教练机发动机使用任务循环推导

在大量的外场统计和空测的基础上, 对某教练机发动机的外场使用载荷进行了分析研究, 推导出了其使用任务循环, 并与MIL-STD-1783进行了对比分析, 为国产同类新型教练机发动机的设计任务循环的预测奠定了基础。      

Unmanned aerial vehicle swarm mission reliability modeling and evaluation method oriented to systematic and networked mission

With the development of Unmanned Aerial Vehicle (UAV) system autonomy, network communication technology and group intelligence theory, mission execution in the form of a UAV swarm will be an important realization of future applications. Traditional single-UAV mission reliability modeling methods have been unable to meet the requirements of UAV swarm mission reliability modeling. Therefore, the UAV swarm mission reliability modeling and evaluation method is proposed. First, aimed at the interdependence among the multiple layers, a multi-layer network model of a UAV swarm is established. At the same time, based on the system having the following characteristics—using a mission chain to complete the mission and applying the connectivity of the mission network—the mission network model of a UAV swarm is established. Second, vulnerability and connectivity are selected as two indicators to reflect the reliability of the mission, and aimed at random attack and deliberate attack, vulnerability and connectivity evaluation methods are proposed. Finally, the validity and accuracy of the constructed model are verified through simulations, and the model and selected indicators can meet the reliability requirements of the UAV swarm mission. In this way, this study provides quantitative reference for UAV-swarm-related decision-making work and supports the development of UAV-swarm-related work.     

基于多目标优化的运输机任务设备配置研究

为得到合理的任务设备配置比例,对运输机任务设备配置进行优化。军用运输机可执行多种任务类型,需要配置不同的任务设备以实现货舱构型的转换。任务设备的配置比例应兼顾任务成功率、经济性和利用率等多目标要求。为此,以小规模运输机队为研究对象,给出了任务设备配置目标优化原则和边界条件,建立了配置模型,运用线性加权和法进行求解,并进行了模型灵敏度分析和偏差分析,得出了各任务设备的最佳配置比例,可解决小规模运输机队的任务设备配置问题。实例证明了配置结果的有效性。     

Possible Future Use of Laser Gravity Gradiometers

With the GRACE mission under way and the GOCE mission well along in the design process, detailed questions concerning the type of future mission that may follow them have arisen. It is generally agreed that determining the time variations in the Earth's gravity field with as high spatial and temporal resolution as is feasible will be the main driver for such a mission. The possible use of laser heterodyne measurements between separate satellites in such a mission has been discussed by a number of people. The first suggestion of emphasizing time variation measurements in a laser mission was the TIDES concept presented in 1992 by Colombo and Chao. Then, in 2000, a GRACE Follow-On mission using laser measurements between two drag-free satellites was discussed by Watkins el al. (2000). More recently, the possibility of utilizing laser measurements between more than two satellites in order to determine two or more components of the gravity gradient tensor simultaneously has been proposed by Balmino. This approach may be desirable in order to reduce the aliasing of time variations between geopotential terms of different degree and order, as well as to improve the resolution in longitude, despite the cost of the additional satellites. In this paper, we discuss specific possible mission geometries for measuring the two diagonal in-plane components of the gravity gradient tensor simultaneously. This could be done, for example, by laser heterodyne measurements between two pairs of satellites in coplanar and nearly polar orbits. This revised version was published online in August 2006 with corrections to the Cover Date.     

Distributed online mission planning for multi-player space pursuit and evasion

There are three important roles in evasion conflict: pursuer, target and defender. Pur-suers’ mission is to access targets;targets’ mission is to escape from pursuers’ capture;defenders’ mission is to intercept pursuers who are potentially dangerous to targets. In this paper, a distributed online mission plan (DOMP) algorithm for pursuers is proposed based on fuzzy evaluation and Nash equilibrium. First, an integrated effectiveness evaluation model is given. Then, the details of collaborative mission planning which includes the co-optimization of task distributing, trajectory and corresponding maneuvering scheme are presented. Finally, the convergence and steadiness of DOMP are discussed with simulation results. Compared with centralized mission planning, DOMP is more robust and can greatly improve the effectiveness of pursuing. It can be applied to dynamic scenario due to its distributed architecture.     

