FLIGHT.mis a tutorial program, heavily commented to make interpretation easy. It provides a full six-degree-of-freedom simulation of an aircraft, as well as trimming calculations and the generation of a linearized model at any flight condition chosen by the user [1]. Changes to aircraft control histories, initial conditions, flag settings, and other program control actions are made by changing the numbers contained in the code; there is no separate user interface. The code has been designed for simplicity and clarity not for speed of execution, leaving a challenge to the reader to find ways to make the program run faster. Numerous additions could be made to the code, including implementation of feedback control logic, simulation of random turbulence or microburst wind shear, and interfaces for real-time execution. No explicit or implicit warranties are made regarding the accuracy or correctness of the computer code.
FLIGHT.mis the script that calls program functions. Initial conditions are defined here, the three primary features (trim, linearization, and simulation) are enabled, and output is generated. Initial perturbations to trim state and control allow transient effects to be simulated. As shown, trimming for steady, level flight is accomplished by first defining a cost function, J, that contains elements of the state rate, then minimizing the cost using the Downhill Simplex (Nelder-Mead) algorithm contained in fminsearch. The longitudinal trimming parameters are stabilator angle, throttle setting, and pitch angle. The linear model is generated by numjac, a numerical evaluation of the Jacobian matrices associated with the equations of motion. The linear model is saved to disk files in the variables Fmodel and Gmodel. MATLAB's ode23, ode45, or ode15s integrate the equations of motion to produce the state history. The state history is displayed in time plots, with angles converted from the radians used in calculation to degrees. The reader can readily change the units of plotted quantities or add additional plots through minor modifications to the code. Any result (e.g., numerical values of the state history) can be displayed in the MATLAB Command Window simply by removing the semi-colon at the end of the line. The flag MODEL selects either a low-angle-of-attack, Mach-dependent model for BizJet A [2] or a high-angle-of-attack, low-subsonic model for Bizjet B.

AeroModelMach.muses aerodynamic and dimensional data contained in [2] with estimates of inertial properties of the generic business jet. Details of the configuration, such as sweep and aspect ratio of the wing and tail, are used in the estimates of Mach effects. Estimates of Mach effects are based on the Prandtl factor or the modified Helmbold equation. AeroModelAlpha.m for BizJet B is derived using handbook methods for estimating geometric, inertial, and aerodynamic characteristics. The model is first built using GeoMassAero.m, which saves three .mat files describing the airplane: InerGeo.mat, DataTable.mat, and RotCont.mat. AeroModelAlpha.m loads the .mat files for use in FLIGHT.m. The angle-of attack range extends from -10 to 90 deg based on conventional low-alpha and Newtonian high-alpha estimates. No Mach, landing gear, spoiler, or flap effects are considered.

加工的运动方程。m是写使用平面地球假设[1]。临时的限制螺旋角的余弦值实施防止奇异计算在近乎垂直的飞行。这种权宜之计介绍附近的一个小错误当螺旋角+ / -90度。函数的事件。m指定一个停止条件终止前的仿真最后一次如果高度低于零。

纵倾控制设置最小化计算了纵向加速度(即二次函数。利率变化的轴向速度,正常速度,TrimCost中包含的音高)。m [1]。TrimCost。米加工。米来生成所需的加速度。的方向余弦矩阵(或旋转)在DCM的函数实现。m [1]。的矩阵变换向量earth-relative体轴框架的参照系。LinModel。m生产状态和控制雅可比矩阵的线性、定常模型调整设置。雅可比矩阵评估名义值的状态和控制。WindField。m produces a three-component wind vector as a function of altitude, with linear interpolation between tabulated points [1]. 1976 U.S. Standard Atmosphere air density, air pressure, air temperature, and sound speed are generated as functions of altitude by Atmos.m.

[1]斯坦格尔、飞行动力学,普林斯顿大学出版社,普林斯顿大学,2004年。
[2]Soderman, p . T。艾肯,t . N。”,全面的风洞测试一小T-Tail非机动的喷气式飞机,”NASA TN d - 6573,华盛顿特区,1971年11月。