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Статті в журналах з теми "Aircraft steering surfaces"
1
Li, Nan, Yu Sun, Jian Yu, Jian-Cheng Li, Hong-fei Zhang, and Sangbing Tsai. "An Empirical Study on Low Emission Taxiing Path Optimization of Aircrafts on Airport Surfaces from the Perspective of Reducing Carbon Emissions." Energies 12, no. 9 (April 30, 2019): 1649. http://dx.doi.org/10.3390/en12091649.
Повний текст джерелаАнотація:
Aircraft emissions are the main cause of airport air pollution. One of the keys to achieving airport energy conservation and emission reduction is to optimize aircraft taxiing paths. The traditional optimization method based on the shortest taxi time is to model the aircraft under the assumption of uniform speed taxiing. Although it is easy to solve, it does not take into account the change of the velocity profile when the aircraft turns. In view of this, this paper comprehensively considered the aircraft’s taxiing distance, the number of large steering times and collision avoidance in the taxi, and established a path optimization model for aircraft taxiing at airport surface with the shortest total taxi time as the target. The genetic algorithm was used to solve the model. The experimental results show that the total fuel consumption and emissions of the aircraft are reduced by 35% and 46%, respectively, before optimization, and the taxi time is greatly reduced, which effectively avoids the taxiing conflict and reduces the pollutant emissions during the taxiing phase. Compared with traditional optimization methods that do not consider turning factors, energy saving and emission reduction effects are more significant. The proposed method is faster than other complex algorithms considering multiple factors, and has higher practical application value. It is expected to be applied in the more accurate airport surface real-time running trajectory optimization in the future. Future research will increase the actual interference factors of the airport, comprehensively analyze the actual situation of the airport’s inbound and outbound flights, dynamically adjust the taxiing path of the aircraft and maintain the real-time performance of the system, and further optimize the algorithm to improve the performance of the algorithm.
2
Liang, Peng, Xueshan Gao, Qingfang Zhang, Rui Gao, Mingkang Li, Yuxin Xu, and Wei Zhu. "Design and Stability Analysis of a Wall-Climbing Robot Using Propulsive Force of Propeller." Symmetry 13, no. 1 (December 29, 2020): 37. http://dx.doi.org/10.3390/sym13010037.
Повний текст джерелаАнотація:
This article introduces a wall-climbing robot that uses the reverse thrust of the propeller as the adsorption force. The robot is symmetrically distributed in structure and the adsorption force is symmetrically distributed before and after so that it can adapt to the surface of a variety of different media materials and achieve stable adsorption and movement of a variety of wall surfaces. The robot mainly uses the reverse thrust of the aircraft propeller as the adsorption force to achieve wall adsorption. The robot relies on four wheels to move forward. The forward power mainly comes from the combined action of the propeller reverse thrust component and the front wheel driving force. During the movement of the robot, the steering is realized by the front wheel differential control. In this paper, we design the structure of a dual-propeller dynamic adsorption wall mobile robot, plan the movement process of the robot from the ground to the wall, analyze the stable adsorption conditions of the robot wall, and carry out the robot’s motion performance and adaptability test under different ground/wall environments to verify that the robot is stable and feasible.
3
Freitag, Dean R., and J. Stephen Dibbern. "Dr Poulter's Antarctic Snow Cruiser." Polar Record 23, no. 143 (May 1986): 129–41. http://dx.doi.org/10.1017/s0032247400028321.
Повний текст джерелаАнотація:
ABSTRACTIn 1939 Dr Thomas C. Poulter, Director of the Armour Institute, Chicago and a veteran of Byrd's second Antarctic expedition, designed and constructed a 30 tonne wheeled vehicle known as the Snow Cruiser for use with the US Antarctic Service Expedition. Designed for self-contained long-distance travel, the vehicle had many new features including twin diesel engines, independent electric drive and steering on each of its four wheels, and a light aircraft carried on the roof. It was built in Chicago and tested briefly on sand dunes nearby, before being driven to Boston amid much public interest for shipment to Antarctica. At the Bay of Whales the vehicle quickly became bogged down in snow, and never moved farther south than the expedition's winter quarters. Modern evaluation of wheel-snow interaction suggests that the Snow'Cruiser unladen was three to five times too heavy for its tyres to support it on snow surfaces. It was nevertheless a bold attempt to push forward the frontiers of mobility in exploration, which failed in a spectacular fashion. The vehicle was left behind when the expedition returned home, and has subsequently been lost.
