Flight characteristic comparison of STS and DTSbased on mathematical model

周亦成; 单鹏

doi:10.13224/j.cnki.jasp.2017.02.012

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Flight characteristic comparison of STS and DTSbased on mathematical model

更新时间：2026-07-07

- Flight characteristic comparison of STS and DTSbased on mathematical model
- Vol. 32, Issue 2, Pages: 344-353(2017)
- 作者机构：
  
  北京航空航天大学能源与动力工程学院,北京,100191
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2017.02.012
  CLC：
- Published：2017
- 稿件说明：
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周亦成, 单鹏. 基于数学模型的单级和双级涡轮增压活塞螺旋桨推进系统飞行特性比较[J]. 航空动力学报, 2017, 32(2): 344-353.

doi: 10.13224/j.cnki.jasp.2017.02.012
周亦成, 单鹏. 基于数学模型的单级和双级涡轮增压活塞螺旋桨推进系统飞行特性比较[J]. 航空动力学报, 2017, 32(2): 344-353. DOI： 10.13224/j.cnki.jasp.2017.02.012.

doi: 10.13224/j.cnki.jasp.2017.02.012 DOI：

摘要

研究了单级涡轮增压活塞螺旋桨推进系统(STS)的部件法数学模型

给出了STS的联合工作方程组

给出了STS的调节方式

计算了STS的高度速度特性.从总体及各部件的高度速度特性方面比较了STS和双级涡轮增压活塞螺旋桨推进系统(DTS).研究表明:选择的STS调节方式可满足其设计目标

相比于DTS实际功率保持高度为12.5km

STS的实际功率保持高度可达到5.5km；在选用相同的螺旋桨和发动机的前提下

STS和DTS中各部件特性的变化规律基本一致

但STS的推进效率、单位推力耗油率、推进系统总效率在高度速度特性图中的变化范围大大窄于DTS的.

Abstract

A componentlevel characteristic simulation method for singlestage turbocharging reciprocating engine propeller propulsion system (STS) was studied. A regulating method of STS was proposed

the jointworking equations of STS were solved

and the altitudevelocity characteristic of STS were simulated. The flying characteristics of overall performance and each component were compared between a STS and a dualstage turbocharging reciprocating engine propeller propulsion system (DTS). Result shows that

the regulating method of STS can meet the design objectives

the full power holding altitude of STS can achieve 5.5km while that of the DTS is 12.5km. When selecting the same propeller and engine

the characteristics of each component between STS and DTS are similar

and the variation ranges of the altitude and velocity of the propulsion efficiency

specific fuel consumption

total efficiency of STS are narrower than those of the DTS.

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Related Institution

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