机载对地观测飞行轨迹设计与对比分析

宫晓琳; 张帅

doi:10.13700/j.bh.1001-5965.2016.0580

机载对地观测飞行轨迹设计与对比分析

doi: 10.13700/j.bh.1001-5965.2016.0580

宫晓琳^{1, 2, ,},
张帅^{1, 2}

1.
北京航空航天大学惯性技术国家级重点实验室, 北京 100083
2.
北京航空航天大学新型惯性仪表与导航系统技术国防重点学科实验室, 北京 100083

基金项目:

国家自然科学基金 61473020

国家自然科学基金 61004129

国家自然科学基金 61233005

国家自然科学基金 61121003

遥感青年科技人才创新资助计划（第一期）

详细信息

作者简介:
宫晓琳女,博士,讲师,硕士生导师。主要研究方向:惯性导航与组合导航、滤波技术与信息融合等。

张帅男，硕士研究生。主要研究方向：组合导航。

通讯作者:
宫晓琳，E-mail: gongxiaolin@buaa.edu.cn

中图分类号: V249.32
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出版历程
- 收稿日期: 2016-07-07
- 录用日期: 2016-10-14
- 网络出版日期: 2017-08-20

Design and comparative analysis of flight trajectory of airborne earth observation

GONG Xiaolin^{1, 2
, ,},
ZHANG Shuai^{1, 2}

1.
Science and Technology on Inertial Laboratory, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
2.
Key Laboratory of Fundamental Science for National Defense-Novel Inertial Instrument and Navigation System Technology, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

Funds:

National Natural Science Foundation of China 61473020

National Natural Science Foundation of China 61004129

National Natural Science Foundation of China 61233005

National Natural Science Foundation of China 61121003

Remote Sensing of Youth Science and Technology Talent Innovation Funding Plan(Phase I)

More Information

Corresponding author: 宫晓琳，E-mail: gongxiaolin@buaa.edu.cn

摘要

摘要:
针对机载对地观测载机长时间匀速直线飞行时分布式位置姿态测量系统（POS）姿态误差随时间积累的问题，基于载机有效机动能够提高分布式POS系统可观测度进而提高系统估计精度的思想，设计并对比多种机动方式下分布式POS系统的估计精度，并对机动后分布式POS系统进入测区前的滤波估计稳定时间、直线飞行成像时长和全球定位系统（GPS）基线长度进行了测试。仿真结果表明，设计的飞行轨迹能够提高成像段运动参数的测量精度，可为机载对地观测最优飞行轨迹的选择和设计提供理论指导。
- 惯性/卫星组合导航 /
- 飞行轨迹 /
- 机动 /
- 传递对准 /
- 位置姿态测量系统(POS)
Abstract:
Aimed at the problem of attitude errors of distributed position and orientation system (POS) accumulate over time when airborne earth observation aircraft moves along a straight line at a constant velocity, a variety of maneuver modes were designed. Not only the estimation accuracy of distributed POS was compared, but also the time of system reaching stability after maneuver and the time of straight flight in imaging segment and baseline length of global position system (GPS) were tested. The method was based on the concept that the effective maneuver can improve the observability of distributed POS. Simulation results show that the designed flight trajectory can improve the measurement accuracy of the imaging segment motion parameters and can provide theoretical guidance for the selection and design of optimal flight trajectory for airborne earth observation.
- SINS/GPS integrated navigation /
- flight trajectory /
- maneuver /
- transfer alignment /
- position and orientation system (POS)

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图 1 机载对地观测飞行轨迹基本方案

Figure 1. Basic scheme of airborne earth observation flight trajectory

下载: 全尺寸图片幻灯片

图 2 5种运动方式的飞行轨迹

Figure 2. Flight trajectory of five modes of motion

下载: 全尺寸图片幻灯片

图 3 无机动、S型、O型、8字型和曲线爬升机动情况下姿态误差

Figure 3. Attitude error of no maneuver、S type maneuver、O type maneuver、8 type maneuver and curve climb maneuver

