Maximum Flight Range Research Articles

Trajectory optimization for the diving segment of air-breathing supersonic vehicle with multi-objective

Abstract Aiming at the trajectory optimization problem of the dive section of the supersonic vehicle under the comprehensive action of different objective functions, a trajectory optimization design method for multi-optimization objectives of air-breathing supersonic vehicles is proposed. The hp adaptive pseudo-spectrum method is used to optimize the dive trajectory of an air-breathing supersonic vehicle with the maximum flight range and maximum landing velocity under the conditions of process constraints such as overload and dynamic pressure by the weighted summation method. It is proved that this method can solve the comprehensive optimization problem of multiple optimization objectives effectively and provides a new thought for the optimization of related fields.

Assessment of flight range and transmission of video information when monitoring emergency situations from an unmanned aircraft in difficult meteorological conditions

The purpose of research. Modern unmanned aerial vehicles of various types provide the ability to perform various tasks of operational information collection, monitoring the state of the environment, technological facilities and territories, updating data on these facilities, as well as for reconnaissance and monitoring their condition. The purpose of the study is to establish the maximum flight range and distance necessary for the organization of a communication channel through which the video stream and flight control commands using the KAM-16 Turbo ¾ method will be transmitted between the ground control complex and the unmanned aerial vehicle in a difficult meteorological situation.Methods are based on the basics of radio electronics, diagnostics and forecasting of the technical condition of aircraft. The methods of multicriteria analysis, parametric and structural synthesis were used. The principles of transmitting video images from drones used to monitor emergency situations were studied. A critical assessment of the maximum flight range of an unmanned aerial vehicle in a difficult meteorological situation was carried out.Results. Analytical formulas for determining the energy potential of a data transmission channel in line of sight are presented. Graphs of the dependence of the energy reserve in the data transmission channel between the unmanned aerial vehicle and the ground control system are presented, which make it possible to determine the maximum distance for transmitting video images in Full HD quality in the 2.4 GHz band. Calculations were carried out on the basis of complex analytical expressions and graphical dependences of the flight range of a micro UAV on the speed of tailwind and headwind were constructed. The maximum headwind speed is calculated, which does not allow the use of micro UAVs in blizzard conditions.Conclusion. A promising area of study of the use of UAV in emergency monitoring are micro-class copters capable of detecting victims by transmitting video information from a thermal imager during search and rescue operations in difficult weather conditions, such as snowstorms.

Algorithm for measuring parameters of radio link of an unmanned aircraft in fpv mode of the centimeter frequency range

The mass use of unmanned aerial vehicles (UAVs) in the mode of remote control "from the first person" (First Person View, FPV) in combat operations radically changes the picture of modern war. Their use makes it possible to damage or destroy enemy equipment, the cost of which is hundreds of times higher than the cost of UAVs. To successfully perform the UAV flight mission in FPV mode, it is necessary to ensure stable radio communication of the UAV with the ground control station (GSC). In the work to organize a radio line between the GSC and the UAV, it is proposed to use radio lines of the centimeter frequency range. At the same time, at the stage of flight mission planning, the UAV operator needs to have information about the parameters of the receiving and transmitting devices of the unmanned aerial vehicle complex (UAVС) in order to calculate the maximum flight range. The purpose of the work is to develop an algorithm for measuring parameters of the radio link of an unmanned aerial vehicle in the FPV mode of the centimeter frequency range. The use of this information will allow the UAVC operator to create a flight map and prepare for a combat mission. The material presented in the article contains practical value for UAV operators and can be used in the organization and planning of the flight mission of multi-rotor UAVs of the tactical level at a given distance. Also, the material can be used by UAV service units for the purpose of checking the technical parameters of the radio link between the UAV and GSC and the optical systems installed on board the UAV (video cameras, thermal imaging cameras, etc.).

