摘要
根据太阳能飞行器单点设计过程的特点,总结出太阳能飞行器的控制方程组,即升重平衡、推阻平衡和能量平衡方程。针对能量平衡的特点,将其分成全天能量闭环和夜间能量闭环,并就上述两个能量闭环分析太阳能飞行器的翼载荷设计边界,研究了由两个能量闭环所形成的翼载荷设计域,探讨了影响翼载荷设计域的参数敏感程度。进一步,基于翼载荷可行设计域提出了一种太阳能飞行器总体设计方法,并通过算例论证了该方法的有效性。本文工作对太阳能飞行器的设计过程有指导意义。
According to the single-point design feature of the solar-powered vehicle conceptual design, the governing equations of the solar-powered vehicle are summarized, that is the balance equations between thrust and drag, lift and gravity and the balance of energy. Based on the feature of the energy balance, the energy cycle is divided into whole-day energy cycle and night energy cycle. The wing load boundaries of the solar-powered vehicle are studied on the basis of the above two energy cycles, thus yielding the feasible design domain i.e. design envelop of the solar-powered vehicle. The sensitivities of design parameters to the feasible design domain are then analyzed. Further, a conceptual design method of the solar-powered vehicle is brought forward on the basis of the wing load analysis, and is verified by a case study. The wing load analysis and conceptual design method studied in this article can provide guidance for the solar-power vehicle design.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2014年第7期735-742,共8页
Journal of Astronautics
基金
国家自然科学基金(90916016)
关键词
太阳能飞行器
高空长航时
设计域
总体设计
翼载荷
Solar-powered airplane
High altitude and long endurance
Design domain
Conceptual design
Wing load