4
Pilkevych, I. A., A. M. Tokar, O. V. Franzhi, R. I. Loboda, and V. V. Dmytruk. "A TRAINING SYSTEM FOR PREPARING OPERATORS OF AERIAL VEHICLE SYSTEMS." Проблеми створення, випробування, застосування та експлуатації складних інформаційних систем, no. 20 (November 26, 2021): 83–97. http://dx.doi.org/10.46972/2076-1546.2021.20.08.
Повний текст джерелаАнотація:
In order to meet the needs of the Armed Forces of Ukraine (AFU) for specialists in the operation of unmanned aerial systems, the Zhitomir Military Institute named by S. P. Korolev deployed training for operators - military pilots. While creating the material and technical base, the issue of developing and introducing into the training process of simulators that would meet the requirements of higher military education training. Development of the scientific training system was carried out on the basis of the list of basic training issues, profound mastery of which is mandatory for the UAV operator’s. The training system was developed, manufactured and implemented in the training process, which is built as a schematic-abstracted one to ensure the conditions of effective learning material assimilation. The content basis of the scientific training system is a flat schematic outline of the aircraft, which contains typical onboard equipment of unmanned aerial vehicles and a reconstructed connection scheme of the elements. The power of the onboard equipment is provided from the classroom power supply via a stabilized power supply unit. Operation of the onboard equipment can be controlled from the manual control panel and from the ground control station via the Mission Planner program. The Mission Planner can also be controlled from the X - Plane flight simulator. In flight simulation mode, the Mission Planner screen displays a map of the flight route, the X-Plane screen displays the view and spatial orientation as well as the corresponding servo drives of the aircraft's steering surfaces and the main engine operation modes. The software of the scientific training system allows planning and adjusting the route and flight program, practicing UAV piloting skills in the flight simulator mode, simulating flight in different weather conditions. The scientific training system includes a two-channel hardware-software oscilloscope which allows to research electric processes in different electric lines of airborne equipment of the aircraft and pair interconnections between them. Functional properties of scientific training system allow to study theoretically and practice practically a wide range of training issues required in training of UAV operators. Up to this circle includes both the issues necessary for mastering drone piloting and the issues necessary for mastering the maintenance and repairs of UAV.
5
Xue, Fei, Yuchao Wang, Zenghui Jiang, and Yinong Yang. "Hypersonic Free Flight Investigation on Rudder Reflection of Aircraft." Proceedings 2, no. 8 (July 12, 2018): 542. http://dx.doi.org/10.3390/icem18-05434.
Повний текст джерелаАнотація:
In order to study the control effect of the rudder surface of the hypersonic vehicle and the coupling dynamic characteristics of the rudder surface deflection and the flight attitude, a technical platform for the deflection and motion coupling of the aircraft rudder surface was designed. The platform ejection mechanism can launch the model into the wind tunnel flow field according to the preset attitude, and model can free flight without support interference. The innovative design of the model internal rudder partial system can guarantee the model to deflect the rudder surface in the free flight process, simulate the real steering process of the aircraft. By changing spring with different springs, the speed of the rudder surface can be changed. The dual optical path and image acquisition technology can capture the motion picture before and after the deflection of the rudder surface from two angles. After the image is matched by model matching, the six degrees of freedom parameter of the model can be changed with the time curve before and after the deflection of the rudder surface, and the area of the six freedom degree curve of the different state model is compared. In other words, the specific influence of dynamic rudder rotation on the motion of the model is known. The wind tunnel test of the model in the hypersonic wind tunnel of the 500 mm is carried out using this platform. The test results are highly repeatable, and the test platform technology is mature and reliable.
6
Lobaty, A. A., A. Y. Bumai, and S. S. Prohorovith. "Step-by-step analytical synthesis of the mathematical model of automotive unmanned aircraft." «System analysis and applied information science», no. 1 (April 26, 2021): 21–28. http://dx.doi.org/10.21122/2309-4923-2021-1-21-28.