MOBILE ADDITIONAL ARMOR PROTECTION FOR A TRUCK

BACKGROUND: The use of armored vehicles allows, under the threat of constant enemy influence, to protect special vehicles and special equipment from the effects of light and heavy small arms, landmines, hand grenade launchers during marches or special operations. However, at present, the issue of protecting freight transport used for transporting personnel, mortar crews, materiel, etc. is quite acute. The goal of the work is to develop a mobile set of additional armor protection for the body of a truck in order to reduce the likelihood of injury to personnel during their transportation by firearms, cumulative ammunition, fragments of artillery ammunition, as well as military equipment during its transportation. Materials and methods. Determination of parameters for the duration of the penetration process and subsequent behavior of armor protection, obtaining accurate data on the resistance and effectiveness of additional armor, analysis of the stress-strain state was performed in the Ansys program. Data were obtained on the penetration process, transition energy and subsequent behavior of armor protection, which will be used to improve armored structures and structures, as well as to improve the safety of equipment in real combat conditions. Results. The article discusses the problem of armor protection of vehicles. Examples are given of the use of additional armor protection for weapons, military and special equipment, in particular in the context of a special military operation. The study presents a mobile set of additional armor protection for the body of a truck, designed to protect personnel from injury from firearms and fragments from exploding ammunition when transported on trucks. Armor protection is made in the form of hinged armor plates, anti-cumulative grilles, secured on the outside with fastening elements. Installed on the outside of the body, armor screens act as barriers, which significantly increases the protective properties when fired from firearms. The article simulates the proposed protection set and analyzes the stress-strain state. Conclusion. Based on the calculations, the values of the maximum speeds and flight range of the bullet were determined for the strength of the additional set of armor protection.

On the possibility of changing the trajectory of a projectile or rocket based on aerodynamic impact in the shock wave zone

A physical hypothesis is proposed that it is possible to change the design trajectory of the projectile on the basis of mechanical action on the entire volume of shockwave zones with a unilateral, asymmetric presence of the second projectile. Deviating from the original trajectory results in a positive result when it comes to a defensive task. A new semi-empirical model has been developed and compiled, which allows you to calculate the trajectory of the projectile taking into account the air resistance to movement. In the new model, it is recommended that only four easily detectable values​ ​ be used in upcoming experiments: the initial departure speed , the maximum altitude , the maximum flight range and the full time. The calculation scheme uses iterative calculations. On the basis of which the values ​ ​ of numerical coefficients in the semi-empirical model are specified. The physical idea that external powerful laser radiation can heat the side surface of the projectile and the entire zone of wave jumps of the seal is justified. On one side of the semi-plant, that is, it is one-way heating. The asymmetrical thermal state on both sides of the missile may cause the missile or projectile to deviate from the previously assigned heading. This circumstance is also in favor of the proposed idea.

Sizing of Multicopter Air Taxis—Weight, Endurance, and Range

In the near future, urban air mobility (UAM) will let an old dream of human society come true: affordable and fast air transportation for almost everyone. Among the various existing designs, the multicopter configuration best combines the advantages of compactness, simplicity, and maturity. These aspects are important for actual use, particularly during the early stage of this market. This study elaborates on the design principles of UAM multicopters by examining existing models in terms of their configuration, weight, and range specifications. In particular, the weights of the different components are estimated based on empirical models, aerodynamic fundamentals for the analysis of UAM multicopters are derived from momentum theory, and the power and energy requirements for hovering and cruise flight are evaluated, thereby enabling estimation of the maximum hovering time and flight range. Finally, a sizing method is introduced and validated against an actual UAM design.

