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以共轴刚性双旋翼直升机为研究对象,对其飞行性能展开研究。首先,建立了考虑双旋翼间干扰、旋翼以及机身对尾推的干扰、旋翼对机身及尾翼干扰的直升机飞行力学模型。其次,建立了共轴刚性双旋翼直升机需用功率计算模型,以X2直升机为算例,计算了其配平状态下的需用功率,并用文献中的试验数据对需用功率计算结果进行了验证。然后,建立了发动机功率与耗油率模型以及直升机飞行性能计算模型。最后,计算并对比了X2直升机带推力螺旋桨模式和纯直升机模式下的飞行性能。研究结果表明,带推力螺旋桨模式的直升机飞行性能优于纯直升机模式的飞行性能。
Abstract：In this paper, coaxial rigid twin rotor helicopter was taken as the research object, and its flight performance was studied. Firstly, a helicopter flight dynamics model considering the aerodynamic interference between twin rotors, the aerodynamic interference of rotor and fuselage to tail thrust, and the aerodynamic interference of rotor to fuselage and empennage was established. Secondly, a calculation model of required power for coaxial rigid helicopter was established. Taking the X2 helicopter as an example the required power under trim state was calculated, and the calculation results were compared with the test data in the references. The models of engine power and fuel consumption rate and helicopter flight performance were established. Finally, the flight performance of X2 helicopter with thrust propeller mode and pure helicopter mode were calculated and compared. It is found that the flight performance of helicopter with thrust propeller mode is better than that of pure helicopter mode.
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基本信息:
DOI：10.13645/j.cnki.f.d.20210811.004
中图分类号:V212.4
引用信息:
[1]田刚印.基于配平的共轴刚性双旋翼直升机飞行性能计算与分析[J].飞行力学,2021,39(05):24-30.DOI:10.13645/j.cnki.f.d.20210811.004.
2021-08-11
2021-08-11
2021-08-11