多无人机监控航路规划

为了提高监控任务的效率，在执行任务前必须规划设计出高效的无人机飞行航路。针对这一问题，考虑在任务区域内进行多无人机监控航路优化存在计算的复杂性和收敛性以及计算数据量限制等问题，采用分散式方法对监控航路进行了优化，并以无人机的监控任务为例提出了一种监控效率指标评估的计算方法，解决了航路规划中的监控效率量化问题。通过该方法得到的无人机监控任务的飞行航路可以有效地提高无人机的监控效率。     

基于遗传算法的无人机协同侦察航路规划

无人机将成为侦察卫星、有人驾驶侦察机的重要补充与增强手段 ,成为未来战场上广泛应用的一种侦察工具。为了提高无人机 (UAV)的侦察效率 ,在执行侦察任务前必需规划设计出高效的无人机侦察飞行航路。针对这一问题 ,本文提出了一种侦察效率指标评估的计算方法 ,解决了航路规划中的侦察效率量化问题。考虑在大范围任务区域内进行侦察航路优化存在计算的复杂性和收敛性等问题 ,本文采用遗传算法对侦察航路进行了优化处理。通过该方法得到的侦察航路可以有效地提高无人机的侦察效率。     

Impact of mission requirements and constraints on conceptual launch vehicle design

The objective of this paper is to analyse the impact of mission requirements and constraints on both the optimum vehicle design and the effects on flight path selection for two types of reusable two-stage-to-orbit launch vehicles. The first vehicle type considered provides horizontal take-off and landing capabilities and is intended to be propelled by an airbreathing propulsion system during stage 1 flight. The second vehicle type assumes a vertical launch and is accelerated by a rocket propulsion system during the booster stage ascent flight. The analysis employs a design tool for simultaneous system and mission optimization. It consists of a CAD-based preliminary vehicle design tool, aerodynamic and aerothermodynamic calculation software, flight simulation programs, and a two-level decomposition optimization algorithm enabling simultaneous system and flight optimization. The results to be presented show that the cruise flight requirement for an European launched mission of the airbreathing vehicle results in a loss of 60 % payload mass as compared to a mere accelerated ascent for a near equatorial mission into the same target orbit assuming constant take-off mass. The strong dependencies of mission requirements on both the optimal vehicle design and the ascent performance are determined for the rocket-powered vehicle type by varying the inclination and altitude of the target orbit.     

Comet nucleus sample return: Plans and capabilities

ROSETTA — the Comet Nucleus Sample Return mission — is one of the four Cornerstone missions to which ESA has committed itself in its approved Long-Term Programme Horizon 2000. The mission is currently being studied in collaboration with NASA. The comet-nucleus samples that ROSETTA is to provide will allow us to study some of the most primitive material in the solar system and the physical and chemical processes that marked the beginning of the system 4.6 billion years ago. For ESA, ROSETTA is a new type of mission: one which will return a sample at cryogenic temperature, and where as much effort has to be spent on preparing the laboratory analysis on-ground as has to be invested in preparing the space segment with the sample acquisition and in situ documentation. As part of the preparation for this mission, ESA is now starting to consider Planetary Protection issues.     

Risk-based technology portfolio optimization for early space mission design

The successful design, development, and operation of space missions requires informed decisions to be made across a vast array of investment, scientific, technological, and operational issues. In the work reported in this paper, we address the problem of determining optimal technology investment portfolios that minimize mission risk and maximize the expected science return of the mission. We model several relationships that explicitly link investment in technologies to mission risk and expected science return. To represent and compute these causal and computational dependencies, we introduce a generalization of influence diagrams that we call inference nets. To illustrate the approach, we present results from its application to a technology portfolio investment trade study done for a specific scenario for the projected 2009 Mars MSL mission. This case study examines the impact of investments in precision landing and long-range roving technologies on the mission capability, and the associated risk, of visiting a set of preselected science sites. We show how an optimal investment strategy can be found that minimizes the mission risk given a fixed total technology investment budget, or alternatively how to determine the minimum budget required to achieve a given acceptable mission risk.     

任务可靠度的估算分析

飞机设计工作中一项十分重要的任务是产品可靠性设计，本文回顾了任务可靠性的基本概念，给出了能够确定飞机完成任务可能性的任务可靠度的估算方法。在此基础上，为说明任务可靠度估算的实际过程，本文最后对某型飞机电传控制系统任务可靠度进行了分析，并给出了分析结论。     

Mission decision-making method of multi-aircraft cooperatively attacking multi-target based on game theoretic framework

Coordinated mission decision-making is one of the core steps to effectively exploit the capabilities of cooperative attack of multiple aircrafts. However, the situational assessment is an essential base to realize the mission decision-making. Therefore, in this paper, we develop a mission decision-making method of multi-aircraft cooperatively attacking multi-target based on situational assessment. We have studied the situational assessment mathematical model based on the Dempster-Shafer (D-S) evidence theory and the mission decision-making mathematical model based on the game theory. The proposed mission decision-making method of antagonized airfight is validated by some simulation examples of a swarm of unmanned combat aerial vehicles (UCAVs) that carry out the mission of the suppressing of enemy air defenses (SEAD).     