HIGH ACCURACY PIECEWISE-ANALYTIC SOLUTIONS AND HIGHER-ORDER NUMERIC SOLUTIONS OF PROJECTILE MOTION WITH A QUADRATIC DRAG FORCE BY THE MULTISTAGE MODIFIED DECOMPOSITION METHOD

We apply the multistage modified decomposition method (MDM) of Rach, Adomian, and Meyers to simulate the atmospheric projectile trajectory subject to a quadratic drag force. We readily obtain both the approximate analytic and numeric solutions through means of one-step recurrence algorithms based on the concept of analytic continuation, where the step size <i>h</i> and the order <i>m</i> are used to control errors. Simply put, the numeric solutions become the nodal values of our piecewise-analytic approximations. The realistic mathematical model includes sinusoidal, quadratic, reciprocal, and product nonlinearities which are conveniently treated by the Adomian polynomials without resort to any linearization or perturbation whatsoever. Fast algorithms of the Adomian polynomials guarantee the efficiency of our approach, and both the approximate analytic and numeric higher-order solutions can be readily generated at will unlike the usual Runge-Kutta methods that rely on a crude linearization. Multistage analytic and numeric decomposition algorithms demonstrate the rapid convergence of our new approach, where the MDM is based on the nonlinear transformation of series by the Adomian-Rach theorem. As an example, we also determine several important aerodynamic measures for the trajectory of a baseball such as the time of ascent, the velocity at the trajectory apex, the maximum height of ascent, then the flight range, the impact velocity and the impact angle with respect to the horizontal, the optimal launch angle, and the maximum flight range. We consider the error analyses for the multistage analytic approximations including the remainder error functions and also introduce the accumulative remainder error functions and the accumulative remainder error bounds for the numeric solutions. Our approximate solutions compare most favorably to the exact solution by Bernoulli.

JRCS: Joint Routing and Charging Strategy for Logistics Drones

Unmanned aerial vehicles (UAVs), commonly known as drones, are currently being used to combat the COVID-19 pandemic through applications, including the delivery of medical supplies, aerial spraying, and public space monitoring. In a pandemic, drone-based delivery is a promising and highly efficient method to reduce transportation time, cost, and exposure to infection. However, owing to both the limited battery lifetime and the limited functions of UAV in-flight missions, it is difficult to implement multiple deliveries over long distances in a single transportation mission. In this article, we study how to extend the drone flight time with charging stations and ensure multiple deliveries in a single mission. For multiple long-distance deliveries, optimization methods are required to design the delivery area networks of customers, charging stations, and delivery routes. We propose a joint routing and charging strategy (JRCS) comprising three phases to perform multiple deliveries in a single mission. We first split the customers of a delivery area using a clustering algorithm according to their distance from the nearest charging station and the maximum flight range. The second phase provides flight segmentation and intersegment routes between the depot, customer locations, and charging stations based on the maximum flight range and safe flight distance. The joint consideration of drone routes with charging stations minimizes the number of charging stations and ensures safe delivery. Finally, we formulate mixed-integer linear programming to solve the drone delivery route problem. According to simulation results, the proposed JRCS outperforms existing delivery approaches in terms of various performance metrics.

Machine learning approach for truck-drones based last-mile delivery in the era of industry 4.0

Under the vision of industry 4.0, the integration of drones in last-mile delivery can transform traditional delivery practices and provide competitive advantages. However, the combinatorial nature of the routing problem and the technical limitations of the drones present a real challenge for adopting a stand-alone drone delivery as an alternative to truck delivery. This study introduces the Parking Location and Traveling Salesman Problem with Homogeneous Drones (PLTSPHD). This problem considers a scenario in which a single truck carries identical drones along with parcels from the depot to preassigned launching/parking sites, from where the drones complete the last-mile deliveries. In contrast to previous studies that tackle truck-drone delivery using conventional optimization approaches, this paper proposes a two-phase machine learning (ML) approach for the PLTSPHD, which minimizes the total operational cost of the last-mile problem. The proposed ML approach for PLTSPHD consists of clustering and routing phases. In the first phase, a constrained k-means clustering algorithm is proposed to cluster delivery locations based on the maximum flight range and number of available drones per truck. A deep reinforcement learning (DRL) model is then developed in the second stage to find an optimal route among all constrained clusters. Experimental results show that solving the presented truck-drone problem using the ML framework can significantly reduce the operational cost compared to standard truck delivery. The constrained clustering reduces the complexity of the routing problem while adhering to the constraints. In addition, the trained DRL model outperforms the state-of-art Google’s OR-tools solver and other types of well-known heuristics in terms of both solution quality and computation time. Moreover, a sensitivity analysis of different key parameters is conducted to highlight some key trade-offs in using multiple drones and their dependence on operating costs and problem sizes.

