Shipborne high-accuracy heading determination method using INS- and GPS-based heading determination system

The heading accuracy of an existing shipborne inertial navigation system (INS) is affected by the oscillatory heading error caused by the misalignment angles between the gyro case and gyro axes. The accuracy of the heading determination system (HDS), which consists of two quadruple GPS antenna arrays, an INS, a total station surveying apparatus (TSSA), and two vessels, is affected by jump errors because of the degradation of tracking performance of the TSSA servo system in high dynamic conditions. Given that only pitch and roll of the INS are utilized in the HDS, we propose a high-accuracy heading determination system that combines the heading rate of the INS and linear fit of the heading difference between INS and HDS, to compensate for jump errors of HDS and oscillatory heading error of the INS. With the designed equipment, both jump errors and the oscillatory heading error can be suppressed effectively. The standard deviations of the heading errors are reduced from ±6 to ±2 and from ±8 to ±5 arcsec in mooring and sea tests, respectively, and a high accuracy of shipborne heading determination can be achieved since the oscillatory heading error is reduced to the 1 arcsec level.     

四元数在GPS船姿测量中的应用

为了对船体姿态进行高精度检测,介绍了四元代数的基础知识和性质及其在GPS船姿测量中的应用,得到了一种更为便捷的解算方法,对保障舰艇武备性能的发挥具有一定实际作用.     

On-the-fly GPS-based attitude determination using single- and double-differenced carrier phase measurements

Carrier phase measurements are primary observations for GPS attitude determination. Although the satellite-related errors can be virtually eliminated by forming single differences, the baseline-related errors such as line biases are still present in the single-differenced carrier phase measurements. It is, therefore, difficult to resolve the single-differenced integer ambiguities due to the line biases. By forming double differences, the line biases of the single-differenced carrier phase measurements can be effectively removed. However, the main disadvantages of this method lie in the fact that the double-differenced measurements are mathematically correlated and consequently the attitude obtained from the double differences is noisy. This paper presents a new algorithm through which both single and double differences are used simultaneously to resolve these problems in real-time. The solution of the integer ambiguities can be obtained by searching for the most likely grid point in the attitude domain that is independent of the correlation with the double differences. Next, the line biases and corresponding single difference integer ambiguities can be resolved on the fly by using the noisy attitude solution obtained from the previous double difference procedure. In addition, the relationship between the physical signal path difference and the line bias is formed. A new method is also applied to derive the attitude angles through finding the optimal solution of the attitude matrix element. The proposed new procedure is validated using ground and flight tests. Results have demonstrated that the new algorithm is effective and can satisfy the requirement of real-time applications.     

GPS-based precise orbit determination of Low Earth Orbiters with limited resources

The combination of GPS measurements and high-fidelity dynamic models via a Kalman filter/smoother, known as the reduced dynamic technique, allows 3D positioning of Low Earth Orbiters to the sub-decimeter level. Such accuracies can only be achieved if the GPS data are nearly continuous, post-processed and a dual-frequency receiver is utilized. The focus of this study is to quantitatively analyze the degradations in position accuracy in the presence of various limitations or constraints, which can be brought on by mission hardware limitations, for example, on micro- or nanosatellites. The constraints explored in this study are as follows: the use of single-frequency data only; real-time processing; limited dynamic modeling due to computing capabilities; and non-continuous GPS receiver operation due to power limits. The experiments are conducted with 6-h data arcs for 7 separate days using data from the CHAllenging Mini-Satellite Payload. A 3D root mean square (rms) error of 15 cm is observed in the best-case solution, in which dual-frequency data are post-processed with all available data. Various levels of accuracy degradations are observed as constraints are placed on this best-case solution. The 3D rms error of the post-processed, single-frequency solution is 68 cm and 1.3 m for the real-time, dual-frequency solution. In very challenging environments, for example, with the receiver on for only 10 min of a 90-min orbit, the 3D rms increases to 350 m.     