Optimal planning for a multi-debris active removal mission with a partial debris capture strategy

In this paper, a new mission model, called a multi-debris active removal mission with partial debris capture strategy, is proposed. The model assumes that a platform only captures part of the scheduled debris at a time and then releases these debris pieces to a disposal orbit. This process is then repeated until all of the scheduled debris is removed. A genetic algorithm with a multiparameter concatenated coding method is designed to optimize the plan of a multi-debris active removal mission wit...     

CCSDS空间包在MOIMS领域中的应用

为了适应未来航天任务的发展,构建以服务为导向的、开放的、可重用的航天器任务操作系统,分析了CCSDS(Consultative Committee for Space Data Systems,空间数据系统咨询委员会)中MOIMS (Mission Operations and Information Management System,任务操作及信息管理系统)领域的任务操作服务框架的原理、层次结构及优点,对任务操作相关的通用服务、功能服务、COM(Common Object Model,通用对象模型)及MAL(Message Abstraction Layer,消息抽象层)对服务的抽象化描述方法进行了研究.MAL向任务操作相关的服务提供了通用的服务模型框架,所有服务均可用MAL消息格式进行规范化的描述,在此基础上建立了MAL消息格式与CCSDS空间包的映射关系,从而以CCSDS空间包为信息栽体实现了航天器与地面系统间的任务操作通信,可以作为以服务为导向的任务操作系统实际工程应用的参考.     

空中加油问题的最优化研究

通过对空中加油在作战使用中的问题进行分析,针对受油机往返各加１次油的情况,给出了空中加油的数学模型,并采用跗算法对问题进行了优化计算,实际计算表明,所建模型具有良好的适应性,能够适合不同的作战环境和不同作战要求,采用跗优化算法研究空中加油问题,优化效率高、具有全局性,并易于计算机实现,所得的加油方案是合理的。     

CLUSTER MISSION OPERATIONS

The Cluster ground segment design and mission operations concept have been defined according to the basic mission requirements, namely, to allow the transfer of the four spacecraft from the initial geostationary transfer orbit achieved at separation from the launcher into the final highly elliptical polar orbits, such that in the areas of scientific interest along their orbits, the four spacecraft will form a tetrahedral configuration with pre-defined separation distances, to be changed every six months during the mission. The Cluster mission operations will be carried out by ESA from its European Space Operations Centre; the task of merging the Principal Investigators' requests into coordinated, regular scientific mission planning inputs to ESOC will be undertaken by the Joint Science Operations Centre. The mission products will be distributed to the scientific community regularly in form of CD-ROMs. Principal Investigators will also have access to quick-look science, housekeeping telemetry and auxiliary data via an electronic network.     

Weibull分布下任务时间可靠度的置信限研究

为解决高可靠度要求的产品系统可靠度的评定问题，针对产品系统的工作时间服从威布尔分布，采用Fiducial方法，提出了只凭工作时间的‘小子样、零失效’可靠性试验样本，求取任务时间可靠度各置信限的方法及公式。给出算例，计算和分析了不同试验样本下系统任务时间可靠度的置信限。结果表明利用数个‘长寿’的‘小子样、零失效’工作时间试验样本，可以获得高置信度下系统任务时间可靠度的大下限；单凭非‘长寿’情况下的‘小子样、零失效’试验样本，只能得到任务时间可靠度的最高限，如能补充辅助可靠性信息，就能得到系统任务时间可靠度的可用置信估计。     

基于蚁群算法的无人机航路规划

为了提高无人机(UAV)作战任务的成功率，在敌方防御区域内执行攻击任务前必须规划设计出高效的无人机飞行航路，保证无人机能够以最小的被发现概率及可接受的航程到达目标点。针对这一问题，对新近发展的蚁群算法进行了讨论，提出了适用于航路规划的优化方法，并对无人机的攻击任务航路进行了仿真计算。仿真结果表明，该方法是一种有效的航路规划方法。     

Mission segment division of the whole aeroengine loading spectrum based on flight actions

This paper studies on a division method of the whole aeroengine loading spectrum flight mission segment and rotor speed mission segment, which is based on the actual flight actions and related to the flight operations of aeroengine and is suitable for the variable-speed aeroengines such as turbojet and turbofan. Through the research, the aeroengine loading spectrum operation-related mission segments can be divided, which can provide important data basis for the life research on the structures wh...