Analying the current situation and the development trend of the carrier rocket engine technology in the world , combining with the characteristis of our rocket engine research institute , and searching the approach that enhance the research and innovation abiiity of catrier rocket engine have practical significance to accelerate technology progress and improve manufacture level 分析世界运载火箭发动机技术发展的现状及趋势，结合我国火箭发动机科研机构的特点，探索提高我国火箭发动机研究、创新能力的途径，对促进我国火箭发动机技术进步，提高火箭发动机研制水平有着重要的现实意义。
The paper anaiyzes the key elements which affect the ability of rescarch and innovation of different kinds of engines . the author raises the conception of carrier rocket engine working process research system : builds the structure model of carrier rocket engine working process research system by using the theory of operationai research and systems engineering : analyzes this structure model by the analytical hierarchy process : calculates the system element important degree and integrate important degree . the research result has some reference values to the rocket engine research institute building and strategy development 论文分析了影响不同类型火箭发动机研究、创新能力的各种因素，提出了运载火箭发动机工作过程研究体系的概念；综合应用系统工程、运筹学理论，建立了运载火箭发动机工作过程研究体系结构模型；对工作过程研究体系结构模型进行了层次分析，确定了体系的层次结构；分析了体系中各个要素的相对重要程度及综合重要程度。
According to purpose of the towed flight , a new trajectory consisting of taking off , climbing phase , level flight phase is presented with . trajectory pitch angle of the towing plane is optimized . according to the flight law of the towing plane , the fin deflection angle and amplification coefficient of particle - system trajectory of carrier rocket are designed , in order to realizing flight steadily of the carrier rocker 根据牵引飞行的目的，对载机应用了“起飞?爬升?平飞”的变轨道飞行方案，同时对载机轨道的倾角、倾角变化规律进行优选设计；再根据载机的飞行规律，对运载器质点系轨道的舵偏规律及其放大系数进行了设计计算，实现运载器稳定牵引飞行。
This paper analyzes the environment both at home and abroad of the carrier rocket engine working process research of the l lth research institute of china aerospace science & technology corporation . the author puts forward the management mode and the strategy plan of the carrier rocket engine working process research system building 论文分析了中国航天科技集团公司第十一研究所在火箭发动机工作过程研究领域面临的国际、国内环境；提出了十一所火箭发动机工作过程研究体系的管理模式、体系建设的战略步骤。
As far as the system observation for accuracy evaluation of carrier rocket is concerned , there may exist different types of observed data and priors . heterogeneous information means that the different information describing the different characteristics of the same object . since all of the information is relevant to the same object , the fusion is possible . it is a key problem that how to fuse the heterogeneous information to obtain the better evaluation result . therefore , the different heterogeneous information and data is thoroughly studied , moreover , the mathematical description for information fusion of different parameter priors and data is constructed in this paper . based on their relationship between different parameters , indirect prior and observation data is transformed into prior in impact point observation space , which is fused with original prior by weight determined by maximum entropy rule to obtain the mixed posterior distribution . therefore , the test results can be given by combining posterior distribution and impact error observed data . then its application on evaluating guidance systematic error is elaborated as it applies trajectory tracking data , test value of coefficients of guidance instrumentation systematic error , impact point observation data and prior . especially , the advantage of this method lies in its application in case that guidance instrumentation systematic error may not be computed precisely . finally a detailed example on evaluation of carrier rocket is given to verify the theory 为充分利用运载火箭观测中的不同观测空间和过程的信息来进行精度评估,针对该背景建立了异质先验融合的数学描述.研究了飞行试验中不同观测空间和过程的异质先验信息和数据,基于不同观测过程的解析关系,将间接过程的先验和观测数据算出的后验分布转换成落点观测空间上的先验,与原落点的先验进行了最大熵加权融合,得到混合后验分布,从而结合落点观测数据给出评定结果.在无法解算出精确的制导工具误差系数的情况下,这种方法充分利用了弹道跟踪数据、工具误差系数的地面测试先验值、落点先验及落点数据,稳健性更好,准确性更高
Secondly , towed system is considered as many rigid body systems . according to research approaches of many rigid body systematic dynamics , the towed systematic engagement calculating models is derived ; according to actual course of the towed flight , deriving mathematics model of the course of taking off and towed flight of the towing plane and of carrier rocket , and corresponding parameter calculate models 其次将牵引系统作为多刚体系统宋考虑，根据多刚体系统动力学研究方法，建立牵引系统约束方程，由此推导出约束力计算公式；根据牵引飞行实际过程，推导出载机、运载器在起飞阶段，巡航飞行阶段的数学模型，以及相应的参数计算模型。
Abstract : this paper discusses the simulation design for carrier rocket control system , designs simulation method for sub - system , presents the project of the function simulation training system basing on the digital simulation method with the sensitive component , puts forwards the realizing process and means 文摘:对运载火箭控制系统模拟仿真的总体设计和分系统模拟与设计进行了讨论，给出了以全数字仿真为基础，结合部分敏感元件，构成功能性模拟仿真训练系统的方案，提出了模拟实现的过程和手段。
