Journal articles: 'Launch vehicle navigation testing'

1

Driscoll, Frederick R., Pierre-Philippe J. Beaujean, and William A. Venezia. "Development and Testing of an A-Sized Rapidly Deployable Navigation and Communication GATEWAY Buoy." Marine Technology Society Journal 40, no. 1 (March 1, 2006): 36–46. http://dx.doi.org/10.4031/002533206787353600.

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A rapidly deployable, intelligent GATEWAY buoy system, capable of both air and sea deployment, has been developed to aid in the navigation and communication of Autonomous Underwater Vehicles (AUVs). The device is based around the A-sized (sonobuoy) standard and is deployable from aircraft, helicopters, ships and submarines using pressure and gravity launch tubes or charge-activated devices. The system consists of Florida Atlantic University (FAU) and Woods Hole Oceanographic Institute (WHOI) acoustic modems, both capable of providing Long Base Line (LBL) positioning, Global Positioning System (GPS) Wide Area Augmentation System (WAAS), and Radio Frequency (RF) communications. It utilizes a combined parachute and anchor, a low drag inflatable buoy, and an intelligent scope-adjusting mooring line spool. The design is based around a “fire-and-forget” methodology which, when the system is turned on and launched, requires no initial knowledge of the operating environment. The interoperable acoustic communication (ACOMMS) system can be operated at ranges up to 3000 meters and can achieve a true data rate of up to 860 bits-per-second using reliable spread-spectrum frequency modulation. The LBL positioning system operates sequentially and does not preclude acoustic communications. Switching between protocols (FAU or WHOI) is achieved through an automated process or is requested via RF commands. The mechanical system is modular and compact. The system is capable of operating in depths between 5 m and 200 m, in conditions up to sea state 3, and in currents up to 1.5 m/s. The mooring is versatile and able to hold in bottom types ranging from mud and sand to broken rock and reef.

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Zosimovych, Nickolay, Niu Xiaodong, Alex Noel Joseph Raj, Alessandro Simeone, and Xiongbin Peng. "Integrated Guidance System of a Commercial Launch Vehicle." MATEC Web of Conferences 179 (2018): 03002. http://dx.doi.org/10.1051/matecconf/201817903002.

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This paper proposes a concept of integrated on-board navigation systems for commercial launch vehicles in the context of the current task, and provided mathematical models of its elements for different variants of designing structure and composition. Has been set and simulated the technical problem of the conceptual design of an integrated navigation system for the space launch vehicle qualified to insert small artificial Earth satellites into low and medium circular orbits with application of GPS technologies.

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Hassani, Mehdi, Jafar Roshanian, and A. Majid Khoshnood. "A reliable analytical navigation system based on symmetrical dynamic behavior of control channels." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 1 (October 2, 2016): 190–99. http://dx.doi.org/10.1177/0954410016664917.

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This study develops an advanced fault recovery strategy to improve the reliability of an aerospace launch vehicle navigation system. The proposed strategy contains fault detection features and can reconfigure the system against common faults in the aerospace launch vehicle navigation system. For this purpose, fault recovery system is constructed to detect and reconfigure normal navigation faults operating as a soft sensor, based on the symmetrical dynamic behavior of the yaw and pitch channels of the vehicle. In the face of pitch channel sensor failure, the Auto Regression Exogenous model of the yaw channel of the vehicle is identified using the recursive instrumental variable methodology. Based on the symmetrical behavior of the aerospace launch vehicle in the yaw and pitch channels, the Auto Regression Exogenous model of the yaw channel is substituted by the dynamic model of the pitch one and consequently, the pitch-rate gyroscope output is constructed to provide fault-tolerant navigation solution. The novel aspect of paper is employing symmetrical dynamic behavior of the yaw and pitch channels as an online tuning of analytical fault recovery solution against unforeseen variations due to its hardware/software property. In this regard, a nonlinear model of the aerospace launch vehicle is simulated using specific navigation failures and the results verified the feasibility of the proposed system. Simulation results and sensitivity analysis show that the proposed techniques can produce more effective estimation results than those of the previous techniques, against sensor failures.

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Lipnitskiy, Yuriy Mikhaylovich, and Aleksandr Victorovich Safronov. "GROUND TESTING OF THE LAUNCH VEHICLE ACOUSTICS." TsAGI Science Journal 45, no. 3-4 (2014): 237–54. http://dx.doi.org/10.1615/tsagiscij.2014011945.

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5

Xu, Bo, Dan Dan Wang, and Zhen Sheng Cheng. "Error Modeling and Simulation Analysis for the Vehicle Launching System Erecting." Advanced Materials Research 566 (September 2012): 680–84. http://dx.doi.org/10.4028/www.scientific.net/amr.566.680.

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Horizontal collimation is the development tendency of the vehicle launching system. During the erect process, the launching system's navigation precision depends on the strap-down inertial navigation system calculation on the launch carrier. So the analysis of every inertial component's error which produces in the inertial navigation process is very necessary. This paper sets the model of the whole erect process, including the launch of the erect drive, the scaling factor,and zero position and installation error of the inertial components. It analyzes the various factors influence on the navigation precision in detail. It provides a good simulation basis and design basis for the error distribution and precision analysis of horizontal collimation technology. And it also provides analysis results for its application and extension, plan making, precision evaluation.

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Zosimovych, Nickolay. "Selecting Design Objectives for an Integrated Guidance System of a Commercial Launch Vehicle with Application of GPS Technologies." Open Aerospace Engineering Journal 6, no. 1 (October 11, 2013): 6–19. http://dx.doi.org/10.2174/1874146001306010006.

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In this article have been proposed the design objectives for an integrated guidance system of a commercial launch vehicle with application of GPS technologies and has been set a technical problem of the conceptual design of an integrated navigation system for the space launch vehicle qualified to inject small artificial Earth satellites into low and medium circular orbits. The conceptual design of the integrated navigation system based on GPS technology involves determination of its structure, models and algorithms, providing the required accuracy and reliability in injecting payloads with due regard to restrictions on weight and dimensions of the system.

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Piatak, David J., Martin K. Sekula, and Russ D. Rausch. "Ares Launch Vehicle Transonic Buffet Testing and Analysis Techniques." Journal of Spacecraft and Rockets 49, no. 5 (September 2012): 798–807. http://dx.doi.org/10.2514/1.a32175.

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Manwatkar, Sushant, S. V. S. Narayana Murty, and P. Ramesh Narayanan. "Failure Analysis of AISI 302 Steel Compression Spring Used in Flush and Purge Valve of Liquid Engine." Materials Science Forum 830-831 (September 2015): 705–8. http://dx.doi.org/10.4028/www.scientific.net/msf.830-831.705.

