Qt 飞行控件（记录下载地址用）

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前言

  一款用Qt做的飞行控件程序，从https://goldenhawking.blog.youkuaiyun.com/article/details/78817426?spm=1001.2014.3001.5506
这篇博客上看到的，但这篇博客里提到的两处源码地址都已经失效了，幸好之前我做过保存，可以从此处下载。
  声明，此处保存保存的代码仅为方便个人研究学习使用，严禁用于商业用途，如产生任何问题，与本人无关。

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效果

  工程文件夹内文档结构如下图所示

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mainwindow.cpp

#include <iostream>
#include <cmath>

#include "MainWindow.hpp"
#include "ui_MainWindow.h"

MainWindow::MainWindow(QWidget* parent) : QMainWindow(parent), m_ui(new Ui::MainWindow)
{
    m_ui->setupUi(this);
    m_timerId = startTimer(0);
    m_time.start();
}

MainWindow::~MainWindow()
{
    std::cout << "Average time step: " << static_cast<double>(m_realTime / m_steps) << " s" << std::endl;

    if ( m_timerId ) killTimer( m_timerId );

    if ( m_ui ) { delete m_ui; m_ui = nullptr; }
}

void MainWindow::timerEvent(QTimerEvent* event)
{
    QMainWindow::timerEvent( event );

    const float timeStep{static_cast<float>(m_time.restart())};

    m_realTime = m_realTime + timeStep / 1000.0f;

    float alpha{};
    float beta{};
    float roll{};
    float pitch{};
    float heading{};
    float slipSkid{};
    float turnRate{};
    float devH{};
    float devV{};
    float airspeed{};
    float altitude{};
    float pressure{28.0f};
    float climbRate{};
    float machNo{};
    float adf{};
    float dme{};

    if ( m_ui->pushButtonAuto->isChecked() ) {
        alpha     =   20.0f * std::sin( m_realTime /  10.0f );
        beta      =   15.0f * std::sin( m_realTime /  10.0f );
        roll      =  180.0f * std::sin( m_realTime /  10.0f );
        pitch     =   90.0f * std::sin( m_realTime /  20.0f );
        heading   =  360.0f * std::sin( m_realTime /  40.0f );
        slipSkid  =    1.0f * std::sin( m_realTime /  10.0f );
        turnRate  =    7.0f * std::sin( m_realTime /  10.0f );
        devH      =    1.0f * std::sin( m_realTime /  20.0f );
        devV      =    1.0f * std::sin( m_realTime /  20.0f );
        airspeed  =  125.0f * std::sin( m_realTime /  40.0f ) +  125.0f;
        altitude  = 9000.0f * std::sin( m_realTime /  40.0f ) + 9000.0f;
        pressure  =    2.0f * std::sin( m_realTime /  20.0f ) +   30.0f;
        climbRate =  650.0f * std::sin( m_realTime /  20.0f );
        machNo    = airspeed / 650.0f;
        adf       = -360.0f * std::sin( m_realTime /  50.0f );
        dme       =   99.0f * std::sin( m_realTime / 100.0f );

        m_ui->spinBoxAlpha->setValue(alpha);
        m_ui->spinBoxBeta->setValue(beta);
        m_ui->spinBoxRoll->setValue(roll);
        m_ui->spinBoxPitch->setValue(pitch);
        m_ui->spinBoxSlip->setValue(slipSkid);
        m_ui->spinBoxTurn->setValue(turnRate);
        m_ui->spinBoxDevH->setValue(devH);
        m_ui->spinBoxDevV->setValue(devV);
        m_ui->spinBoxHead->setValue(heading);
        m_ui->spinBoxSpeed->setValue(airspeed);
        m_ui->spinBoxMach->setValue(machNo);
        m_ui->spinBoxAlt->setValue(altitude);
        m_ui->spinBoxPress->setValue(pressure);
        m_ui->spinBoxClimb->setValue(climbRate);
        m_ui->spinBoxADF->setValue(adf);
        m_ui->spinBoxDME->setValue(dme);
    } else {
        alpha     = static_cast<float>(m_ui->spinBoxAlpha->value());
        beta      = static_cast<float>(m_ui->spinBoxBeta->value());
        roll      = static_cast<float>(m_ui->spinBoxRoll->value());
        pitch     = static_cast<float>(m_ui->spinBoxPitch->value());
        heading   = static_cast<float>(m_ui->spinBoxHead->value());
        slipSkid  = static_cast<float>(m_ui->spinBoxSlip->value());
        turnRate  = static_cast<float>(m_ui->spinBoxTurn->value());
        devH      = static_cast<float>(m_ui->spinBoxDevH->value());
        devV      = static_cast<float>(m_ui->spinBoxDevV->value());
        airspeed  = static_cast<float>(m_ui->spinBoxSpeed->value());
        pressure  = static_cast<float>(m_ui->spinBoxPress->value());
        altitude  = static_cast<float>(m_ui->spinBoxAlt->value());
        climbRate = static_cast<float>(m_ui->spinBoxClimb->value());
        machNo    = static_cast<float>(m_ui->spinBoxMach->value());
        adf       = static_cast<float>(m_ui->spinBoxADF->value());
        dme       = static_cast<float>(m_ui->spinBoxDME->value());
    }

    m_ui->widgetPFD->setFlightPathMarker(alpha, beta);
    m_ui->widgetPFD->setRoll(roll);
    m_ui->widgetPFD->setPitch(pitch);
    m_ui->widgetPFD->setSlipSkid(slipSkid);
    m_ui->widgetPFD->setTurnRate(turnRate / 6.0f);
    m_ui->widgetPFD->setDevH(devH);
    m_ui->widgetPFD->setDevV(devV);
    m_ui->widgetPFD->setHeading(heading);
    m_ui->widgetPFD->setAirspeed(airspeed);
    m_ui->widgetPFD->setMachNo(machNo);
    m_ui->widgetPFD->setAltitude(altitude);
    m_ui->widgetPFD->setPressure(pressure);
    m_ui->widgetPFD->setClimbRate(climbRate / 100.0f);

    m_ui->widgetNAV->setHeading(heading);
    m_ui->widgetNAV->setHeadingBug(0.0f);
    m_ui->widgetNAV->setCourse(0.0f);
    m_ui->widgetNAV->setBearing(adf, true);
    m_ui->widgetNAV->setDeviation(devH, true);
    m_ui->widgetNAV->setDistance(dme, true);

    m_ui->widgetSix->setRoll(roll);
    m_ui->widgetSix->setPitch(pitch);
    m_ui->widgetSix->setAltitude(altitude);
    m_ui->widgetSix->setPressure(pressure);
    m_ui->widgetSix->setAirspeed(airspeed);
    m_ui->widgetSix->setHeading(heading);
    m_ui->widgetSix->setSlipSkid(slipSkid * 15.0f);
    m_ui->widgetSix->setTurnRate(turnRate);
    m_ui->widgetSix->setClimbRate(climbRate);

    m_ui->widgetPFD->update();
    m_ui->widgetNAV->update();
    m_ui->widgetSix->update();

    m_steps++;
}

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资源下载

本次实验全部代码请至此处下载。

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