hlpdlg.frm

vb 调用matlab方法实例

VERSION 5.00
Begin VB.Form hlpDlg 
   Caption         =   "Information"
   ClientHeight    =   6090
   ClientLeft      =   60
   ClientTop       =   345
   ClientWidth     =   7185
   LinkTopic       =   "Form1"
   MaxButton       =   0   'False
   MinButton       =   0   'False
   Moveable        =   0   'False
   ScaleHeight     =   6090
   ScaleWidth      =   7185
   StartUpPosition =   1  'CenterOwner
   Begin VB.CommandButton OKButton 
      Caption         =   "OK"
      Height          =   615
      Left            =   2280
      TabIndex        =   0
      Top             =   5160
      Width           =   2775
   End
   Begin VB.Label hlp_text 
      BorderStyle     =   1  'Fixed Single
      Height          =   4575
      Left            =   240
      TabIndex        =   1
      Top             =   240
      Width           =   6735
   End
End
Attribute VB_Name = "hlpDlg"
Attribute VB_GlobalNameSpace = False
Attribute VB_Creatable = False
Attribute VB_PredeclaredId = True
Attribute VB_Exposed = False
Private Sub Form_Activate()

Select Case main_form.selectMode.ListIndex
Case 0
  hlpStr = "This is a demonstration of tracking and orbit trajectories and paths.                                              " & _
  "                                                                                                                            " & _
  "               Mode1: Rocket and Plane                                                                                                       " & _
  "        This is a demonstration of number of interesting curves and trajectories " & _
  "of a rocket moving at constant speed while always pointing towards the moving " & _
  "plane. Such a method of tracking is known as dog-tracking. Simular " & _
  "trajectories are those followed by air-to-air and air-to-ground missiles. " & _
  "In this simulation you have the control of rocket velocity, plane velocity " & _
  "and plane trajectory. So you have the ability to compair different combination " & _
  "and find the best performance. " & _
  "The algorithm of this tracking is to change a velocity vector of the rocket " & _
  "every time step, that way the rocket always points in the direction of the " & _
  "plane. The main equation of vector tracking is:                                                                             " & _
  "                                                  v = v0 * (P - R) / |P - R|                                                                                                        " & _
  "where                                                                                                                                                  " & _
  "v - rocket velocity vector                                                                                                             " & _
  "v0 - rocket velocity modal value                                                                                                    " & _
  "P - plane state vector                                                                                                                   " & _
  "R - rocket state vector                                 "
   
 Case 1
  hlpStr = "Mode2: Four rockets                                                                                                " & _
  "                   This is a demonstration of trajectories " & _
  "followed by a four missiles catching each other. It can be seen " & _
  "that each missile always points in the direction of another " & _
  "missile. In this simulation you have the control of each rocket " & _
  "velocity. The algorithm of this tracking demonstration is simular " & _
  "to the previous algorithm with four dimensional implementation."

 Case 2
  hlpStr = "Mode3: Orbits                                                                                                               " & _
  "          This is a demonstration of orbits of planets " & _
  "and satellites that described by three Kepler''s laws " & _
  "or by Newton''s law of universal gravitation in case of " & _
  " the central force problem. The solution for this case " & _
  " may be written in polar form in this way:                                                   " & _
  "                        r = p / ( 1 + e*cos(phi) )                                                                                        " & _
  "            Where p is known as the parameter of the orbit, and " & _
  "e as the accentricity of the orbit. For " & _
  "different values of e the orbit take forms " & _
  "of circle, elipse, hyperbola and parabola. Physically the " & _
  "distinction between the different curves is determined by the total " & _
  "energy (potential plus kinetic) of moving mass."

 End Select
hlp_text.Caption = hlpStr

End Sub

Private Sub OKButton_Click()
  hlpDlg.Hide
End Sub