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AISI 302 stainless steel is used for making compression springs for launch vehicle programmes. One such AISI 302 stainless steel compression spring used in flush and purge valve of liquid engine of a satellite launch vehicle failed during testing. The failure was at the second round of spring and it failed in a slanted type fracture. Detailed metallurgical analysis indicated that the failure was due to fatigue.

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Song, Haryong, and Yongtae Choi. "Distributed multiple model extended information filter with unbiased mixing for satellite launch vehicle tracking." International Journal of Distributed Sensor Networks 14, no. 4 (April 2018): 155014771876926. http://dx.doi.org/10.1177/1550147718769263.

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A distributed extended information filter-based interacting multiple model estimator with unbiased mixing is proposed for satellite launch vehicle tracking. In this problem, multiple heterogeneous sensors such as radars, telemetry systems receiving onboard Global Positioning System—inertial navigation system data, and electro-optical targeting systems are used. The extended information filter is used for nonlinear estimation dealing with ballistic model and spherical coordinate observation. The multiple Markov switching models comprise thrusting and coasting modes having different state vector dimensions for the launch vehicle. To effectively combine both state vectors, an unbiased mixing technique is applied and then the distributed extended information filter integrates local states and information matrix contributions. Hence, the proposed algorithm takes into account both heterogeneity of tracking sensors and multiplicity of vehicle’s dynamic model. We prove the superiority of the proposed algorithm by conducting Monte Carlo simulation with nominal trajectory data of Korea Space Launch Vehicle-1. Comparative simulation results demonstrate that the performance of the proposed method has been improved in vehicle’s position root mean square error.

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10

Chen, Kai, Fuqiang Shen, Jun Zhou, and Xiaofeng Wu. "SINS/BDS Integrated Navigation for Hypersonic Boost-Glide Vehicles in the Launch-Centered Inertial Frame." Mathematical Problems in Engineering 2020 (November 12, 2020): 1–16. http://dx.doi.org/10.1155/2020/7503272.

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According to the trajectory specialty of hypersonic boost-glide vehicles, a strapdown inertial navigation system/BeiDou navigation satellite system (SINS/BDS) algorithm based on the launch-centered inertial (LCI) frame for hypersonic vehicles is proposed. First, the related frame system, especially the launch earth-centered inertial (LECI) frame, and the SINS mechanization in the LCI frame are introduced. Second, SINS discrete updating algorithms in the LCI frame for the compensation of coning, sculling, and scrolling effects are deduced in the attitude, velocity, and position updating algorithms, respectively. Subsequently, the Kalman filter of the SINS/BDS integrated navigation in the LCI frame is obtained. The method of converting BDS receiver position and velocity from the Earth-centered Earth-fixed (ECEF) frame to the LCI frame is deduced through the LECI frame. Finally, taking the typical hypersonic boost-glide vehicles as the object, the SINS/BDS algorithm vehicle field test and hardware-in-the-loop simulation are performed.

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11

Hasani, Mahdi, Jafar Roshanian, and A. Majid Khoshnooda. "Analytical fault tolerant navigation system for an aerospace launch vehicle using sliding mode observer." Advances in aircraft and spacecraft science 4, no. 1 (January 25, 2017): 53–64. http://dx.doi.org/10.12989/aas.2017.4.1.053.

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Umadevi, P., A. Navas, Kesavabrahmaji Karuturi, A. Abdul Shukkoor, J. Krishna Kumar, Sreejith Sreekumar, and A. Mohammed Basim. "Inertial Navigation System for India’s Reusable Launch Vehicle-Technology Demonstrator (RLV-TD HEX) Mission." Journal of The Institution of Engineers (India): Series C 98, no. 6 (October 24, 2017): 689–96. http://dx.doi.org/10.1007/s40032-017-0404-8.

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13

Welch, John W., Bailey Z. Zhao, and Derek J. McVay. "Effectiveness and Value of Space Vehicle Thermal Vacuum Testing." Journal of the IEST 63, no. 1 (December 1, 2020): 63–74. http://dx.doi.org/10.17764/1557-2196-63.1.63.

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Abstract Environmental testing of spacecraft flight hardware is performed to detect design and workmanship defects and verify mission requirements prior to launch. At the space vehicle level of assembly, the thermal vacuum test simulates an environment particularly well-suited for verifying mission performance requirements. In this paper, the test objectives of the space vehicle thermal vacuum test are reviewed and an assessment is made of the effectiveness and value of the test. Recent thermal vacuum test data is used to determine how the uniqueness of the thermal vacuum test environment achieves test purposes and how the test ensures mission assurance for space vehicles.

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14

Tall, M. H., P. F. Rynne, J. M. Lorio, and K. D. von Ellenrieder. "Visual-Based Navigation of an Autonomous Surface Vehicle." Marine Technology Society Journal 44, no. 2 (March 1, 2010): 37–45. http://dx.doi.org/10.4031/mtsj.44.2.6.

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AbstractThis paper presents the work of a team of undergraduate and graduate students at Florida Atlantic University (FAU) who compete in the annual Autonomous Surface Vehicle (ASV) competition held jointly by the Association for Unmanned Vehicle Systems International (AUVSI) and the U.S. Office of Naval Research (ONR). The conceptual design of the vehicle, its physical realization, and the results of both preliminary testing and the final competition are presented. The initial configuration of a stereoscopic vision system and navigation algorithm is explored through testing in a controlled environment. With this approach, the vehicle is shown to be capable of navigating through various courses of colored buoys; approximately 25% of the attempts result in successful navigation of all buoy pairs while 75% of the attempts result in successful navigation of half the buoy pairs or more.

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Chen, Hongmei, Hongbo Gao, and Huijuan Zhang. "Integrated navigation approaches of vehicle aided by the strapdown celestial angles." International Journal of Advanced Robotic Systems 17, no. 3 (May 1, 2020): 172988142093200. http://dx.doi.org/10.1177/1729881420932008.

