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弹箭与制导学报 >

2025 , Vol. 45 >Issue 6: 1249 - 1257

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2025.06.036

学术文章

亚轨道/临近空间空天运输轨道设计与对比

  • 魏喜庆 , 1 ,
  • 翟文涛 2 ,
  • 杜厦 3, 4 ,
  • 史翔宇 1 ,
  • 李建敦 , 1, *
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  • 1 上海电机学院,上海 201306
  • 2 上海卫星工程研究所,上海 201100
  • 3 西北工业大学宁波研究院,浙江 宁波 315103
  • 4 宁波天擎航天科技有限公司,浙江 宁波 315048
李建敦(1982—),男,副教授,博士。E-mail:。

魏喜庆(1982—),男,讲师,博士。E-mail:。

收稿日期: 2025-03-12

  网络出版日期: 2026-01-24

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Orbital Design and Comparison of Sub-orbital/Near-space Long-range Aerospace Transport Spacecraft

  • WEI Xiqing , 1 ,
  • ZHAI Wentao 2 ,
  • DU Sha 3, 4 ,
  • SHI Xiangyu 1 ,
  • LI Jiandun , 1, *
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  • 1 Shanghai Dianji University,Shanghai 201306,China
  • 2 Shanghai Institute of Satellite Engineering,Shanghai 201100,China
  • 3 Ningbo institute of Northwestern Polytechnical University,Ningbo 315103,Zhejiang China
  • 4 Ningbo Tianqing Aerospace Technology Co., Ltd,Ningbo 315048,Zhejiang China

Received date: 2025-03-12

  Online published: 2026-01-24

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摘要

针对洲际高速运输及全球范围快速精确打击需求,本文创新性提出基于不同空域特性的两种轨道设计方案。针对依靠惯性滑翔的亚轨道飞行器方案,通过动力学建模建立速度矢量解算方法,并结合齐奥尔科夫斯基方程精确计算燃料需求。对于临近空间高超声速飞行方案,构建巡航数学模型并基于升阻比特性推导超燃冲压发动机燃料方程。理论计算与数值仿真表明:两种方案在燃料消耗方面呈现显著的航程相关性,且存在明确的技术优势交叉点——当航程超过临界值时,轨道飞行器燃料需求显著低于高超声速方案。特别地,临近空间飞行器的性能不仅与航程相关,更与升阻比参数密切耦合。本研究通过系统对比两种轨道方案的技术特性,为空天运输飞行器设计提供了理论依据与量化决策支持。

关键词： 轨道; 航天器; 高超声速; 飞行轨迹; 运输

本文引用格式

魏喜庆 , 翟文涛 , 杜厦 , 史翔宇 , 李建敦 . 亚轨道/临近空间空天运输轨道设计与对比[J]. 弹箭与制导学报, 2025 , 45(6) : 1249 -1257 . DOI: 10.15892/j.cnki.djzdxb.2025.06.036

Abstract

To address the requirements of intercontinental high-speed transportation and global precision strike capabilities,this study innovatively proposes a dual-mode orbital design scheme based on distinct aerospace domain characteristics.For the suborbital vehicle scheme utilizing inertial gliding,a velocity vector resolution method is established through dynamic modeling,combined with Tsiolkovsky’s equation for precise fuel requirement calculation.Regarding the near-space hypersonic flight scheme,a cruise mathematical model is constructed and scramjet engine fuel equations are derived based on lift-to-drag ratio characteristics.Theoretical calculations and numerical simulations reveal that both schemes exhibit significant range-dependent fuel consumption characteristics with a defined technological advantage crossover point:beyond critical range thresholds,orbital vehicles demonstrate substantially lower fuel demands compared to baseline hypersonic solutions.Notably,near-space vehicle performance shows strong coupling with both range and lift-to-drag ratio parameters.Through systematic comparison of technical characteristics between the two orbital schemes,this research provides theoretical foundations and quantitative decision-making support for aerospace transportation vehicle design.

Key words： Orbits; Spacecraft; Hypersonic; Flight trajectories; Transportation

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