Повний текст джерелаАнотація:
The problem of the stage-by-stage synthesis of the mathematical model of the autopilot of an unmanned aerial vehicle (UAV) is considered. At the first stage, an analytical synthesis of the control acceleration applied to the center of mass of the UAV is performed to form a specified trajectory of its flight. On the basis of the results received at the first stage, at the subsequent stages, the problem of synthesizing a mathematical model of the UAV autopilot is solved with the specified requirements for ensuring the stability and dynamic accuracy of UAV control. Under actual assumptions about the corresponding nature of changes in the trajectory parameters and variables that characterize the motion of the UAV in space, the use of a linear mathematical model of the evolution of the state vector of the UAV and its control system is substantiated. When synthesizing a mathematical model of the UAV autopilot, the method of modal control of the system was used for a specified mathematical model of the object. For a specified model of motion and aerodynamic characteristics of the UAV, the law of deviation of the control steering surface is analytically received, which depends on the parameters of the translational and rotational movement of the UAV. Computer simulation of the analytically received results of control synthesis for the specified characteristics of UAVs and specific using conditions was carried out, which clearly showed the efficiency and prospects of using this approach for the synthesis of control systems for UAVs of various purposes and design.
7
Robinson, N. H., J. D. Allan, J. A. Trembath, P. D. Rosenberg, G. Allen, and H. Coe. "The lofting of Western Pacific regional aerosol by island thermodynamics as observed around Borneo." Atmospheric Chemistry and Physics Discussions 12, no. 1 (January 12, 2012): 1215–65. http://dx.doi.org/10.5194/acpd-12-1215-2012.
Повний текст джерелаАнотація:
Abstract. Vertical profiles of aerosol chemical composition, number concentration and size were measured throughout the lower troposphere of Borneo, a large tropical island in the western Pacific Ocean. Aerosol composition, size and number concentration measurements (using an Aerodyne Aerosol Mass Spectrometer, Passive Cavity Aerosol Spectrometer Probe and Condensation Particle Counter, respectively) were made both upwind and downwind of Borneo, as well as over the island itself, on board the UK BAe-146 research aircraft as part of the OP3 project. Two meteorological regimes were identified – one dominated by isolated terrestrial convection (ITC) which peaked in the afternoon, and the other characterised by more regionally active mesoscale convective systems (MCS). Upwind profiles show aerosol to be confined to a shallow marine boundary layer below 930 ± 10 hPa (~760 m above sea level, a.s.l.). As this air mass advects over the island with the mean free troposphere synoptic flow during the ITC-dominated regime, it is convectively lofted above the terrestrial surface mixed layer to heights of between 945 ± 22 (~630 m a.s.l.) and 740 ± 44 hPa (~2740 m a.s.l.), consistent with a coupling between the synoptic steering level flow and island sea breeze circulations. Terrestrial aerosol was observed to be lofted into this higher layer through both moist convective uplift and transport through turbulent diurnal sea-breeze cells. At the peak of convective activity in the mid-afternoons, organic aerosol loadings in the lofted layer were observed to be substantially higher than in the morning (by a mean factor of three). This organic matter is dominated by secondary aerosol from processing of biogenic gas phase precursors. Aerosol number concentration profiles suggest formation of new particles aloft in the atmosphere. By the time the air mass reaches the west coast of the island, terrestrial aerosol is enhanced in the lofted layer. Such uplift of aerosol in Borneo is expected to increase aerosol lifetimes in the lower free troposphere downwind, as they are above the boundary layer and therefore less likely to be lost by wet or dry deposition. It is also likely to change the role they play in the semi-direct and direct aerosol effects. The long chain of islands extending from Malaysia to Australia may all similarly be expected to present an orographic barrier to low level mean flow. This would lead to significant transport of aerosol into the tropical free troposphere across the Western Pacific region.
8
Robinson, N. H., J. D. Allan, J. A. Trembath, P. D. Rosenberg, G. Allen, and H. Coe. "The lofting of Western Pacific regional aerosol by island thermodynamics as observed around Borneo." Atmospheric Chemistry and Physics 12, no. 13 (July 12, 2012): 5963–83. http://dx.doi.org/10.5194/acp-12-5963-2012.