GPS-based precise orbit determination of the very low Earth-orbiting gravity mission GOCE

 A prerequisite for the success of future gravity missions like the European Gravity field and steady-state Ocean Circulation Explorer (GOCE) is a precise orbit determination (POD). A detailed simulation study has been carried out to assess the achievable orbit accuracy based on satellite-to-satellite tracking (SST) by the US global positioning system (GPS) and in conjunction the implications for gravity field determination. An orbit accuracy at the few centimeter level seems possible, sufficient to support the GOCE gravity mission and in particular its gravity gradiometer. Received: 21 January 2000 / Accepted: 4 July 2000     

Simultaneous determination of gravitational acceleration and ground vibrations by free fall experiments

We investigated how well we can simultaneously determine the gravitational acceleration and ground vibrations with many free falls at short intervals by using synthetic data which contain quadratic functions, sinusoids and white noise in order to improve the accuracy of absolute gravimetry and to realize the measurements without a seismometer. As a result of simulations, lower white noise, longer dropping time and longer duration of a series of free falls improve the accuracy in determination of g. The sampling internvals and the dropping intervals, on the other hand, hardly affect the accuracy so long as they are shorter than Nyquist intervals. Both the gravitational acceleration and the waveform of the long period vibrations can be well determined with a series of free falls of about only 2 cm dropping distance without deterioration in the accuracy with this procedure.     

GPS卫星精密定轨中的地球引力加速度研究

影响GPS精密定轨的因素除卫星轨道初值外还取决于力模型的精度,而地球引力加速度是GPS卫星精密定轨力模型中最为重要的部分。为满足精密定轨需要,该文针对目前各IGS中心所采用的简化动力法,深入研究了GPS卫星精密定轨中的地球引力加速度,详细推导了相关公式并编写程序,先后选取7颗GPS卫星及1颗卫星进行计算验证,结果表明:该文所采用的算法得到的地球引力加速度的计算精度优于10E-11ms~(-2),并且当引力位模型阶数为8~12阶时,引力加速度无明显差异。     

The absolute determination of the gravitational acceleration at Sydney, Australia

An absolute measurement of the gravitational acceleration “g” has been made at the National Standards Laboratory, Chippendale, N.S.W., Australia. The determination was made by studying the free motion of a body projected vertically upwards in a vacuum and the time between its initial and final passages through two horizontal planes of known vertical separation was measured. The measured value ofg at a point 12 metres above the floor in room B. 37 of the National Standards Laboratory is 9.7967134 m/s² The corresponding value at floor level at the BMR gravity station is 9.796717 m/s² Paper presented at the meeting of the International Gravimetric Commission, Paris 7–11 September 1970.     

GPS多普勒伪距平滑定位与测速方法

针对卫星导航系统受移动载体所处特殊工作环境及状态的影响,导致载波相位观测值发生周跳并引起载波相位平滑伪距产生较大误差的问题,该文提出一种基于高精度且不受周跳影响的多普勒频移观测值对精度相对较低的伪距观测值进行平滑的方法;采用GPS多普勒频移进行伪距平滑,并计算移动载体的位置信息;通过结合求解的位置信息与多普勒频移进一步完成移动载体速度的求取。静、动态实验结果表明:该文提出的多普勒频移平滑伪距算法能够进一步提高载体的定位和测速精度。     

利用GPS速度场求解构造块体的运动参数

文章推导了利用GPS观测速度计算构造块体转动参数和变形参数的统一模型,并基于此模型,利用GPS速度场资料,计算了中国大陆六个一级块体的转动参数和变形参数。     

Swarm卫星精密定轨与加速度法恢复地球重力场

CHAMP卫星和GOCE卫星分别于2010年和2013年坠落,GRACE卫星仍然超预期运行,随时会坠落,而后续重力卫星计划GRACE Follow-On预计2018年发射,在此期间,Swarm作为唯一的低轨重力观测卫星,将填补重力卫星观测的空白。本文对Swarm卫星精密定轨与加速度法恢复地球重力场进行了研究,实现了Swarm卫星运动学厘米级精密定轨和简化动力学厘米级精密定轨,并基于加速度法恢复了Swarm地球重力场模型。     