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The integrated navigation method based on star sensor celestial angles (altitude angle and azimuth angle) is proposed to serve the need for rapidly responsive, reliable, and precise of a hypersonic vehicle under a sophisticated environment. An integrated navigation algorithm suitable for large azimuth misalignment is established under launching point inertial coordinate and local geographical coordinate system based on altitude angle and azimuth angles. Meanwhile, a Bayesian method for data dropouts aided by the strapdown celestial angles is presented for the rapid variability in the celestial star angle with active galaxies. A nonlinear Bayesian filter is applied to implement the simulation on account of the nonlinear feature of the state and measurement equations. The simulation results showed that the Bayesian method for integrated navigation data dropouts could be accomplished by altitude angle and azimuth angle aiding in both launching point inertial coordinate and local geographical coordinate systems, which converge to 1′ in 10 s. The method indicated that the integrated navigation significant errors derived from initial localization and initial attitude alignment could be modified by the strapdown inertial navigation system (SINS) supported by the star sensor’s celestial angle in the local geographic coordinate system in the early launch stage. For the seconds of the flight phase, the integrated navigation aided by celestial angles in the launching point inertial coordinate system was guaranteed for the feasibility and validity. During the flight, the feasibility and validity of integrated navigation were guaranteed aided by celestial angles in launching point inertial coordinate system.

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Kaparias, I., and M. G. H. Bell. "Testing a reliable in-vehicle navigation algorithm in the field." IET Intelligent Transport Systems 3, no. 3 (2009): 314. http://dx.doi.org/10.1049/iet-its.2008.0075.

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17

Daly, P. "Aspects of the Soviet Union' s Glonass Satellite Navigation System." Journal of Navigation 41, no. 02 (May 1988): 186–98. http://dx.doi.org/10.1017/s0373463300009279.

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Global satellite navigation systems have been under development by the United States and the Soviet Union for many years. The US Navstar GPS system saw its first launch in 1978 and the USSR's Glonass system followed 4 years later. The US space shuttle, which was foreseen as the launch vehicle for Navstar spacecraft, received an enormous setback in 1986 as a result of the Challenger accident. In the meantime, Glonass launches, which carry three spacecraft at once into orbit, have proceeded without incident (until the failure on 24 April 1987). Both systems are currently still in test phase and can be expected to reach operational status in 3 or 4 years' time. In the meantime, the idea of combining Navstar and Glonass into a single civil programme has many attractions for all concerned. Some aspects of Glonass orbital characteristics and signal structure are discussed with this end in view. In addition, features of the data message content of Navstar and Glonass are also compared, to gain a better understanding of the feasibility of a dual satellite navigation system.

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Kim, Sung-Wan, and Dong-Chul Park. "Compact S-Band Antenna Hat for RF Compatibility Testing of Launch Vehicle." Journal of Korean Institute of Electromagnetic Engineering and Science 26, no. 2 (February 27, 2015): 148–57. http://dx.doi.org/10.5515/kjkiees.2015.26.2.148.

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Abrahamm, P. K., and B. Valsa. "Quality Assurance Challenges in Testing and Evaluation of Reusable Launch Vehicle Systems." Current Science 114, no. 01 (January 10, 2018): 144. http://dx.doi.org/10.18520/cs/v114/i01/144-147.

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Varaprasad, R., and V. Seshagiri Rao. "Range Safety Real-time System for Satellite Launch Vehicle Missions–Testing Methodologies." Defence Science Journal 56, no. 5 (November 1, 2006): 693–700. http://dx.doi.org/10.14429/dsj.56.1933.

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21

Li, Yong Kui, Li Jun Chen, and Xue Wei Bai. "Design of Automated Guided Vehicle for Field Application." Advanced Materials Research 461 (February 2012): 88–92. http://dx.doi.org/10.4028/www.scientific.net/amr.461.88.

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A type of GPS-navigation wheel testing vehicle was designed for operating in field environment. The commonly used material and standardized parts were selected to construct mechanical system; and the general electronic component as well as personal computer was used to construct the control system. The experiment conducted with the testing vehicle shows that the vehicle has sufficient capacity for ordinary loading, meanwhile it runs smoothly and of good maneuverability. It provides a practical platform for studying GPS-navigation technique applied on agricultural machines in field working condition

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Zhao, Hui, Zhi Xiong, Lijuan Shi, Feng Yu, and Jianye Liu. "A robust filtering algorithm for integrated navigation system of aerospace vehicle in launch inertial coordinate." Aerospace Science and Technology 58 (November 2016): 629–40. http://dx.doi.org/10.1016/j.ast.2016.09.023.

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Hasani, S. M. Mehdi, A. Majid Khoshnood, and Jafar Roshanian. "Fault Detection in Navigation System of ALV Based on Symmetrical Behavior of Control Channels." Applied Mechanics and Materials 798 (October 2015): 266–70. http://dx.doi.org/10.4028/www.scientific.net/amm.798.266.

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The present study develops an advanced Fault detection (FD) strategy to improve the reliability of an Aerospace Launch Vehicle (ALV) navigation system. For this purpose, FD system is constructed to detect normal navigation faults operating as a soft sensor, based on the symmetrical dynamic behavior of the yaw and pitch channels of the vehicle. In the face of pitch channel sensor failure, the dynamic model of the yaw channel of the vehicle is identified using the recursive least squares (RLS) method. Based on the symmetrical behavior of the ALV in the yaw and pitch channels, the dynamic model of the yaw channel is substitute by the dynamic model of the pitch one and consequently, the pitch gyroscope output is constructed to provide fault detection navigation solution. The novel aspect of this fault detection system is employing symmetrical dynamic behavior of the yaw and pitch channels as an online tuning of analytical fault detection system against unforeseen variations due to its hardware/software property. Simulation Results and sensitivity analysis show that the proposed techniques can produce better estimation results than those of the previous techniques against sensor failures.

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Samuel, A., N. Jayalal, B. Valsa, C. A. Ignatious, and J. Zachariah. "Software Fault Injection Testing of the Embedded Software of a Satellite Launch Vehicle." IEEE Potentials 32, no. 5 (September 2013): 38–44. http://dx.doi.org/10.1109/mpot.2012.2236150.

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Jing, Wuxing, Xu Zheng, and Changsheng Gao. "Influence of Initial State Errors on Perturbation Guidance Accuracy." Defence Science Journal 69, no. 1 (January 10, 2019): 10–19. http://dx.doi.org/10.14429/dsj.69.11527.

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The inertial navigation system is aligned and leveled before the launch of a long-range vehicle. However, the initial state errors caused by the non-uniformity of the Earth can influence the parameters in flight dynamics, which will bring about serious uncertainty for the impact point of a long-range vehicle. Firstly, this paper analyses the influence mechanism of initial state errors on nominal trajectory, navigation trajectory and guidance trajectory. Then, a propagation model of engine-cutoff state deviation caused by initial state errors is derived under the condition of without-guidance. On this basis, an accuracy analytical solution of initial state errors on perturbation guidance is finally proposed to obtain the real impact-point of the long-range vehicle. In the simulations, the influence properties of initial state errors on perturbation guidance is analysed, give influence regularities of single initial state error, and obtain the statistical properties of engine-cutoff state deviations and impact-point deviation by Monte Carlo technique. From the simulation results, it seems that the navigation state tracks the nominal state. However, the real impact- point deviation has not been truly eliminated, instead of the almost target-hit deviation calculated by navigation output. The proposed analytical guidance accuracy model can be rapidly computed to provide a compensation for guidance and control system to improve hit accuracy.