Повний текст джерелаАнотація:
Abstract. Vertical profiles of aerosol chemical composition, number concentration and size were measured throughout the lower troposphere of Borneo, a large tropical island in the western Pacific Ocean. Aerosol composition, size and number concentration measurements (using an Aerodyne Aerosol Mass Spectrometer, Passive Cavity Aerosol Spectrometer Probe and Condensation Particle Counter, respectively) were made both upwind and downwind of Borneo, as well as over the island itself, on board the UK BAe-146 research aircraft as part of the OP3 project. Two meteorological regimes were identified – one dominated by isolated terrestrial convection (ITC) which peaked in the afternoon, and the other characterised by more regionally active mesoscale convective systems (MCS). Upwind profiles show aerosol to be confined to a shallow marine boundary layer below 930 ± 10 hPa (~760 m above sea level, a.s.l.). As this air mass advects over the island with the mean free troposphere synoptic flow during the ITC-dominated regime, it is convectively lofted above the terrestrial surface mixed layer to heights of between 945 ± 22 (~630 m a.s.l.) and 740 ± 44 hPa (~2740 m a.s.l.), consistent with a coupling between the synoptic steering level flow and island sea breeze circulations. Terrestrial aerosol was observed to be lofted into this higher layer through both moist convective uplift and transport through turbulent diurnal sea-breeze cells. At the peak of convective activity in the mid-afternoons, organic aerosol loadings in the lofted layer were observed to be substantially higher than in the morning (by a mean factor of three). This organic matter is dominated by secondary aerosol from processing of biogenic gas phase precursors. Aerosol number concentration profiles suggest formation of new particles aloft in the atmosphere. By the time the air mass reaches the west coast of the island, terrestrial aerosol is enhanced in the lofted layer. Such uplift of aerosol in Borneo is expected to increase aerosol lifetimes in the lower free troposphere downwind, as they are above the boundary layer and therefore less likely to be lost by wet or dry deposition. It is also likely to change the role they play in the semi-direct and direct aerosol effects. The long chain of islands extending from Malaysia to Australia may all similarly be expected to present an orographic barrier to low level mean flow. This would lead to significant transport of aerosol into the tropical free troposphere across the Western Pacific region.
9
Rankin, James, Bernd Krauskopf, Mark Lowenberg, and Etienne Coetzee. "Operational Parameter Study of Aircraft Dynamics on the Ground." Journal of Computational and Nonlinear Dynamics 5, no. 2 (February 18, 2010). http://dx.doi.org/10.1115/1.4000797.
Повний текст джерелаАнотація:
The dynamics of passenger aircraft on the ground are influenced by the nonlinear characteristics of several components, including geometric nonlinearities, aerodynamics, and interactions at the tire-ground interface. We present a fully parameterized mathematical model of a typical passenger aircraft that includes all relevant nonlinear effects. The full equations of motion are derived from first principles in terms of forces and moments acting on a rigid airframe, and they include implementations of the local models of individual components. The overall model has been developed from and validated against an existing industry-tested SIMMECHANICS model. The key advantage of the mathematical model is that it allows for comprehensive studies of solutions and their stability with methods from dynamical systems theory, particularly, the powerful tool of numerical continuation. As a concrete example, we present a bifurcation study of how fixed-radius turning solutions depend on the aircraft’s steering angle and center of gravity position. These results are represented in a compact form as surfaces of solutions, on which we identify regions of stable turning and regions of laterally unstable solutions. The boundaries between these regions are computed directly, and they allow us to determine ranges of parameter values for safe operation. The robustness of these results under the variation in additional parameters, specifically, the engine thrust and aircraft mass, are investigated. Qualitative changes in the structure of the solutions are identified and explained in detail. Overall our results give a complete description of the possible turning dynamics of the aircraft in dependence on four parameters of operational relevance.
10
Казак, В. М., Т. В. Будзинська, and В. Ю. Міщерякова. "CONTROL ALGORITHM AIRCRAFT UNDER SUDDEN STEERING SURFACE DAMAGE." Science-based technologies 1, no. 1 (November 24, 2009). http://dx.doi.org/10.18372/2310-5461.1.5193.
Повний текст джерелаДисертації з теми "Aircraft steering surfaces"
1
Бурлеев, Олег Леонидович. "Усовершенствование фотоэлектрических преобразователей перемещений в компьютерных системах контроля угловых параметров самолета". Thesis, Национальный аэрокосмический университет им. Н. Е. Жуковского "Харьковский авиационный институт", 2015. http://repository.kpi.kharkov.ua/handle/KhPI-Press/19583.
Повний текст джерелаАнотація:
Диссертация на соискание ученой степени кандидата технических наук по специальности 05.13.05 - компьютерные системы и компоненты. - Национальный технический университет "Харьковский политехнический институт", Харьков, 2016.