UAV Swarm Scheduling Method for Remote Sensing Observations during Emergency Scenarios

Recently, unmanned aerial vehicle (UAV) remote sensing has been widely used in emergency scenarios; the operating mode has transitioned from one UAV to multiple UAVs. However, the current multiple-UAV remote sensing mode is characterized by high labor costs and limited operational capabilities; meanwhile, there is no suitable UAV swarm scheduling method that can be applied to remote sensing in emergency scenarios. To solve these problems, this study proposes a UAV swarm scheduling method. Firstly, the tasks were formulated and decomposed according to the data requirements and the maximum flight range of a UAV; then, the task sets were decomposed according to the maximum flight range of the UAV swarm to form task subsets; finally, aiming at the shortest total flight range of the task subsets and to balance the flight ranges of each UAV, taking the complete execution of the tasks as the constraint, the task allocation model was constructed, and the model was solved via a particle swarm optimization algorithm to obtain the UAV swarm scheduling scheme. Compared with the direct allocation method and the manual scheduling methods, the results show that the proposed method has high usability and efficiency.

Применение модели глобальной атмосферы в оценке летно-технических характеристик и построении рубежа досягаемости при подготовке полетных заданий для беспилотных летательных аппаратов морского базирования

When standard atmosphere is used in range and altitude flight profile assessment of the unmanned aerial vehicles (UAVs) flight performance, it does not take into account the huge variety of meteorological factors on different routes. Hence, it does not accurately assess the maximum flight range. It is a strategy of the “worst combinations in terms of the probability of meteorological factors” for the entire surface of the Earth at all seasons. The paper proposes a global atmosphere model to be used in flight range assessment, and compares the model with the meteorological data archive. To build the reach line when preparing flight missions for sea-based unmanned aerial vehicles, the study proposes to use the global atmosphere model, which takes into account the meteorological parameters of a given place and month, since the wind, for example, has a particularly strong effect on the flight range and has significant seasonal-latitudinal variability. The global atmosphere model and a simplified mathematical flight model can be also used in assessing the maximum permissible length of the operational section when preparing a flight route.

Larval Ecology of Anopheles Mosquitoes in Kudat, Sabah

The emergence of human Plasmodium knowlesi malaria appeared to have been precipitated by the displacement of the natural environment of macaques and Anopheles mosquitoes resulting from deforestation and land-use changes in Malaysia. A longitudinal survey of larval habitats was conducted from May 2015 to April 2016 in the District of Kudat, Sabah to better understand how these changes have affected mosquitoes across six land use categories. Larvae were collected by dipping and reared in the laboratory for the identification of adults. Five anopheline and three culicine species were present: Anopheles balabacensis, An. barbirostris, An. lesteri, An. borneensis, An. umbrosus, Aedes albopictus, Culex gelidus, and Toxorhynchites sp. An. balabacensis was found in all six land-use types. Biodiversity by genera was high in all land-use types. The relative importance of land use types and larval habitats as sources of potential vectors was analyzed by the Kruskal-Wallis H test by ranks. In decreasing order Anopheles larvae were found in rubber tree plantation &gt; coconut plantation &gt; clearing site &gt; palm oil plantation &gt; forest &gt; settlement area. Important larval habitats were intermittent stream &gt; ditch &gt; pond &gt; artificial container &gt; puddle &gt; river &gt; slow-flowing stream. Eighteen breeding sites of An. balabacensis were within (500 m) the average maximum flight range of the species and houses at risk for malaria. Knowledge gained from the study can be used to assess the need for vector control in preventing the spread of P. knowlesi in vulnerable areas.