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Pu, Huayan, Yuan Liu, Jun Luo, Shaorong Xie, Yan Peng, Yi Yang, Yang Yang, et al. "Development of an Unmanned Surface Vehicle for the Emergency Response Mission of the ‘Sanchi’ Oil Tanker Collision and Explosion Accident." Applied Sciences 10, no. 8 (April 14, 2020): 2704. http://dx.doi.org/10.3390/app10082704.

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Unmanned surface vehicles (USVs) as unmanned intelligent devices can replace humans to perform missions more efficiently and safely in dangerous areas. However, due to the complex navigation environment and special mission requirements, USVs face many challenges in emergency response missions for marine oil spill accidents. To solve these challenges in the emergency response mission of the ‘Sanchi’ oil tanker collision and explosion accident, we designed and deployed an USV to perform the missions of real-time scanning and water sampling in the shipwreck waters. Compared with the previous USVs, our USV owned the following characteristics: Firstly, the improved navigation control algorithms (path following and collision avoidance) can provide high navigation accuracy while ensuring navigation safety; Secondly, an improved launch and recovery system (LARS) enabled the USV to be quickly deployed and recovered in the mission area; Thirdly, a new sampling system was specially designed for the USV. Our USV completed the missions successfully, not only providing a lot of information for rescuers but also offering a scientific basis for follow-up work.

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Eramo, Vincenzo, Francesco Lavacca, Francesco Valente, Andrea Pisculli, and Stefano Caporossi. "Simulation and Experimental Evaluation of a Flexible Time Triggered Ethernet Architecture Applied in Satellite Nano/Micro Launchers." Aerospace 5, no. 3 (August 9, 2018): 84. http://dx.doi.org/10.3390/aerospace5030084.

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The success of small satellites has lead to the study of new technologies for the realization of Nano and Micro Launch Vehicle (NMLV) in order to make competitive launch costs. The paper has the objective to define and experimentally investigate the performance of a communication system for NMLV interconnecting the End Systems as On-Board Computer (OBC), telemetry apparatus, Navigation Unit...we propose a low cost Ethernet-based solution able to provide the devices with high interconnection bandwidth. To guarantee hard delays to the Guide, Navigation and Control applications we propose some architectural changes of the traditional Ethernet network with the introduction of a layer implemented in the End Systems and allow for the lack of any contention on the network links. We show how the proposed solution has comparable performance to the one of TTEthernet standard that is a very expensive solution. An experimental test-bed equipped with Ethernet switches and Hercules boards by Texas Instruments is also provided to prove the feasibility of the proposed solution.

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Löwenau, J. P., P. J. Th Venhovens, and J. H. Bernasch. "Advanced Vehicle Navigation applied in the BMW Real Time Light Simulation." Journal of Navigation 53, no. 1 (January 2000): 30–41. http://dx.doi.org/10.1017/s0373463399008681.

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Advanced vehicle navigation based on the US Global Positioning Systems (GPS) will play a major role in future vehicle control systems. Contemporary vehicle navigation systems generally consist of vehicle positioning using satellites and location and orientation of the vehicle with respect to the roadway geometry using a digitised map on a CD-ROM. The standard GPS (with Selective Availability) enables positioning with an accuracy of at least 100 m and is sufficiently accurate for most route guidance tasks. More accurate, precision navigation can be obtained by Differential GPS techniques. A new light concept called Adaptive Light Control (ALC) has been developed with the aim to improve night-time traffic safety. ALC improves the headlamp illumination by means of continuous adaptation of the headlamps according to the current driving situation and current environment. In order to ensure rapid prototyping and early testing, the step from offline to online (real-time) simulation of light distributions has been successfully completed in the driving simulator. The solutions are directly ported to real vehicles to allow further testing with natural road conditions.

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Mutlu, Lutfi, and Erol Uyar. "Indoor Navigation and Guidance of an Autonomous Robot Vehicle by Using Wireless (ZigBee) Cummunication." Advanced Materials Research 463-464 (February 2012): 1634–37. http://dx.doi.org/10.4028/www.scientific.net/amr.463-464.1634.

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In this work, a novel approach for navigation and guidance of a duo cycle autonomous robot vehicle by using ZigBee wireless control is presented. For navigation the angular position and location of the vehicle is measured intermittent by means of an electronic compass and a linear position encoder. Both measured values are then compared through a PC with the reference points of a certain trajectory, so that a given path can be followed by the vehicle autonomously. Besides navigation a self developed algorithm is integrated to the system control for possible obstacle avoidance and optimal path finding. The results of experimental testing showed the effectiveness of the proposed approach.

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Stephen, J., and G. Lachapelle. "Development and Testing of a GPS-Augmented Multi-Sensor Vehicle Navigation System." Journal of Navigation 54, no. 2 (May 2001): 297–319. http://dx.doi.org/10.1017/s0373463301001357.

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An integrated multi-sensor vehicle navigation system is presented that uses a low-cost rate gyro and differential odometry to supplement GPS under signal masking conditions such as tree foliage and urban canyons. Signal masking is often accompanied by extreme multi-path in urban centres with tall buildings, and is also found in wooded areas, enclosed car parks, tunnels, etc. The purpose of the system tested is to provide an accuracy of better than 20 metres almost 100% of the time throughout these interruptions, which are assumed to last up to a few minutes. The equipment used is discussed in detail, as is the method used for filtering measurements. Results are presented from tests carried out in an urban core with relatively long periods of signal loss – up to several minutes over a 6-km test circuit. Tests in urban canyons demonstrate that it is difficult to reach the above specifications with aiding from differential odometry alone due to the high precision of the wheel-scale factor required. However, with the use of a rate gyro and odometry, RMS errors are below 20 metres while availability is nearly 100%. Some of the large deviations could probably be better controlled if GPS multi-path errors were detected before they are allowed to corrupt the filtered solution.

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Thomas, Tessy, D. Jahagirdar, Iyyanki Krishna, and L. Varaprasad. "Online Trajectory Reshaping for a Launch Vehicle to Minimize the Final Error Caused by Navigation and Guidance." Defence Science Journal 63, no. 3 (May 16, 2013): 254–61. http://dx.doi.org/10.14429/dsj.63.2414.