Диссертация посвящена решению научно-практической задачи усовершенствования процесса измерения и контроля угловых перемещений рулевых поверхностей самолета. Проанализированы современные методы преобразования угловых перемещений. Описан физический принцип их действия, указаны достоинства и недостатки каждого метода. Рассмотрены наиболее характерные конструкции преобразователей, реализующих оптический метод измерения. В результате анализа устройств определена нехватка преобразователей, которые одновременно объединяют несколько преимуществ, среди которых: малые габариты конструкций, возможность производить высокоточные измерения без внесения изменений в конструкцию объекта исследования, малое количество световодов. Усовершенствованы методы фотоэлектрических измерений угловых перемещений рулевых поверхностей самолета для компьютерных систем контроля. В них, в отличие от существующих, используются такие компоненты, как: зеркало, блок поддержки уровня, кодовый диск с тремя кодирующими дорожками, держатели с оптическими элементами. Применение указанных компонентов позволяет проводить высокоточные измерения и контроль угловых перемещений при отсутствии технологической возможности изменять конструкцию объекта вращения, уменьшить габаритные параметры измерительных устройств. Предложены функциональные схемы устройств, реализующих усовершенствованные методы, а также описаны принципы их действия. Обосновано расширение области их применения. Повышена эффективность процесса измерения угловых перемещений рулевых поверхностей самолета за счет интеграции в компьютерные системы контроля разработанных фотоэлектрических преобразователей.Thesis for scientific the Degree candidate of technical sciences in the specialty 05.13.05 - computer systems and components. - National Technical University "Kharkov Polytechnic Institute", Kharkiv, 2016. The dissertation is devoted to solving scientific and applied tasks of efficiency rising measuring and control processes of angular displacement the aircraft steering surfaces. The methods for photoelectric measuring the angular displacement the aircraft steering surfaces are improved and functional schemes of devices that implement them. The algorithmic tools and software that implements optimization multivariate experiments plans using branch and bound method is developed. The optimal parameters in term of uniform distribution of optical fiber butt ends the angular displacement photoelectric converters with application of mirror are found. First synthesized mathematical models of work the photoelectric converter the aircraft surface steering angle in each control point of the measuring range, which allow to increase accuracy photovoltaic 1' and adapt sensitivity of the measuring device to the design features the aircraft steering surfaces. The architecture of the computer system angular displacement steering control surfaces of the aircraft is and developed.
2
Бурлєєв, Олег Леонідович. "Вдосконалення фотоелектричних перетворювачів переміщень в комп'ютерних системах контролю кутових параметрів літака". Thesis, НТУ "ХПІ", 2016. http://repository.kpi.kharkov.ua/handle/KhPI-Press/19580.
Повний текст джерелаАнотація:
Дисертація на здобуття наукового ступеня кандидата технічних наук за спеціальністю 05.13.05 - комп'ютерні системи та компоненти. - Національний технічний університет "Харківський політехнічний інститут", Харків, 2016.
Дисертація присвячена вирішенню науково-прикладної задачі вдосконалення процесу вимірювання і контролю кутових переміщень рульових поверхонь літака. Вдосконалено методи фотоелектричних вимірювань кутових переміщень рульових поверхонь літака для комп’ютерних систем контролю та розроблено функціональні схеми пристроїв, що їх реалізують. Розроблено алгоритмічні та програмні засоби, що реалізують оптимізацію планів багатофакторних експериментів з використанням методу гілок і меж. Знайдено оптимальні, з точки зору рівномірності, параметри розподілу торців світловодів фотоелектричного перетворювача кутових переміщень із застосуванням дзеркала. Вперше одержано математичні моделі роботи фотоелектричного перетворювача кутових переміщень рульової поверхні літака в кожній контрольній точці діапазону вимірювань, що дозволяють підвищити точність фотоелектричного перетворювача до 1´ і адаптувати чутливість вимірювального пристрою до конструктивних особливостей рульових поверхонь літака. Обґрунтовано і розроблено архітектуру комп'ютерної системи контролю кутових переміщень рульових поверхонь літака.Thesis for scientific the Degree candidate of technical sciences in the specialty 05.13.05 - computer systems and components. - National Technical University "Kharkov Polytechnic Institute", Kharkiv, 2016. The dissertation is devoted to solving scientific and applied tasks of efficiency rising measuring and control processes of angular displacement the aircraft steering surfaces. The methods for photoelectric measuring the angular displacement the aircraft steering surfaces are improved and functional schemes of devices that implement them. The algorithmic tools and software that implements optimization multivariate experiments plans using branch and bound method is developed. The optimal parameters in term of uniform distribution of optical fiber butt ends the angular displacement photoelectric converters with application of mirror are found. First synthesized mathematical models of work the photoelectric converter the aircraft surface steering angle in each control point of the measuring range, which allow to increase accuracy photovoltaic 1' and adapt sensitivity of the measuring device to the design features the aircraft steering surfaces. The architecture of the computer system angular displacement steering control surfaces of the aircraft is and developed.
