【作者】 张耀磊；

【导师】 唐硕；

【作者基本信息】 西北工业大学 ， 飞行器设计， 2006， 硕士

【摘要】 并联两级可重复使用运载器(Reusable launch vehi cle—RLV)是由升力体外形的轨道器和升力体外形的助推器并联组成的、以火箭发动机为动力、垂直起飞、水平着陆的两级可重复使用运载器。在上升飞行段轨道器和助推器分离前,助推器发动机提供上升总动力;分离后,助推器滑翔返回,水平着陆;而轨道器在分离点发动机点火,继续爬升入轨,完成在轨任务后返回,水平着陆。它不仅可以多次重复使用,还可以快速、方便地向空间运送有效载荷,较长时间地在轨停留和在轨机动,完成各种空间作业。RLV同时具有很高的军事和民用价值,受到高度重视。 RLV的研制技术难度大,系统集成性强,具有很多关键技术。在研制其物理样机之前,非常有必要建立RLV系统的虚拟样机,以优选设计方案、评估飞行器性能、验证关键技术设计。本文参考运载火箭、弹道导弹和航天飞机数学模型和运行过程,针对并联两级可重复使用运载器特性,将运行过程划分为上升段、级间分离段等九个飞行阶段,并给出相应数学模型,建立仿真模型。这些模型包括: 1.通用模型: 1) 基础算法库:包括常用坐标系定义、欧拉角的定义、仿真算法库的建立等; 2) 环境模型库:包括大气模型、地球模型、月球模型、太阳模型等: 3) 力与力矩模型库:包括动力系统、气动力与力矩、引力等。其中动力系统包括主推进系统、轨道机动系统和反作用控制系统; 4) 运动学与动力学模型库:包括质心与姿态的动力学和运动学方程。 2.分段模型: 1) 上升段模型:分为组合体上升和轨道器上升入轨: 2) 级间分离段模型:建立面对称并联式分离、轴对称并联分离和串联式分离; 3) 返回段模型:包括轨道再入段、能量管理段、进场着陆段; 4) 助推器返回模型:分为自由段、转弯段和滑翔到能量管理界面、能量管理段、进场着陆段。 在此基础上,并充分考虑样机的合理性、可重用性、可扩展性以及易用性,建立上升段、分离段、轨道器在轨段、轨道器再入段、轨道器能量管理段、轨道器着陆段、助推器返回段、助推器能量管理段和助推器着陆段九个独立的子系统,并建立RLV整个飞行过程的虚拟样机系统。从仿真结果和可靠性对比验证分析可知,该样机能够满足粗粒度的RLV仿真要求,得到的结果合理可信。更多还原

【Abstract】 Parallel-Two-Stage Reusable launch vehicle (RLV) is joined side-by-side by the orbiter and the roll booster, which are both of lift-body configurations. It is launched vertically, powered by engines, and lands horizontally. Before separation, RLV is thrust by the engines in the roll booster. And after separation, the roll booster glides back and lands horizontally, while the orbiter accents and enters orbit for a scheduled task. After finishing the task, the orbiter also glides back and lands horizontally. RLV is defined as a multifunctional spacecraft, which can be re-launched to conveniently transport payload to space. It can run in orbit for a long time and can also complete missions with flexibility. Because of its high value in military and civil fields, many countries have attached great importance to it and conducted out active plans to develop it.Consulting the flight program and mathematical models of rockets, missiles and space shuttles, this paper divides the RLV flight program into nine stages, including Accenting Stage, Separation Stage, and so on. Simulation models are built on the base of mathematical models. The models are as follows:1. Common Models:1) Basic Algorithm Library. There are different coordinate definitions in common use, e.g., the definition of used angles, the simulation algorithms library, and so on;2) Environment Model Library: The library includes Atmosphere Model, the Earth Model, and so on;3) Force and Moment Model: Power System and gravitation are included in the model. Power System includes Main Propulsion System (MPS), Reaction Control System (RCS) and Orbital Maneuver System (OMS);4) Motion Model: It includes Kinematics and Dynamics functions.2. Models by Stage:1) Accent Stage Model: Accent of RLV and the orbiter is included;2) Separation Model: Series-wound mode, parallel-plane symmetry mode and parallel-axial symmetry mode are defined to form Separation Model;3) Return Stage Model: Reentry, Energy Management and Auto-landing stages are analyzed to build Return Stage Model;4) Roll Booster Return Model: The model is made up of uncontrolled stageand so on;On the basis of mathematical models and basic simulation models, rationality, reusability, expansibility and convenience of VPM are considered to build the VPM system of RLV’s whole flight course, which includes nine subsystems such as Accent Stage Subsystem and so on.From the results of simulation, we can conclude that this prototype can meet the demands of the coarse granularity simulation in RLV system and present reasonable outcome.更多还原