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捷联惯导系统的位置误差和速度误差,通常取决于该系统内部误差参数的量值以及这些误差在飞行中的传播方式。捷联惯导系统内部误差参数中的每一项都可以表征为这样一个随机变量,其在整个惯导系统和飞行中已知变化和零均值呈概率分布。可以建立一个数学“误差模型”,它可以根据每项主要误差源的变化,预测给定飞行轨迹的惯导系统位置误差和速度误差的统计性能。这个“误差模型”还清楚地表明,捷联惯导系统的预期的误差取决于所选择的飞行轨迹。捷联系统设计师可利用这个模型得到符合技术性能要求的每项误差参数的变化范围。这种方法叫做“误差预算”。用这种方法作出的误差预算,可以预测出任一给定飞行轨迹的捷联惯导系统的统计性能。然而,对于象SNU84-1这类机动性能高的飞行器来说,在其动态的飞行范围之内,飞行轨迹有可能大大地激发惯导系统内部的某些误差源,以至设计不出成本效益好的切实可行的惯导系统来满足这一系列飞行的特殊性能要求。因此,我们的偿试是,“尽可能好”地设计惯导系统。引进一套标准飞行轨迹,将使捷联惯导系统的设计师能够建立一个能满足特定飞行轨迹的特殊性能要求的误差预算,而不必对该系统的元件提出不合实际的要求。要获得成本效益好的设计,提出的元件技术要求必须能保证惯导系统在最坏的环境条件下正常工作。在给出捷联系统的误差预算过程中,误差源通常可互相平衡。本文介绍了一种方法,采用这一方法,可望在给定的性能水平情况下,使惯导系统的成本最小。注:在本文中,“成本”可包括惯导系统所需要的任何一种或所有的资源,如使用周期成本、获得成本、体积、质量、能源需要等等。成本也可以是以上这些资源的加权和。
SINS position error and speed error, usually depends on the amount of error parameters within the system and the error of these in-flight mode of transmission. Each of the SINS internal error parameters can be characterized as a random variable with a known probability of change and zero mean over the entire inertial navigation system and in flight. A mathematical “error model” can be established that predicts the statistical performance of the inertial navigation system position and velocity errors for a given flight path based on changes in each of the major sources of error. This “error model” also clearly shows that the expected error of SINS depends on the chosen flight path. The strapdown system designer can use this model to get a range of variations for each error parameter that meets the technical performance requirements. This method is called “error budget.” The error budget made in this way can predict the statistical performance of SINS for any given flight path. However, for a highly maneuverable aircraft like the SNU84-1, it is possible for a flight path to greatly excite certain sources of error within the inertial navigation system within its dynamic range of flight, so as not to provide cost-effective design Of practical inertial navigation system to meet the special performance requirements of this series of flights. Therefore, our attempt is to design the “inertial navigation system” as “as possible”. The introduction of a standard flight path will allow SINS designers to establish an error budget that meets the specific performance requirements of a particular flight path without having to impose unrealistic demands on the components of the system. To achieve a cost-effective design, the proposed element technical requirements must ensure that the inertial navigation system is working under the worst environmental conditions. Error sources are usually balanced with each other in giving the error budget of the strapdown system. This article describes a method by which it is expected to minimize the cost of an inertial navigation system for a given level of performance. Note: In this context, “cost” may include any or all of the resources needed by an inertial navigation system such as cycle costs, cost, volume, quality, energy needs, and so on. The cost can also be a weighted sum of these resources.