下载: 全尺寸图片幻灯片

表 1 惯性器件性能参数

Table 1. Performance parameters of inertial sensors

器件水平	陀螺仪漂移/((°)·h^-1)	加速度计偏置/μg
高精度	0.01	10
中精度	0.05	50
低精度	0.1	100

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表 2 飞行轨迹影响因素与参数选取

Table 2. Influencing factors and parameter selection of flight trajectory

子IMU惯性器件水平	测区前机动方式	测区前飞行时长/s	直线段飞行时长/s	GPS基线长度/km
高精度	无机动	0	100	20
中精度	S型	100	200	40
低精度	O型	200	400	60
	8字型	300
	曲线爬升	400

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表 3 5种运动方式的轨迹参数

Table 3. Trajectory parameters of five modes of motion

运动方式	时间/s	运动状态
1	0~400	匀速直线
	400~600	顺时针转180°
	600~1 000	匀速直线
2	0~100	匀速直线
	100~800	S型机动
	800~1 200	匀速直线
	1 200~1 400	顺时针转180°
	1 400~1 800	匀速直线
3	0~100	匀速直线
	100~500	O型机动
	500~900	匀速直线
	900~1 100	顺时针转180°
	1 100~1 500	匀速直线
4	0~100	匀速直线
	100~1 000	8字型机动
	1 000~1 400	匀速直线
	1 400~1 600	顺时针转180°
	1 600~2 000	匀速直线
5	0~500	曲线爬升
	500~900	匀速直线
	900~1 100	顺时针转180°
	1 100~1 500	匀速直线

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表 4 不同机动方式下成像段姿态误差统计(STD)

Table 4. Statistics of imaging segment attitude error under different maneuvering modes (STD)

机动方式	航向角估计误差/(°)	俯仰角估计误差/(°)	横滚角估计误差/(°)
无机动	0.248 3	0.037 6	0.040 4
S型	0.012 0	0.008 2	0.004 1
O型	0.020 9	0.008 2	0.004 1
8字型	0.011 6	0.008 4	0.004 0
曲线爬升	0.152 1	0.009 2	0.003 8

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表 5 不同T₁下成像段姿态误差统计(STD)

Table 5. Statistics of imaging segment attitude error with different T₁ (STD)

T₁/s	航向角估计误差/(°)	俯仰角估计误差/(°)	横滚角估计误差/(°)
0	0.011 6	0.008 4	0.004 0
100	0.011 6	0.008 3	0.004 0
200	0.009 1	0.008 5	0.003 8
300	0.009 3	0.008 2	0.003 8
400	0.009 9	0.008 1	0.003 8
500	0.010 2	0.008 2	0. 0038

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表 6 不同T₂下成像段姿态误差统计(STD)

Table 6. Statistics of imaging segment attitude error with different T₂ (STD)

T₂/s	航向角估计误差/(°)	俯仰角估计误差/(°)	横滚角估计误差/(°)
100	0.008 3	0.007 6	0.003 8
200	0.008 6	0.007 7	0.003 9
400	0.009 1	0.008 5	0.003 8

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表 7 不同GPS基线长度下GPS定位精度

Table 7. GPS positioning accuracy under different baseline lengths of GPS

GPS基线长度/km	水平定位精度/m	高度定位精度/m
20	0.1	0.2
40	0.5	1
60	1	2

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表 8 不同GPS基线长度下成像段子系统运动参数误差统计(STD)

Table 8. Statistics of motion parameter error of imaging segment subsystem under different baseline lengths of GPS (STD)

运动参数	GPS基线长度/km
运动参数	20	40	60
航向角/(°)	0.010 1	0.009 8	0.009 8
俯仰角/(°)	0.008 0	0.008 0	0.008 1
横滚角/(°)	0.003 7	0.003 8	0.003 8
东向速度/(m·s^-1)	0.013 7	0.016 2	0.018 1
北向速度/(m·s^-1)	0.016 2	0.017 1	0.018 9
天向速度/(m·s^-1)	0.019 4	0.019 4	0.020 1
纬度/m	0.205 7	0.244 5	0.246 5
经度/m	0.168 8	0.230 8	0.278 2
高度/m	0.494 2	0.484 9	0. 519 2
基线长度/m	0.218 0	0.597 2	1.275 7

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