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Rzucidło, Paweł. "Unmanned Air Vehicle Research Simulator - Prototyping and Testing of Control and Navigation Systems." Solid State Phenomena 198 (March 2013): 266–71. http://dx.doi.org/10.4028/www.scientific.net/ssp.198.266.

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This paper presents an experimental research simulator of an Unmanned Aerial Vehicle (UAV) and supporting systems, designed at the Department of Avionics and Control, Rzeszow University of Technology. The research simulator enables hardware-in-the-loop testing of an autopilot, actuators, the ground control station and telemetry modules. Particular hardware blocks can be integrated with real-time environment with the use of a CAN data bus, Ethernet interface and a set of popular serial interfaces. Current experiments support development and hardware-in-the-loop testing of advanced flight control and navigation systems of a small UAV (taking into account both the on-board and the ground segments).

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Zhu, Kai, Xuan Guo, Changhui Jiang, Yujingyang Xue, Yuanjun Li, Lin Han, and Yuwei Chen. "MIMU/Odometer Fusion with State Constraints for Vehicle Positioning during BeiDou Signal Outage: Testing and Results." Sensors 20, no. 8 (April 17, 2020): 2302. http://dx.doi.org/10.3390/s20082302.

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With the rapid development of autonomous vehicles, the demand for reliable positioning results is urgent. Currently, the ground vehicles heavily depend on the Global Navigation Satellite System (GNSS) and the Inertial Navigation System (INS) providing reliable and continuous navigation solutions. In dense urban areas, especially narrow streets with tall buildings, the GNSS signals are possibly blocked by the surrounding tall buildings, and under this condition, the geometry distribution of the in-view satellites is very poor, and the None-Line-Of-Sight (NLOS) and Multipath (MP) heavily affects the positioning accuracy. Further, the INS positioning errors will quickly diverge over time without the GNSS correction. Aiming at improving the position accuracy under signal challenging environment, in this paper, we developed an MIMU(Micro Inertial Measurement Unit)/Odometer integration system with vehicle state constraints (MO-C) for improving the vehicle positioning accuracy without GNSS. MIMU/Odometer integration model and the constrained measurements are given in detail. Several field tests were carried out for evaluating and assessing the MO-C system. The experiments were divided into two parts, firstly, field testing with data post-processing and real-time processing was carried out for fully assessing the performance of the MO-C system. Secondly, the MO-C was implemented in the BeiDou Satellite Navigation System (BDS)/integrated navigation system (INS) for evaluating the MO-C performance during the BDS signal outage. The MIMU standalone positioning accuracy was compared with that from the MIMU/Odometer integration (MO), MO-C and MIMU with constraints (M-C) for assessing the Odometer, and the influence of the constraint on the positioning errors reduction. The results showed that the latitude and longitude errors could be suppressed with Odometer assisting, and the height errors were suppressed while the state constraints were included.

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Tauhid Ahmad, Noor Hidayah, Nurliza Salim, Adhwa Amir Tan, Syahrim Azhan Ibrahim, and Maszlan Ismail. "High-Intensity Acoustic Chamber System Spectrum Profiling for Satellite Launching Environment." Applied Mechanics and Materials 793 (September 2015): 605–9. http://dx.doi.org/10.4028/www.scientific.net/amm.793.605.

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Assembly, Integration and Test Centre at National Space Agency (ANGKASA) consist of Reverberation Acoustic Test Facility (RATF). The test facility are used to generate very high sound pressure levels for satellite testing, space vehicle components including flight hardware. This reverberant type of chamber is capable to simulate acoustic field of rocket launch. This paper is discussed on the requisite of high-intensity acoustic testing. The characteristic of chamber and the noise generating capabilities for high-intensity acoustic testing are described. The maximum requirement of chamber at 155dB spectrum profiling result is discussed in this paper.

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Sánchez Morales, Eduardo, Julian Dauth, Bertold Huber, Andrés García Higuera, and Michael Botsch. "High Precision Outdoor and Indoor Reference State Estimation for Testing Autonomous Vehicles." Sensors 21, no. 4 (February 6, 2021): 1131. http://dx.doi.org/10.3390/s21041131.

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A current trend in automotive research is autonomous driving. For the proper testing and validation of automated driving functions a reference vehicle state is required. Global Navigation Satellite Systems (GNSS) are useful in the automation of the vehicles because of their practicality and accuracy. However, there are situations where the satellite signal is absent or unusable. This research work presents a methodology that addresses those situations, thus largely reducing the dependency of Inertial Navigation Systems (INSs) on the SatNav. The proposed methodology includes (1) a standstill recognition based on machine learning, (2) a detailed mathematical description of the horizontation of inertial measurements, (3) sensor fusion by means of statistical filtering, (4) an outlier detection for correction data, (5) a drift detector, and (6) a novel LiDAR-based Positioning Method (LbPM) for indoor navigation. The robustness and accuracy of the methodology are validated with a state-of-the-art INS with Real-Time Kinematic (RTK) correction data. The results obtained show a great improvement in the accuracy of vehicle state estimation under adverse driving conditions, such as when the correction data is corrupted, when there are extended periods with no correction data and in the case of drifting. The proposed LbPM method achieves an accuracy closely resembling that of a system with RTK.

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Cannon, M. E., R. Nayak, G. Lachapelle, O. S. Salychev, and V. V. Voronov. "Low-Cost INS/GPS Integration: Concepts and Testing." Journal of Navigation 54, no. 1 (January 2001): 119–34. http://dx.doi.org/10.1017/s0373463300001259.

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The high cost of inertial units is the main obstacle for their inclusion in precision navigation systems to support a variety of application areas. Standard inertial navigation systems (INS) use precise gyro and accelerometer sensors; however, newer inertial devices with compact, lower precision sensors have become available in recent years. This group of instruments, called motion sensors, is six to eight times less costly than a standard INS. Given their weak stand-alone accuracy and poor run-to-run stability, such devices are not usable as sole navigation systems. Even the integration of a motion sensor into a navigation system as a supporting device requires the development of non-traditional approaches and algorithms. The objective of this paper is to assess the feasibility of using a motion sensor, specifically the MotionPak™, integrated with DGPS and DGLONASS information, to provide accurate position and attitude information, and to assess its capability to bridge satellite outages for up to 20 seconds. The motion sensor has three orthogonally mounted ‘solid-state’ micro- machined quartz angular rate sensors, and three high performance linear servo accelerometers mounted in a compact, rugged package. Advanced algorithms are used to integrate the GPS and motion sensor data. These include INS error damping, calculated platform corrections using DGPS (or DGPS/DGLONASS) output, velocity correction, attitude correction and error model estimation for prediction. This multi-loop algorithm structure is very robust, which guarantees a high level of software reliability. Vehicular and aircraft test trials were conducted with the system in land vehicle mode and the results are discussed. Simulated outages in GPS availability were made to assess the bridging accuracy of the system. Results show that a bridging accuracy of up to 3 m after 10 seconds in vehicular mode and a corresponding accuracy of 6 m after 20 seconds in aircraft mode can be obtained, depending on vehicle dynamics and the specific MotionPak™ unit used. The attitude accuracy was on the order of 22 to 25 arcmin for roll and pitch, and about 44 arcmin for heading.