RFID-tagged amazonian stingless bees confirm that landscape configuration and nest re-establishment time affect homing ability

Bee flight capacity determines the area that a colony can exploit, and this knowledge is essential to formulate management and conservation strategies for each species. In this study, we evaluated the flight capacity of Melipona seminigra using radio frequency identification (RFID). Three questions were addressed: Do the RFID tags affect the flight of M. seminigra workers? What is the effect of the landscape on foraging activity? Does the time since the colony was re-established affect the flight range of foragers? Our results indicate that the RFID tag used does not affect the flight ability of M. seminigra. Bees marked with nontoxic paint vs. RFID tags had the same return ratio and return time to the colony of origin. Flight capacity was affected by the landscape, because the return rate to the colonies was higher from the tested vegetated area than from the sterile area. The time elapsed since the bee colony re-establishment also affected the flight range because the return rate increased with time since the colony was relocated in the new site. We estimate that M. seminigra workers make foraging flights of approximately 1000 m from the colony and that the maximum flight range is 5000 m. Colonies of this species take more than 1 or 2 months to be able to fully exploit a landscape.

Propeller design to improve flight dynamics features and performance for coaxial compound helicopters

The coaxial compound configuration has been proposed as a concept for future high-performance rotorcraft. The co-axial rotor system requires no anti-torque device, while the longitudinal thrust is provided by a propeller. A well-designed propeller can ensure both the performance and the cruise efficiency. The propeller design also influences the flight dynamics of such configuration. To design the propeller parameters of the coaxial compound helicopter, the propeller modelling and design method devised by Adkins and Liebeck is firstly introduced. A flight dynamics model of the coaxial compound helicopter is developed. Trim characteristics, power consumption results, and handling qualities features are calculated with variable propeller parameters at optimum (corresponding to the maximum flight range) and maximum speeds. The results indicate that the propeller parameters alter its efficiency and improve the performance characteristics of this helicopter. In addition, the propeller design also influences the flight dynamics characteristics and handling qualities of the coaxial compound helicopter, and consequently affect the power consumption indirectly. In this light, a design method for the propeller has been developed by formulating the design procedure into the nonlinearly constrained optimisation problem based on the flight dynamics characteristics. The method is demonstrated by evaluating propeller parameters to improve the performance in both optimum and high-speed range, which could also guarantee the handling qualities of the rotorcraft for related requirements.

A Note on Maximum Flight Range and Maximum Flight Duration of Airplanes

A Note on Maximum Flight Range and Maximum Flight Duration of Airplanes

Влияние компоновки гиперзвукового летательного аппарата в условиях габаритных ограничений на дальность полета

The article examines the influence of the configuration of a hypersonic flight vehicle with a hori-zontal cruise flight section on the maximum flight range under the conditions of limiting dimen-sions. The ram jet and the solid propellant rocket engine were chosen as the cruise engine, and re-spective calculations were performed. The hypersonic flight vehicle was configured based on the design patented in the Russian Federation, under the condition of launch using the 3S14 universal launcher. Dependencies of the maximum range on the ratio between the launch mass to the payload were analysed. The mass efficiency indicator for a two-stage ballistic missile was chosen as a crite-rion for a comparison with other available alternatives.

System for automatic control of the motion of the center of mass of the unmanned aerial vehicle

The synthesis of the control system of the unmanned aerial vehicle under conditions of information and wind disturbances has been performed. The trajectory of the flight of an unmanned aerial vehicle under different initial conditions is discussed and an optimal trajectory is chosen for the complete execution of the flight task. It is shown that from the point of view of the flight task execution time and flight stability under disturbed conditions, the best starting angle of 45 degrees. At the same time, control was started at the active stage of flight, in order to compensate for the exit of the aircraft for altitude, which is limited to 25 kilometers in order to fully perform the flight mission. The maximum flight range of the unmanned aerial vehicle with the given parameters was provided under limited conditions of the flight mission, it is altitude.

