The invention relates to a course controllability evaluation method for a tailless layout aircraft, and belongs to the technical field of aircraft evaluation. Comprising the following steps: acquiring aircraft parameters related to course; setting an evaluated state point; obtaining a course inertia coupling index according to a calculation formula of a yaw rate derivative; according to the sideslip angle dynamic equation, a course finite time convergence index is obtained through reasonable assumption calculation; comparing the maximum residual course moment coefficient with the course inertia coupling index and the absolute value of the course finite time convergence index, and judging whether the aircraft layout scheme meets the course inertia coupling index and the course controllability index or not. According to the method, course controllability indexes are designed based on the most original mechanical equation, evaluation can be carried out only through a few simple parameters of the aircraft, universality is achieved, and accurate evaluation is carried out on the layout of a brand new one-round aircraft in multiple states within a short time.
本发明涉及一种无尾布局飞机的航向可控性评估方法,属于飞行器评估技术领域。包括:获取与航向有关的飞机参数;设定评估的状态点;根据偏航速率导数的计算公式得到航向惯性耦合指标;根据侧滑角动态方程,通过合理的假设计算得到航向有限时间收敛指标;比较最大剩余航向力矩系数与所述航向惯性耦合指标、所述航向有限时间收敛指标绝对值大小,判断该飞机布局方案是否满足航向惯性耦合指标以及航向可控性指标。本发明方法依托最原始的力学方程,设计航向可控性指标,只需飞机少数几个简单参数即可评估,具有通用性,针对多种状态、短时间内对全新一轮飞机布局作精准评估。
Course controllability evaluation method for tailless layout aircraft
一种无尾布局飞机的航向可控性评估方法
2024-05-28
Patent
Electronic Resource
Chinese
IPC: | G06F ELECTRIC DIGITAL DATA PROCESSING , Elektrische digitale Datenverarbeitung / B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen |
Tailless layout large maneuvering flight course stability augmentation design method
European Patent Office | 2024
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