Тези доповідей конференцій з теми "Aircraft steering surfaces"
1
Rankin, James, Bernd Krauskopf, Mark Lowenberg, and Etienne Coetzee. "Operational Parameter Study of Aircraft Ground Dynamics." In ASME 2009 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2009. http://dx.doi.org/10.1115/detc2009-86293.
Повний текст джерелаАнотація:
The dynamics of passenger aircraft on the ground are influenced by the nonlinear characteristics of several components, including geometric nonlinearities, the aerodynamics and interactions at the tyre-ground interface. We present a fully parametrised mathematical model of a typical passenger aircraft that includes all relevant nonlinear effects. The full equations of motion are derived from first principles in terms of forces and moments acting on a rigid airframe, and they include implementations of the local models of individual components. The overall model has been developed from and validated against an existing industry-tested SimMechanics model. The key advantage of the mathematical model is that it allows for comprehensive studies of solutions and their stability with methods from dynamical systems theory, in particular, the powerful tool of numerical continuation. As a concrete example, we present a bifurcation study of how fixed-radius turning solutions depend on the aircraft’s steering angle and centre of gravity position. These results are represented in a compact form as surfaces of solutions, on which we identify regions of stable turning and regions of laterally unstable solutions. The boundaries between these regions are computed directly and they allow us to determine ranges of parameter values for safe operation. The robustness of these results under the variation of an additional parameter, specifically, the engine thrust is investigated. Qualitative changes in the structure of the solutions are identified and explained. Overall our results give new insight into the possible turning dynamics of the aircraft in dependence on three parameters of operational relevance.
2
Memmolo, Vittorio, Carmine Vaselli, Nicola Cimminiello, Pasquale Salvato, Ernesto Monaco, and Fabrizio Ricci. "Structural Health Monitoring of Electro-Mechanical Actuators in Aviation: Recent Breakthroughs and Further Challenges." In 2021 48th Annual Review of Progress in Quantitative Nondestructive Evaluation. American Society of Mechanical Engineers, 2021. http://dx.doi.org/10.1115/qnde2021-75230.
Повний текст джерелаАнотація:
Abstract Electrical actuation systems have recently been introduced in aviation pursuing the concepts of More Electric Aircraft. Instead of employing hydraulic pipelines, Electro-Mechanical Actuator (EMA) transfers the power by “wires” with a consequent improvement of the aircraft actuation performance. However, the integration of linear electromechanical actuators is promising yet challenging in safety critical systems. Within this context, this work critically reviews electromechanical actuators currently available for aerospace application, the limits for their upcoming deployment and the different solutions to achieve an on-condition maintenance to reduce any safety risk during lifetime. First of all, the typical conversion mechanism adopted so far are briefly described with emphasis on the most suited for aerospace applications. A further insight is given to failure modes of these systems, which dramatically contrast the countless inherent advantages thereof. A particular attention is given to the jamming of the driven load, which is a critical mechanical transmission failure in many applications such as primary flight controls or landing gears extension and steering. Finally, the focus is moved to possible strategies to avoid any hazard induced by this failure. In particular, any structural alteration which is prone to induce jamming can be monitored towards the establishment of a predictive maintenance. Different possibilities are available in the way to timely assess the bearing of inner EMA surfaces where screwing is enabled.
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Cairui, Y., Z. Guoping, L. Zhenshan, W. Yuanyin, and S. Xuyao. "Shock resistance performance analysis of surface warships steering electric control cabinet based on DDAM." In CSAA/IET International Conference on Aircraft Utility Systems (AUS 2020). Institution of Engineering and Technology, 2021. http://dx.doi.org/10.1049/icp.2021.0468.
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