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Antonov, Dmitry, Leonid Kolganov, Aleksey Savkin, Egor Chekhov, and Maxim Ryabinkin. "NAVIGATION AND MOTION CONTROL SYSTEMS OF THE AUTONOMOUS UNDERWATER VEHICLE." EUREKA: Physics and Engineering 4 (July 31, 2020): 38–50. http://dx.doi.org/10.21303/2461-4262.2020.001361.

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Autonomous underwater vehicles (AUVs) are widely used and have proven their effectiveness in tasks such as transportation safety, area monitoring and seafloor mapping. When developing AUV’s navigation and control systems, the engineers have to ensure the required levels of accuracy and reliability for solving navigation and motion control tasks in autonomous underwater operation under restrictions on the overall dimensions and power consumption of the AUV. The main purpose of this paper is to present preliminary results of AUV navigation and motion control systems development. The AUV’s navigation system is built around strapdown inertial navigation system (SINS) designed specifically for this AUV. When surfaced, position and angular SINS correction is performed using data from dual-antenna GNSS receiver and doppler velocity log (DVL). When underwater, SINS position and velocity correction is performed using acoustic navigation system (ANS) and DVL data. AUV’s control system provides manual and automatic control. Manual control is carried out in real-time by operator via fiber-optic cable using a joystick. Automatic control allows AUV to move independently along a specified trajectory at a given depth and speed. The AUV also has a collision avoidance system that utilizes readings from a forward-facing acoustic rangefinder to estimate time before impact based on AUV’s analytic model. If possible collision is detected, information is transmitted to the control system so that a further appropriate action can be taken. Computer simulation utilizing the analytic AUV model was used in order to check the performance characteristics of the designed control and navigation algorithms. After confirming the operability of the developed algorithms, preliminary tests of the AUV were carried out. During the tests, AUV’s on-board equipment and navigation system readings were recorded and compared to the readings of the reference system, which was also installed on the AUV. During the tests, the dynamic characteristics of the AUV were evaluated. AUV’s characteristics obtained during simulation and testing will be used as a reference during future development

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B., Biju Prasad, Biju N., and Radhakrishna Panicker M.R. "High redundancy electromechanical actuator for thrust vector control of a launch vehicle." Aircraft Engineering and Aerospace Technology 91, no. 8 (September 2, 2019): 1122–32. http://dx.doi.org/10.1108/aeat-06-2018-0165.

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Purpose The purpose of this paper is to design an electromechanical actuator which can inherently tolerate a stuck or loose failure without any need for fault detection isolation and reconfiguration. Design/methodology/approach Generalized design methodology for a thrust vector control application is adopted to reduce the design iterations during the initial stages of the design. An optimum ball screw pitch is selected to minimize the motor sizing and maximize the load acceleration. Findings A high redundancy electromechanical actuator for thrust vector control has lower self-inertia and higher reliability than a direct drive simplex configuration. This configuration is a feasible solution for thrust vector control application because it offers a more acceptable and graceful degradation than a complete failure. Research limitations/implications Future work will include testing on actual hardware to study the transient disturbances caused by a fault and their effect on launch vehicle dynamics. Practical implications High redundancy electromechanical actuator concept can be extended to similar applications such as solid motor nozzle in satellite launch vehicles and primary flight control system in aircraft. Social implications High redundancy actuators can be useful in safety critical applications involving human beings. It can also reduce the machine downtime in industrial process automation. Originality/value The jam tolerant electromechanical actuator proposed for the launch vehicle application has a unique configuration which does not require a complex fault detection isolation and reconfiguration logic in the controller. This enhances the system reliability and allows a simplex controller having a lower cost.

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Chen, Kai, Jun Zhou, Fu-Qiang Shen, Han-Yan Sun, and Hao Fan. "Hypersonic boost–glide vehicle strapdown inertial navigation system / global positioning system algorithm in a launch-centered earth-fixed frame." Aerospace Science and Technology 98 (March 2020): 105679. http://dx.doi.org/10.1016/j.ast.2020.105679.

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Long, Da Feng, Jun Liu, Jun Li Sun, and Xiao Ming Zhang. "Vehicle-Mounted Satellite Receiver Positioning System Based on the MEMS Gyro." Applied Mechanics and Materials 220-223 (November 2012): 947–51. http://dx.doi.org/10.4028/www.scientific.net/amm.220-223.947.

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To ensure that the vehicular satellite receiver get enough of their own real-time, accurate attitude information, considering the requirements low-cost, MEMS (Micro- Electron Mechanical System) inertial device is applied to the design of attitude positioning system for satellite receiver. Because of the low accurate degree, inertial navigation can’t fully used to help receiver to produce parameter. This paper undertakes to make use of parameter of velocity and attitude produced by laser gyro navigation system that installed in the head of the vehicle as MEMS inertial positioning system external combination information resource. And to integrate the MEMS inertial positioning system in the model of combining velocity and attitude by using Sage-Hausa adaptive filtering algorithm to evaluate the error of inertial navigation system on line, and rectify its calculating result so as to improve its degree of accurate. Through numerous analogical grounds vehicle operation experiments, the MEMS attitude positioning could reach the degree of accurate requirements by satellite receiver, therefore the testing program is feasible.

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Farrell, Jay A., Han-Shue Tan, and Yunchun Yang. "Carrier Phase GPS-Aided INS-Based Vehicle Lateral Control." Journal of Dynamic Systems, Measurement, and Control 125, no. 3 (September 1, 2003): 339–53. http://dx.doi.org/10.1115/1.1592190.

