在未来海洋资源争夺中，海军对于两栖登陆及海域作战的装备需求越来越迫切。高速巡航垂直起降飞行器（High-Speed Vertical Take-Off and Landing Aircraft, 简称HSVTOL）兼具直升机和固定翼飞机的优点，成为未来两栖作战的首选装备。HSVTOL作为一种新概念飞行器，其概念设计尚未形成成熟的方法论，原有的飞机设计方法也不能直接套用。针对这一问题，本文围绕HSVTOL的概念设计方法展开了研究，主要工作如下：

（1）明确了HSVTOL的任务使命和性能要求，确定了其动力系统为涡轴-涡扇变循环发动机（TurboShaft-turboFan Variable Cycle Engine, 简称TSFVCE），总体布局采用可折叠倾转旋翼构型加延伸翼的方案。

（2）提出了一种针对HSVTOL的总体基本参数估算方法：首先基于燃油系数法估算最大起飞重量，然后针对不同性能要求进行约束分析并建立旋翼与机翼参数的关联关系，进而创建用于选取HSVTOL总体基本参数的“新型界限线图”。根据所选总体参数，完成了HSVTOL的气动外形设计和机体各部件的参数化建模，并针对HSVTOL的特殊构型设计了一套与之匹配的可折叠旋翼机构。

（3）计算分析了HSVTOL的重量特性、气动特性、飞行性能、操稳特性及倾转过渡走廊，其中，计算所得全机巡航升阻比为9.3，航程达到2583 km，最大巡航速度超过818 km/h，满足设计要求和性能指标。通过HSVTOL样机缩比模型风洞试验进一步验证了数值方法计算结果的可靠性及设计方案的合理性。

研究结果表明，本文所提出HSVTOL总体基本参数估算方法具有较高的可信度，基于此方法所形成的HSVTOL概念设计方案能够满足其设计要求和指标，具有较好的可靠性。

In the future competition for marine resources, the demand for equipment for amphibious landings and sea operations by navies is becoming increasingly urgent. High-Speed Vertical Take-Off and Landing Aircraft (HSVTOL), which combines the advantages of helicopters and fixed-wing aircraft, has emerged as the preferred equipment for future amphibious operations. As an emerging concept aircraft, HSVTOL lacks a mature methodology for its conceptual design, and existing aircraft design methods cannot be directly applied. To address this issue, this paper conducts research on the conceptual design method for HSVTOL. The main work is as follows:

(1) The mission objectives and performance requirements of the HSVTOL have been clearly defined, and the adoption of vertical takeoff and landing capabilities. The power system is determined to be a TurboShaft-turboFan Variable Cycle Engine (TSFVCE), and the overall layout employs a foldable tiltrotor configuration with extended wings.

(2) A method for estimating the basic parameters of the HSVTOL has been proposed: the maximum takeoff weight is estimated based on the fuel fraction method; constraint analyses are conducted for different performance requirements, and the correlation between rotor and wing parameters is established. A constraint diagram is created for selecting the basic parameters of the HSVTOL. Based on the selected basic parameters, the aerodynamic shape design of the HSVTOL and the parametric modeling of its various components are completed, and a set of foldable rotor mechanisms matching the special configuration of the HSVTOL is designed.

(3) The weight characteristics, aerodynamic properties, flight performance, handling and stability characteristics, and tilt-transition corridor of the HSVTOL are analyzed. With a cruise lift-to-drag ratio of 9.3, a range of 2583 km, and a max cruise speed exceeding 818 km/h, it meets design requirements. Wind tunnel tests with a scaled model verify the calculations and design rationality.

The research results demonstrate that the proposed method for estimating the basic parameters of HSVTOL has high credibility. The conceptual design scheme formed based on this method meets the design requirements and indicators with good reliability.

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