| 摘要 |
PURPOSE: A computer-readable recording medium including a 6DOF analysis program of a plane is provided to perform the analysis of the basic control, spin, and actual speed of a KC-100 plane by using 6DOF simulation. CONSTITUTION: A flight condition including an altitude, speed, power, and a trim option of a plane is inputted to a computer (S101). A former state variable, aerodynamic derivate data, weight data, and engine thrust data are initialized (S102). A trim state of a plane about the flight condition is calculated and the state variable is updated according to the trim state (S104). A standby condition about the flight condition is calculated to be updated (S105). A control input value including a value about each control surface of the plane and a value about a power lever is inputted to the computer (S106). [Reference numerals] (S101) Step where a support is given in order to input a flight condition including an altitude, speed, power, and a trim option of a plane to a computer; (S102) Step where a former state variable, aerodynamic derivate data, weight data, and engine thrust data are initialized; (S103) Step where the trim state of a plane about the flight condition, which has been inputted at the S101 step, is calculated; (S104) Step where the state variable is updated according to the trim state calculated at the S103 step; (S105) Step where a standby condition about the flight condition inputted at the S101 step is updated; (S106) Step where a support is given in order to input a control input value including a value about each control surface of the plane and a value about a power lever to the computer; (S107) Step where aerodynamic derivative data, weight data, and engine thrust data are calculated based on the flight condition inputted at the S101 step and the control input value inputted at the S106 step along with necessary variable values summoned from a simulation database; (S108) Step where the state variable is updated based on the aerodynamic derivative data, the weight data, and the engine thrust data calculated at the S107 step |
