惯导装置精度试验火箭橇弹道设计

以9km 火箭橇试验设施为基础， 就惯导装置精度试验所需的长时、大过载 弹道条件， 提出了一种火箭橇弹道的设计方法。建立了火箭橇主动段和刹车段运动方 程， 针对火箭发动机推力、气动力、摩擦力和刹车力等主要动力学因素， 结合工程经 验，提出了选取原则和方法。以某惯导装置精度试验为背景，设计了火箭橇试验弹道， 通过试验验证，设计结果与实测数据基本一致，满足总体要求，并对其中出现的主要误 差进行了分析和评估。该研究能够为惯导装置开展精度试验奠定良好的火箭橇弹道设计 基础。

Ballistic Design of the Rocket Sled on INS Accuracy Testing

This paper is based on the 9km rocket sled track, for INS accuracy test required the length of time and high overload, a design method was put forward for rocket sled ballistic. The motion equations of powered and braked phase of the rocket sled was established, the selecting principles and methods were come out for the main power factors such as motor power of the rocket thrust, aerodynamic force, friction force, braking force and so on, which were combined with the engineering experience. Based on a INS accuracy test, the test with the rocket sled ballistic was designed, for verified by test, design results were the same as the measured data, which meet the overall requirements. Besides, the main errors have been analyzed and estimated with the test results. This research settled a well test with the rocket sled ballistic design basis for the INS accuracy test.