Analysis and selection of the parametric profile of a powerplant engine for a light trainer aircraft

The relevance of this study is predetermined by the improvement to the fuel efficiency of an aircraft and, as a consequence, by the reduced cost of the life cycle of an aircraft engine, which is part of a power assembly at the training aircraft the type of DART-450. We have theoretically substantiated the flight-technical and economic characteristics of a modern light aircraft for training flying personnel. Underlying the research methods is a set of parameters, characteristics and indicators, which generally reflect the technical-economic perfection of engine in the powerplant of the technical system «powerplant ‒ airframe» at a light training aircraft. The scientific novelty of this research is in the formation of a new parametric shape of a turboprop engine for the powerplant of a light training aircraft the type of DART-450, taking into consideration the modeling of the predefined flight cycle of an aircraft and the life cycle of the engine. Numerical study has established that the maximum flight range of aircraft with different engines at the same takeoff weight is largely determined by a fuel reserve, rather than the efficiency of fuel consumption. Therefore, an engine with the lowest capacity has the advantage in all characteristics except for a takeoff distance, which is the shortest for an aircraft with the engine of maximum power. The results have substantiated that in order to perform tasks related to training flight personnel it is appropriate to install the engine AI-450SR, which has the lowest life cycle cost. It is obvious that a given aircraft with the installed engine will have the lowest cost per flight hour. However, to perform reconnaissance and strike missions at an aircraft the type of DART-450, it is advisable to install the engine AI-450SR. To perform only the strike missions at an aircraft the type of DART-450, it is expedient to install the engine MS-500V-S, which has more power than the considered motors

Quantifying the impact of low-cost carriers on international air passenger movements to and from major airports in Asia

Asia is the world’s most rapidly growing aviation market, and the region now cradles the largest number of low-cost carriers (LCCs). This paper identifies the causal effect of LCC entry on international air passenger flows to and from 30 major airports in Asia using reservation-based international air passenger traffic data for years 2010 and 2015 (N=123,148). In order to bypass the endogeneity arising from self selection of LCCs’ entry decision as well as confounding by unobservables, the paper utilizes multiple identification strategies, namely, difference-in-differences (DID), propensity score matching coupled with DID, DID with inverse-probability weighted regression adjustment, and a fuzzy regression discontinuity design (RDD) with the maximum flight range of an aircraft typically used by LCCs as the cutoff. The results consistently show that LCC impact on international air passenger traffic is strictly positive, and is decreasing over distance with slight convexity. Another finding is that the impact of LCC entry net of competition effect holding market concentration constant accounts for the major part of the overall impact, i.e. LCC replacing full-service carriers greatly increases international air passenger movements in Asia.

Cooperative search-attack mission planning for multi-UAV based on intelligent self-organized algorithm

This paper proposes an intelligent self-organized algorithm (ISOA) to solve a cooperative search-attack mission planning problem for multiple unmanned aerial vehicles (multi-UAV). This algorithm adopts the distributed control architecture which divides the global optimization problem into several local optimization problems. Each UAV is able to solve its own local optimization problem, and then make the optimal decision for the multi-UAV system through the information exchange among UAVs. The search-attack mission planning process is divided into two phases, the one is waypoints generation under constraints of UAV's maneuverability, collision avoidance and maximum range, the other is path generation which takes account of the threat avoidance. In the first phase, an improved distributed ant colony optimization (ACO) algorithm is presented to carry out the mission planning and generate waypoints. Considering the range constraint of UAV, a new state transition rule is designed to guide UAV back to its initial point within the maximum flight range. In the second phase, Dubins curve is employed to smoothly connect the waypoints generated by the ACO. As for the unexpected threats during the flight, an online threat avoidance method is proposed to replan the paths. Finally, simulations are carried out to analyze the convergence performance, external responsiveness and internal scalability of the proposed ISOA for the multi-UAV search-attack mission planning problem.