GPS单点测速的误差分析及精度评价 (英文)

Error sources which decrease the accuracy of GPS in absolute velocity determination have been changed since SA was turned off. Firstly, quantities of all kinds of error sources that influence velocity determination are analyzed. The potential accuracy of GPS absolute velocity determination is derived from both theory and field GPS data simulation. After that, two tests were carried out to evaluate the performance of GPS absolute velocity determination in the case of a static and an airborne GPS receiver and INS （Inertial Navigation System） instrument in kinematic mode. In static mode, the receiver velocity has been estimated to be several mm/s with the carrier-phase derived Doppler measurements, and several cm/s with the receiver generated Doppler measurements. In kinematic mode, GPS absolute velocity estimates are compared with the synchronized measurements from the high accuracy INS. The root mean square statistics of the velocity discrepancies between GPS and INS come up to dm/s. Moreover, it has a strong correlation with the acceleration or jerk of the aircraft.     

Influence of clock jump on the velocity and acceleration estimation with a single GPS receiver based on carrier-phase-derived Doppler

Since the Selective Availability was turned off, the velocity and acceleration can be determined accurately with a single GPS receiver using raw Doppler measurements. The carrier-phase-derived Doppler measurements are normally used to determine velocity and acceleration when there is no direct output of the raw Doppler observations in GPS receivers. Due to GPS receiver clock drifts, however, a GPS receiver clock jump occurs when the GPS receiver clock resets itself (typically with 1 ms increment/decrement) to synchronize with the GPS time. The clock jump affects the corresponding relationship between measurements and their time tags, which results in non-equidistant measurement sampling in time or incorrect time tags. This in turn affects velocity and acceleration determined for a GPS receiver by the conventional method which needs equidistant carrier phases to construct the derived Doppler measurements. To overcome this problem, an improved method that takes into account, GPS receiver clock jumps are devised to generate non-equidistant-derived Doppler observations based on non-equidistant carrier phases. Test results for static and kinematic receivers, which are obtained by using the conventional method without reconstructing the equidistant continuous carrier phases, show that receiver velocity and acceleration suffered significantly from clock jumps. An airborne kinematic experiment shows that the greatest impact on velocity and acceleration reaches up to 0.2 m/s, 0.1 m/s² for the horizontal component and 0.5 m/s, 0.25 m/s² for the vertical component. Therefore, it can be demonstrated that velocity and acceleration measurements by using a standalone GPS receiver can be immune to the influence of GPS receiver clock jumps with the proposed method.     

GPS单基线实时姿态测量系统分析与实现

分析和实现了基于单基线的GPS实时姿态测量系统。通过对姿态参数的精度分析,得出了姿态测量精度同基线长度和相对精度因子的关系;分析了姿态测量系统中单点定位对相对定位精度的影响;最后对姿态测量系统的实时性和姿态测量的结果进行了分析。本文的研究对GPS姿态测量技术的工程应用和理论研究具有一定的参考价值。     

经验加速度补偿对HY-2A卫星精密定轨的影响

针对HY-2A卫星定轨中存在系统误差的问题,该文提出了加入经验加速度补偿系统误差。为了获得HY-2A卫星的高精度轨道,采用星载DORIS距离变率数据探索了经验加速度对定轨精度的影响。探讨了1d、3d和7d作为经验加速度周期的定轨精度差异,分析了3d作为经验加速度周期时在径向、法向和切向3个方向设置经验加速度对定轨精度的不同影响。研究结果表明:HY-2A卫星在径向和切向不存在系统误差,而在法向存在系统误差,因而在法向设置经验加速度进行力学模型补偿能够取得较好的定轨结果;3d作为经验加速度的补偿周期较为合适,不仅能够减少解算参数个数,缩短计算时间,而且径向定轨精度可达到1.00cm,满足HY-2A卫星精密定轨需求。     