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This paper describes the design, analysis, and implementation of a vehicle control system using control state information obtained from a carrier phase (CP) differential global positioning system (DGPS) aided inertial navigation system (INS). Experimental data from CP DGPS/INS control experiments onboard a PATH1 vehicle is included. This testing was completed with a magnetometer sensing system onboard and running to provide a ground truth reference for comparison with the CP DGPS/INS. Navigation accuracy has previously been demonstrated at the cm level with the full navigation state updated at 150 Hz. In this article, lateral position control performance is demonstrated during challenging high-speed maneuvers with trajectory tracking accuracy at the decimeter level. During these initial experiments, the control state updated at 30 Hz. Increased trajectory following accuracy is possible, but there is an inherent tradeoff between the tracking accuracy and the ride comfort. This level of performance demonstrates that CP DGPS/INS technology has the potential to serve as one component of the reliable multisensor centimeter-level position reference system that is necessary for vehicle position control applications, including automated highway systems (AHS).

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Kim, Hee-Un, and Tae-Suk Bae. "Deep Learning-Based GNSS Network-Based Real-Time Kinematic Improvement for Autonomous Ground Vehicle Navigation." Journal of Sensors 2019 (March 31, 2019): 1–8. http://dx.doi.org/10.1155/2019/3737265.

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Much navigation over the last several decades has been aided by the global navigation satellite system (GNSS). In addition, with the advent of the multi-GNSS era, more and more satellites are available for navigation purposes. However, the navigation is generally carried out by point positioning based on the pseudoranges. The real-time kinematic (RTK) and the advanced technology, namely, the network RTK (NRTK), were introduced for better positioning and navigation. Further improved navigation was also investigated by combining other sensors such as the inertial measurement unit (IMU). On the other hand, a deep learning technique has been recently evolving in many fields, including automatic navigation of the vehicles. This is because deep learning combines various sensors without complicated analytical modeling of each individual sensor. In this study, we structured the multilayer recurrent neural networks (RNN) to improve the accuracy and the stability of the GNSS absolute solutions for the autonomous vehicle navigation. Specifically, the long short-term memory (LSTM) is an especially useful algorithm for time series data such as navigation with moderate speed of platforms. From an experiment conducted in a testing area, the LSTM algorithm developed the positioning accuracy by about 40% compared to GNSS-only navigation without any external bias information. Once the bias is taken care of, the accuracy will significantly be improved up to 8 times better than the GNSS absolute positioning results. The bias terms of the solution need to be estimated within the model by optimizing the layers as well as the nodes each layer, which should be done in further research.

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Hrishikeshavan, Vikram, and Inderjit Chopra. "Refined lightweight inertial navigation system for micro air vehicle applications." International Journal of Micro Air Vehicles 9, no. 2 (June 2017): 124–35. http://dx.doi.org/10.1177/1756829316682534.

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This paper discusses the design, hardware and software methodology, and testing of an ultralight inertial navigation system (Embedded Lightweight Kinematic Autopilot-Revised (ELKA-R)) that can be used as a controller in a wide range of micro air vehicle systems. ELKA-R was designed using the 32-bit low-power ARM Cortex-M4 microprocessor as the microcontroller unit. The microcontroller unit interfaced with state of the art 9 degrees-of-freedom inertial measurement unit using inter-integrated circuit communication (I2C) protocol. A wireless transceiver was also incorporated with serial peripheral interface to wirelessly coordinate pilot inputs and sensor information with a remote basestation. Multiple timer protocols were configured to generate individual driver signals to a wide variety of motor and actuator configurations. The printed circuit board was designed as a four layer layout. ELKA-R weighed 1.7 g with a board area of 4.82 cm2, thus making it one of the smallest and lightest kinematic autopilots in open literature that can be applied to any generic micro air vehicle system. ELKA-R was tested on a variety of micro air vehicle flight demonstrators. Hover stabilization rates of 1000 Hz were achieved which were comparable to the autopilots on larger quad rotor systems such as DJI Phantom and AR-Drone. Oscillations in attitude were reduced by up to 50%–70% when compared with a previous generation lightweight autopilot.

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Arango, J. Felipe, Luis M. Bergasa, Pedro A. Revenga, Rafael Barea, Elena López-Guillén, Carlos Gómez-Huélamo, Javier Araluce, and Rodrigo Gutiérrez. "Drive-By-Wire Development Process Based on ROS for an Autonomous Electric Vehicle." Sensors 20, no. 21 (October 27, 2020): 6121. http://dx.doi.org/10.3390/s20216121.

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This paper presents the development process of a robust and ROS-based Drive-By-Wire system designed for an autonomous electric vehicle from scratch over an open source chassis. A revision of the vehicle characteristics and the different modules of our navigation architecture is carried out to put in context our Drive-by-Wire system. The system is composed of a Steer-By-Wire module and a Throttle-By-Wire module that allow driving the vehicle by using some commands of lineal speed and curvature, which are sent through a local network from the control unit of the vehicle. Additionally, a Manual/Automatic switching system has been implemented, which allows the driver to activate the autonomous driving and safely taking control of the vehicle at any time. Finally, some validation tests were performed for our Drive-By-Wire system, as a part of our whole autonomous navigation architecture, showing the good working of our proposal. The results prove that the Drive-By-Wire system has the behaviour and necessary requirements to automate an electric vehicle. In addition, after 812 h of testing, it was proven that it is a robust Drive-By-Wire system, with high reliability. The developed system is the basis for the validation and implementation of new autonomous navigation techniques developed within the group in a real vehicle.

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PARCZEWSKI, Krzysztof, and Kazimierz ROMANISZYN. "The proposition of utilisation the vehicle in 1:5 scale to construction and testing of an autonomous vehicle." Combustion Engines 168, no. 1 (February 1, 2017): 125–28. http://dx.doi.org/10.19206/ce-2017-119.

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In the near future, vehicles will be moving autonomously with little participation or completely without the driver affecting on the vehicle move. Task of driver will be limited to identify the end point of the vehicle route. Vehicles, to meet this challenge, must be equipped with the control systems and supervising the movement of the vehicle, reacting onto the movement of pedestrians and other vehicles, road signs, time of day and weather conditions. The movement of the vehicle will be controlled and driven by a system on board a vehicle, but will also be required to tracking the vehicles position and its movement parameters using of the vehicle satellite navigation systems. In addition, the motion trajectory of the vehicle will be determined and any deviation from the target track will be corrected. The article presents a proposal for determining the trajectory of the vehicle based on the control points specified by the coordinates of the location of the vehicle and ways of correcting the trajectory of the vehicle. For this purpose was utilized the vehicle in scale.

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Jiang, Wen, and Zhaohua Yang. "Guidance Law Design for Terminal Area Energy Management of Reusable Launch Vehicle by Energy-to-Range Ratio." Mathematical Problems in Engineering 2014 (2014): 1–8. http://dx.doi.org/10.1155/2014/929731.

