基于网络的GPS时钟信号发布系统

从空管的实际应用出发,本次研究尝试以TCP Server/Client的模式进行GPS时钟信号的网络发布,通过这种方式实现多套系统灵活的时钟信号引接。     

一种快速求解整周模糊度的方法

针对FARA方法搜索整周模糊度组合数比较大,LAMBDA方法需要浮点解精度比较高的缺点,提出一种求解GPS载波相位测量整周模糊度的分步法。用LAMBDA方法搜索出来的整周模糊度作为FARA方法的初始解,进而用FARA方法解算出它的最终解。实验结果表明,该方法能缩短搜索整周模糊度的时间,快速准确地确定整周模糊度。     

Atmosphere sounding by GPS radio occultation: First results from TanDEM-X and comparison with TerraSAR-X

On 21 June 2010 the TerraSAR-X satellite was joined by the TanDEM-X satellite. A Global Positioning System (GPS) radio occultation (RO) experiment using the twin satellites has been carried out to estimate the precision of GPS atmospheric soundings. For the Day Of Year (DOY) 330–336, 2011, we analyze phase and amplitude data recorded by GPS receivers separated by a few hundred meters in a low earth orbit and derive collocated atmospheric refractivity profiles. In the altitude range 10–20 km the standard deviation between TerraSAR-X and TanDEM-X refractivity does not exceed 0.15%. The standard deviation is rapidly increasing for lower and higher altitudes; close to the surface and at an altitude of 30 km the standard deviation reaches 0.8% and 0.5%, respectively. Systematic deviations between TerraSAR-X and TanDEM-X refractivity in the considered altitude range (0–30 km) are negligible. The results confirm the anticipated high precision of the GPS RO technique. However, the difference in the retrieved refractivity in the lower troposphere for different Open Loop (OL) signal tracking parameters, altered onboard TanDEM-X for DOY 49–55, 2012, calls for an in depth analysis. At the moment we can not exclude that a potential bias in the OL Doppler model introduces a bias in our retrieved refractivity at altitudes <8$<8$ km.     

Response of the EIA ionosphere to the 7-8 May 2005 geomagnetic storm

In this paper, response of low latitude ionosphere to a moderate geomagnetic storm of 7–8 May 2005 (SSC: 1920 UT on 7 May with Sym-H minimum, ∼−112 nT around 1600 UT on 8 May) has been investigated using the GPS measurements from a near EIA crest region, Rajkot (Geog. 22.29°N, 70.74°E, Geomag.14°), India. We found a decrease in total electron content (TEC) in 12 h after the onset of the storm, an increase during and after 6 h of Sym-H deep minimum with a decrease below its usual-day level on the second day during the recovery phase of the storm. On 8 May, an increase of TEC is observed after sunset and during post-midnight hours (maximum up to 170%) with the formation of ionospheric plasma bubbles followed by a nearly simultaneous onset of scintillations at L-band frequencies following the time of rapid decrease in Sym-H index (−30 nT/h around 1300 UT).     

一种射频仿真时统子系统的技术设计

针对射频仿真系统中的时间同步问题,设计基于FPGA、DSP和GPS的时间统一系统。从工程实施的角度出发,详细阐述时统的硬件设计,介绍IRIG-B码的解码原理和各采样频率信号输出的过程。试验证明：该时统克服了常规时统设备的不足,性能更稳定,可靠性更高,更易于调试。     

利用GPS/INS导引飞机精密进场的数值仿真研究

建立了飞机进场的数学模型和导航观测器模型;确定了导引飞机精密进场的最优控制;以Airbus-300为例,给出了稳定的着陆窗口;计算了在GPS的各种定位精度范围内,从着陆窗口内开始着陆的飞机所能达到的等级;研究了GPS采样周期对飞机着陆精度的影响;分析了大气紊流和常值侧风对飞机着陆精度的影响。从计算和数值仿真结果得出了一些初步结论。     

GPS速度法确定飞机空速系统位置误差

飞机空速系统位置误差的测定,飞行试验中有多种常规方法,但期精度只能满足常规型号空速系统的验证要求。针对这一问题提出了ＧＰＳ速度法,叙述了该方法的原理、实施过程和数据处理方法,讨论了方法的系统精度并给出了误差估算结果。通过对某型飞机的验证试飞,表明该方法简便易行,可满足气动补偿型空速系统的试飞验证要求。     

SINS/GPS制导炸弹俯仰平面制导控制一体化设计

根据SINS/GPS制导炸弹动力学特性,首先推导了俯仰通道的制导控制一体化状态模型.然后在充分考虑制导和控制回路的不确定性基础上,利用terminal滑模控制方法,设计了制导控制一体化状态反馈控制律,所设计的控制器一方面保证制导炸弹满足打击精度和末端落角约束要求,另一方面保证控制回路的稳定性与鲁棒自适应性.采用模糊控制克服了变结构控制项引起的系统抖振.最后,分别进行了极端气动条件与取投放域边界值情况下的某型SINS/GPS制导炸弹六自由度飞行控制弹道仿真,仿真结果验证了此方法的有效性.     

基于车载平台的飞行管理系统DR/GPS 导航试验验证

飞行管理系统是民用飞机的关键航空电子系统。飞行管理系统制造商有责任对飞行管理系统开展大量的试验以验证飞行管理系统功能和性能的符合性。考虑数字验证的局限性和飞行试验验证的巨大代价,本文利用车载平台开展飞行管理系统综合导航功能的验证,试验结果表明设计的飞行管理系统DR/GPS 导航方法能够满足95% 的飞行时间水平方向达到0.1 海里的导航精度要求,为实际的飞行测试提供了试验数据参考。