Entry flight performance is assessed for single-stage discrete-event drag-modulation trajectory control on Mars with two different real-time guidance algorithms: a heuristic velocity trigger and numerical predictor–corrector. Three degree-of-freedom simulation and Monte Carlo techniques are used to determine flight performance across a range of mission and vehicle design parameters. Trends are identified in flight performance across different initial conditions, ballistic-coefficient ratios, and target ranges. Results indicate that both guidance algorithms can provide landing accuracy better than 10 km across likely vehicle properties and entry conditions. The heuristic velocity trigger performs nearly as well as the numerical predictor–corrector for low-ballistic-coefficient ratios and entry flight-path angles steeper than approximately $–18\mathrm{deg}$. The numerical predictor–corrector provides consistent flight performance across all feasible mission and vehicle parameters with accuracy better than approximately 5 km. Overall, single-stage discrete-event drag-modulation trajectory control is a feasible option for accurate landings for ballistic coefficients below approximately $140{\mathrm{kg}/\mathrm{m}}^2$ and landed altitudes above 0 km.

通过两种不同的实时制导算法：启发式速度触发和数值预测器-校正器，评估了火星单级离散事件阻力调制轨迹控制的进入飞行性能。三自由度仿真和蒙特卡洛技术用于确定一系列任务和车辆设计参数的飞行性能。可以确定不同初始条件，弹道系数和目标范围内飞行性能的趋势。结果表明，两种制导算法都可以在可能的车辆性能和进入条件下提供优于10 km的着陆精度。启发式速度触发器的性能几乎与数值预测器–弹道系数低且进入飞行路径角度比大约陡峭的校正器要好$--\mathrm{18岁}度$。数值预报器–校正器可在所有可行的任务和飞行器参数上提供稳定的飞行性能，其准确度优于约5 km。总体而言，单级离散事件阻力调制轨迹控制是精确降落弹道系数约低于10的可行选择。$140{\mathrm{公斤}/\mathrm{米}}^2$ 并在0公里以上降落。