qhTime;
if (eh.CalZs(ca.A_gasCharac, ca.A_Ma, ca.A_alpha, out CD, out CY))
{
Y = PlaneCal.CalY(cen.Ae_qc, ca.A_S, CY);
G = PlaneCal.CalG(ca.A_m);
Fz = PlaneCal.CalFz(ca.A_T, ca.A_alpha, 0, 0, Y, G);
}
}
//UpdateTBoxDataInfo("===Fz:" + Fz + Environment.NewLine);
if (Fz > 0)
{
//进入下一阶段
state0 = false;
state1 = true;
//MessageBox.Show("进入飞行阶段");
break;
}
else
{
ca.A_alpha = 0;
}
}
}
}
else
{
stopReason = "气动力特性数据越界";
AfterCalFail();
break;
}
}
else
{
stopReason = "发动机数据越界";
AfterCalFail();
break;
}
}
}
else
{
stopReason = "气动力特性数据越界";
AfterCalFail();
break;
}
}
else
{
stopReason = "发动机数据越界";
AfterCalFail();
break;
}
}
if (state1)
{
ca.A_f = 0;
CalModeAngleOpt();
}
}