Algorithmic support of a small-sized navigation system on the basis of the magnetoinertial course transmitter

The algorithmic support of a small-sized navigation system on the basis of the magnetoinertial course transmitter is considered; the support makes it possible to significantly reduce accumulating errors that are due to incomplete data on wind parameters and decrease requirements for random errors of initial data sensors.     

Inertial navigation system synthesis approach and gravity-inducederror sensitivity

A design criterion for improving the performance of the speed-damped inertial navigation system is presented. The single-axis speed-damped system is approached by optimizing the response of the system to a step-function disturbing signal. Butterworth, integral of time-multiplied absolute-value of error (ITAE), and solution-time standard forms are assumed to be the figures of merit for optimizing the system performance. The steady-state RMS (root-mean-square) gravity-induced navigation errors that are excited in the speed-damped system are determined for two gravity uncertainty models. The proposed figures of merit are compared. These comparisons reveal the sensitivity of predicted navigation errors to uncertainties in the gravity statistics, and simplify the choice of a suitable figure of merit for use in the design and error analysis of inertial navigation systems     

《电子商务概论》课程体系改革探索

分析了＂电子商务概论＂的课程性质,指出了其在现阶段课程教学中存在的问题,结合自身实践教学经历,从课程理论内容到实践教学内容出发,设计了一套集＂课内＋课外＂,＂校内＋校外＂的课程教学体系,为电子商务概论的课程建设提供参考。     

Real-time navigation using the global positioning system

This paper presents the results of an investigation of the application of the Global Positioning System (GPS) to real-time integrated missile navigation. We present quantifiable measures of navigation accuracy as a function of GPS user segment parameters. These user segment parameters include antenna phase response accuracy, single versus dual frequency, and Kalman filter structure and size. We also formulate some new phase-locked loop (PLL) filter designs for application in GPS receivers, and demonstrate their superiority over more conventional filters     

基于航行系统体系结构的动态空域规划

基于新航行系统体系结构的动态空域规划方法可以充分挖掘和发挥空域的潜能,不仅能够完成国家战略层面的航路、航线、管制扇区结构设计,还可以作为评估现有独立管制扇区是否最大限度地满足空域用户不断增长需求的依据。本文在参考美国航行系统体系结构发展的基础上,提出基于该体系的空域规划建模过程,以及关键性指标的应用,对动态空域划分与协调规则进行初步分析,为科学规划空域提供技术支     

Multiposition alignment of strapdown inertial navigation system

The authors demonstrate that the stationary alignment of strapdown inertial navigation system (SDINS) can be improved by employing the multiposition/technique. Using an observability analysis, it is shown that an optimal two-position alignment not only satisfies complete observability conditions but also minimizes alignment errors. This is done by analytic rank testing of the stripped observability matrix and numerical calculation of the error covariance. It is also shown that an optimal three-position alignment accelerates the convergence of the alignment error compared with two-position alignment     

A strapdown inertial navigation system for the flat-Earth model

The development of a strapdown inertial navigation system (SINS) for aerodynamically controlled vehicles, which are limited to altitudes below 30 km (that is, a small distance compared with the Earth's radius of about 7000 km), or using the so-called flat-Earth model (FEM), is the principal objective of this work. In dealing with the FEM equations, the north, east, down (NED) frame on the surface of the Earth is taken as an inertial reference frame. Although, this frame is both accelerating and rotating, the accelerations associated with the Earth's rotation are negligible compared with the acceleration that can be produced by a maneuvering aircraft. Also, in this model, the gravity is taken as constant. In developing the SINS for the FEM, the aerodynamic force and moment have dominant roles, depending primarily on such variables as the angle of attack and sideslip, their derivatives, components of the angular velocity of the aircraft, and the control inputs. On the other hand, the SINS deals with such variables as the small-angle rotation vectors. Thus, it was necessary to link both set of variables as state variables of the strapdown FEM as is done in this work. The developed model is relevant for small (less than 200) angles of attack and sideslip.     

平台式惯性导航系统在线可靠性评估技术

平台式惯性导航系统是现代导航的重要设备,由于其所处环境和制造工艺各不相同,导致各个体之间的可靠性有着明显的差异。如果对收集到的性能误差数据进行统一处理,无法准确地反映个体之间的差异性,不利于掌握平台式惯性导航系统个体的可靠性规律。针对该问题,对平台式惯性导航系统的在线可靠性评估方法进行了重点研究。结合平台式惯性导航系统使用过程中的性能变化特点和失效机理,利用复合Poisson过程建立了其性能退化模型,并给出了性能参数评估方法。通过算例分析,说明建立的性能退化模型能够较好地描述平台式惯性导航系统的性能退化规律,有助于掌握平台式惯性导航系统的可靠性水平。     

中国第二代卫星导航系统民用航空应用需求研究

一、概述 根据波音公司的预测,在未来20年内,中国将经历其航空史上市场发展最为迅猛的时期,中国的国内航空客运量将以每年7．9％的速度增长,航空货运量将以每年7．1％的速度增长,机队数量将由2007年的1300架增长到2027年的4560架,中国将成为除美国外最大的航空市场。随着航空运输的增长,现有轮辐式的运输方式将面临越来越大的压力,旅客们不希望由于中转换乘增加旅行时间,运输量的增长将导致枢纽机场的繁忙程度和延误率进一步增加。     