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A new guidance scheme that utilizes a trajectory planning algorithm by energy-to-range ratio has been developed under the circumstance of surplus energy for the terminal area energy management phase of a reusable launch vehicle. The trajectory planning scheme estimates the reference flight profile by piecing together several flight phases that are defined by a set of geometric parameters. Guidance commands are readily available once the best reference trajectory is determined. The trajectory planning algorithm based on energy-to-range ratio is able to quickly generate new reference profiles for testing cases with large variations in initial vehicle condition and energy. The designed flight track has only one turn heading, which simplifies the trajectory planning algorithm. The effectiveness of the trajectory planning algorithm is demonstrated by simulations, which shows that the guided vehicle is able to successfully dissipate energy and reach the desired approach and landing glideslope target with small tracking errors.

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Jayaprasad, G., P. P. Dhanlakshmi, and S. Hemachandran. "Analysis of electrical discontinuity problem in MLB using Ishikawa model." Circuit World 42, no. 4 (November 7, 2016): 201–6. http://dx.doi.org/10.1108/cw-08-2016-0036.

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Purpose The purpose of this study/paper is regarding analysis of electrical discontinuity in penultimate layer of a few batches of Multilayer Boards (MLB) fabricated and supplied by a vendor. The ever-increasing demand of miniaturization in launch vehicle and spacecraft electronics systems has led to the usage of multilayer printed circuit boards (PCBs) for realizing high-performance electronics circuitry. Multilayer boards (MLBs) fabricated by qualified agencies based on the customer requirement are being used in the critical launch vehicle/spacecraft systems after evaluating the preliminary test results supplied by the vendor. However, a few batches of MLBs fabricated and supplied by a particular vendor (“A”) showed a discontinuity problem in a few PCB tracks connected by soldering pads. As these MLBs are part of Flight critical systems of both launch vehicle and spacecraft, a malfunction in the board may lead to fatal errors during fight or on-orbit, thereby jeopardizing the mission. Design/methodology/approach A systematic approach was followed to have a thorough understanding of the problem, and major tests such as inspection, continuity measurement, microsection of the plated through hole (PTH) and Scanning Electron Microscopy–Energy Dispersive X-ray Analysis tests were conducted on identified test boards based on Ishikawa model. Emphasis was given for horizontal microsection, as it has got a clear edge in detecting defects at any point of PTH barrel to inner-layer copper interface. Findings Systematic testing and evaluation on specimen revealed the presence of unwanted material at the bonding area of inner-layer copper and PTH copper due to inadequate fabrication process. The un-cleaned epoxy materials present at the bonding area creates a weak bond between barrel and inner-layer copper. Electrical strength of the MLB is the strength of this link. This weaker interconnection leads to electrical discontinuity of inner-layer tracks. Originality/value MLBs are part of Flight critical systems of both Launch Vehicle and Spacecraft; a malfunction in the board may lead to fatal errors during fight or on-orbit, thereby jeopardizing the mission. Case study of an original failure observed in MLBs helped to achieve normal functioning of systems and avoided failures at later stage of mission.

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VADUVESCU, Vlad Aurelian, Teodor Lucian GRIGORIE, Petre NEGREA, and Costinel Laurentiu CORCAU. "Hardware structure for an INS/GPS integrated navigator." INCAS BULLETIN 11, no. 4 (December 8, 2019): 203–13. http://dx.doi.org/10.13111/2066-8201.2019.11.4.18.

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The paper exposes the design, experimental development and testing of a hardware structure that integrates the two widely used concepts in air navigation, INS and GPS. Its detection components are an inertial module and a satellite positioning module, the data provided by them being fused with a microcontroller. The satellite positioning module is a UBLOX NEO-6M, while the inertial module, which is in fact an inertial measurement unit, includes three analogue miniaturized inertial sensors: two bi-axial analogue gyros, LPY510AL and LPR510AL, and a three-axial analogue accelerometer, MMA7361L. Since it was desired the development of the navigation application in Matlab-Simulink, to integrate the two modules it was chosen a dsPIC33EP512MU810 microcontroller, which is found in the MPLAB Device Blocks for Simulink library's microcontroller list. The first tests were performed in the laboratory conditions, with the system in various fixed positions, while the dynamic testing of the system was carried out by boarding it on a testing car, which played also the role of monitored vehicle. Simultaneously with the acquisition of experimental data, a real-time monitoring of the vehicle was made by placing its position on a map.

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Lu, Ming Feng, Bang Cheng Liu, Jian Ping Wu, Fu Kuo Hsu, and Wen Tzeng Huang. "The Indoor Automatic Guided Vehicle with an IR Positioning and Low-Cost Inertial Navigation System." Applied Mechanics and Materials 300-301 (February 2013): 494–99. http://dx.doi.org/10.4028/www.scientific.net/amm.300-301.494.

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In this study an indoor automatic guided vehicle (AGV) which is not a line-following type is constructed. Low-cost inertial navigation system (INS) and indoor positioning system (IPS) are proposed to replace the high-cost laser navigation system. These AGVs are guided by their own INS almost all the time of running in our system. The IPS constructed by infrareds is used to calibrate the accumulative errors of the inertial system after a specific time interval. Testing results show deviation is about 5% after long time and long distance of movement. This research proves the stability of this system which allows AGVs to work in warehouses by low-cost INS and IPS.

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Constantinescu, Cristian Emil. "A reactive control system for a partially guided small sounding rocket." MATEC Web of Conferences 304 (2019): 07011. http://dx.doi.org/10.1051/matecconf/201930407011.

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Most small sounding rockets are unguided vehicle. Stability is solved aerodynamically using fins and/or rapidly spinning the vehicle and trajectory is determined by the azimuth and elevation of the launch pad as the rocket usually fly a gravity turn. Access to upper atmosphere usually require two or three stages and the presence of fins on the upper stages inflict a penalty on the stability of the launcher in the start configuration. The paper presents a modification made to an existing launcher suggested by the need to add dead weight for stability when flying small payloads. By eliminating the fins from the second stage and using a RCS for active stability and control of the upper stage several opportunities arise: the aerodynamic configuration is simpler and the stability in the start configuration improved, drag is reduced a bit, non-gravity turn evolutions are possible and special payload requested attitudes (mainly orienting a camera towards ground) are conceivable. Of course, this require a new OBC with enhanced sensors and new navigation and flight control algorithms.

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Journal articles on the topic 'Launch vehicle navigation testing'

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