The invention discloses a solar unmanned aerial vehicle design method which comprises the following steps: firstly, constructing an energy balance design feasible region and a weight balance feasible region of a solar unmanned aerial vehicle according to the weight and wing area of the solar unmanned aerial vehicle; then, according to the weight and wing area of the solar unmanned aerial vehicle, constructing a full-power expression of the solar unmanned aerial vehicle under a climbing rate constraint, a stable disc overload constraint, a maximum flight height constraint and a maximum flight speed constraint, and finally, taking a public area formed by the relational expressions as a design feasible region of the solar unmanned aerial vehicle; the design feasible region is constructed based on the weight and the wing area of the solar unmanned aerial vehicle, and is not based on the traditional design thought that the thrust-weight ratio is associated with the wing load any more; by associating the weight and the wing area of the solar unmanned aerial vehicle for design, the overall parameters of the solar unmanned aerial vehicle, such as the full-aircraft weight, the wing area and the subsystem weight, meeting the design requirements can be quickly obtained, and then engineers are guided to efficiently and conveniently carry out the scheme design work of the type of unmanned aerial vehicle.
本申请公开了一种太阳能无人机设计方法,首先根据太阳能无人机的重量和翼面积构建太阳能无人机的能量平衡设计可行域和重量平衡可行域,随后根据太阳能无人机的重量和翼面积构建太阳能无人机在爬升率约束、稳盘过载约束、最大飞行高度约束和最大飞行速度约束下的全功率表达式,最后将上述关系式构成的公共区域作为太阳能无人机的设计可行域;本申请的设计可行域是基于太阳能无人机的重量与翼面积构建,不再基于推重比与翼载荷关联的传统设计思路,通过关联太阳能无人机的重量和翼面积进行设计能够快速得到满足设计要求的太阳能无人机全机重量、翼面积、分系统重量等总体参数,进而指导工程师高效便捷的开展该类型无人机方案设计工作。
Solar unmanned aerial vehicle design method
一种太阳能无人机设计方法
2024-01-19
Patent
Electronic Resource
Chinese
IPC: | 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 |