顾及卫星非圆轨道改正的GNSS精密测速方法

详细推导了卫星非圆轨道改正的计算公式,给出高精度测速顾及该项误差的处理策略．采用全球均匀分布的12个国际GNSS服务（IGS）测站的多普勒和载波相位观测数据,仿动态评估了该项误差对测速精度的影响．结果表明:基于历元间载波相位差分的测速方法,改正后东、北、天顶方向分别提高8％、9％和10％,三维测速精度从9.9 mm／s改正到8.9 mm／s;基于原始多普勒的测速方法,东、北方向与载波相位差分方法的改正数值基本一致,天顶方向约是载波相位差分方法的改正数值的一半．      

Local effects of redundant terrestrial and GPS-based tie vectors in ITRF-like combinations

Tie vectors (TVs) between co-located space geodetic instruments are essential for combining terrestrial reference frames (TRFs) realised using different techniques. They provide relative positioning between instrumental reference points (RPs) which are part of a global geodetic network such as the international terrestrial reference frame (ITRF). This paper gathers the set of very long baseline interferometry (VLBI)–global positioning system (GPS) local ties performed at the observatory of Medicina (Northern Italy) during the years 2001–2006 and discusses some important aspects related to the usage of co-location ties in the combinations of TRFs. Two measurement approaches of local survey are considered here: a GPS-based approach and a classical approach based on terrestrial observations (i.e. angles, distances and height differences). The behaviour of terrestrial local ties, which routinely join combinations of space geodetic solutions, is compared to that of GPS-based local ties. In particular, we have performed and analysed different combinations of satellite laser ranging (SLR), VLBI and GPS long term solutions in order to (i) evaluate the local effects of the insertion of the series of TVs computed at Medicina, (ii) investigate the consistency of GPS-based TVs with respect to space geodetic solutions, (iii) discuss the effects of an imprecise alignment of TVs from a local to a global reference frame. Results of ITRF-like combinations show that terrestrial TVs originate the smallest residuals in all the three components. In most cases, GPS-based TVs fit space geodetic solutions very well, especially in the horizontal components (N, E). On the contrary, the estimation of the VLBI RP Up component through GPS technique appears to be awkward, since the corresponding post fit residuals are considerably larger. Besides, combination tests including multi-temporal TVs display local effects of residual redistribution, when compared to those solutions where Medicina TVs are added one at a time. Finally, the combination of TRFs turns out to be sensitive to the orientation of the local tie into the global frame.     

An improved and extended GPS-derived 3D velocity field of the glacial isostatic adjustment (GIA) in Fennoscandia

We present a new GPS-derived 3D velocity field for the Fennoscandia glacial isostatic adjustment (GIA) area. This new solution is based upon ∼3,000 days of continuous GPS observations obtained from the permanent networks in Fennoscandia. The period encompasses a prolongated phase of stable observation conditions after the northern autumn of 1996. Several significant improvements have led to smaller uncertainties and lower systematic errors in the new solutions compared to our previous results. The GPS satellite elevation cut-off angle was lowered to 10°, we fixed ambiguities to integers where possible, and only a few hardware changes occurred over the entire network. The GAMIT/GLOBK software package was used for the GPS analysis and reference frame realization. Our new results confirmed earlier findings of maximum discrepancies between GIA models and observations in northern Finland. The reason may be related to overestimated ice-sheet thickness and glaciation period in the north. In general, the new solutions are more coherent in the velocity field, as some of the perturbations are now avoided. We compared GPS-derived GIA rates with sea-level rates from tide-gauge observations, repeated precise leveling, and with GIA model computations, which showed consistency.