常规布局小型飞行器设计参数优化研究

对以螺旋桨为动力的长航时小型飞行器，在概念设计阶段的设计参数进行了敏感性分析。主要包含三个方面：一是飞机飞行状态，包括巡航高度；巡航速度及巡航升力系数。二是飞机机翼几何参数，包括尖梢比、展弦比和翼型。三是发动机的布局形式。飞机概念设计是在明确了设计要求的前提下开展的。在满足设计约束的基础上，通过对升力面气动特性及相互干扰分析，机翼剖面的设计选择以及升阻力特性的分析，典型部件重量构成的统计分析，计算出不同构型状态下的飞机重量和重心，保持纵向静安定度在合理范围内，通过对飞机有无配平情况下的阻力特性比较，寻求特定高度满足长航时设计要求的设计点。     

Optimization of the ship's navigation and controlling system with results of sea trials

This paper considers the state-of-the-art information technologies applied to solve the automatic track-keeping problem of the ship on a preset system of straight tacks and on a preset route to the area of hydrographic survey. A navigation-and-controlling system aboard a hydrographic vessel GS-439 was used to provide the fulfillment of the task. The results of the sea trials of control problems are given. They have shown rather good accuracy of the ship track-keeping on a preset system of straight tacks and on a preset route as well as the efficiency of automatic ship passing to the first tack and passing over to the next tacks in surveying the seabed relief, using a multi-channel echo sounder     

基于航行力学思想的坐标系研究

针对理论分析及工程实践对传统研究武器系统在多种介质环境中运动的学科提出的要求,提出了建立"航行力学"的构想。首先提出了航行与航行器的概念;其次将航行器在水中、大气中、外太空等不同介质环境下的坐标系及空间位置与姿态进行了定义;最后,讨论了航行器各坐标系的相互关系及转换,为初步建立航行力学理论奠定了基础。     

改性酚醛基复合材料的摩擦系数研究

研制了一种准高速列车盘形制动装置用混杂纤维增强改性酚醛基复合材料,在1:1惯性力矩试验台上研究了在干摩擦条件下以不同制动初速度、不同闸片压力实施惯性制动时的摩擦特性,利用扫描电镜对试验后的材料摩擦表面形貌进行观察。试验结果表明:瞬时摩擦系数随瞬时速度的变化与制动初速度有关,高接触压力下的摩擦系数低于低接触压力下的摩擦系数;在于摩擦、一次停车惯性制动条件下,临界使用条件是接触压力为0.82MPa,制动初速度为27.3m/s。摩擦表面生成摩擦膜是摩擦系数变化的主要原因。     

On the generalization of true proportional navigation

A simple framework to define generalized true proportional navigation (GTPN) guidance laws is presented. It is shown that this framework subsumes many of the generalizations presented in the earlier literature. The capture regions of a number of GTPN guidance laws are obtained through a rigorous qualitative analysis. The method of analysis is simpler and lends itself directly to an easy geometrical interpretation. A considerable amount of misinterpretation in the previous results, arising out of certain basic misconceptions, are corrected here. It is shown that a logical application of the guidance philosophy, through a minor modification of GTPN to take into account the direction of rotation of the line-of-sight (LOS), contributes substantially to the expansion of the capture region in the relative velocity space. In particular, it is shown that the capture region also extends to the negative closing velocity region, thus making the modified GTPN almost comparable, so far as the domain of capturability of guidance laws is concerned, to the pure proportional navigation (PPN) guidance law. A number of new results on the exact bounds on the capture region are derived and illustrated through examples     

Steering the station back on course

Rising costs of the International Space Station prompted NASA to convene a panel of experts to assess the quality of ISS cost estimates and review program assumptions and requirements. The panel concluded that NASA was unable to accurately predict ISS costs or to support requests for increased funding for the ISS through 2006 and should maintain a U.S. core complete program with three-person crews with 6-month stays on the ISS. International response to the panel report was negative with space agencies from Japan, Russia, Canada, and Europe taking issue with the expected impact on ISS construction and use.     

Basic performance of BeiDou-2 navigation satellite system used in LEO satellites precise orbit determination

The visibility for low earth orbit（LEO） satellites provided by the BeiDou-2 system is analyzed and compared with the global positioning system（GPS）. In addition, the spaceborne receivers＇ observations are simulated by the BeiDou satellites broadcast ephemeris and LEO satellites orbits. The precise orbit determination（POD） results show that the along-track component accuracy is much better over the service area than the non-service area, while the accuracy of the other two directions keeps at the same level over different areas. However, the 3-dimensional（3D） accuracy over the two areas shows almost no difference. Only taking into consideration the observation noise and navigation satellite ephemeris errors, the 3D accuracy of the POD is about30 cm. As for the precise relative orbit determination（PROD）, the 3D accuracy is much better over the eastern hemisphere than that of the western hemisphere. The baseline length accuracy is 3.4 mm over the service area, and it is still better than 1 cm over the non-service area. This paper demonstrates that the BeiDou regional constellation could provide global service to LEO satellites for the POD and the PROD. Finally, the benefit of geostationary earth orbit（GEO） satellites is illustrated for POD.     

装备研制费用参数估算方法研究

参数法是进行装备研制费用估算的有效方法之一.介绍了参数费用估算的历史和基本原理,分析了装备研制费用的主要驱动因素,将其作为估算参数,并给出了装备研制费用参数估算的基本流程.最后,基于国际先进的参数估算软件True Planning,对国外新一代直升机进行了参数估算的实例研究,显示了参数估算的有效性.