Course Of Flight Research Articles

Influence of bioinspired morphing on the flow field characteristics of UAV wings at low Reynolds number

The aerodynamic performance of unmanned aerial vehicles (UAV) can be improved by optimizing the surface flow characteristics over a wide range of angle of attack (AoA) through novel mechanisms. Recently, the bioinspired camber morphing concept has received greater attention because of the proven ability of nature species towards the retention of aerodynamic performance under different environmental conditions. In particular, birds like Eagles ( Accipitriformes) increase their wing camber in the course of flight to achieve maximum climbing altitude with good manoeuvring capability. The biomimetic designs such as the corrugated bone structure of Eel fish ( Anguilliformes) helps to achieve the wing camber morphing with optimal aerodynamic load distributions. The present work is focused on the bioinspired variable camber morphing (VCM) strategy to enhance the flow control behaviour and aerodynamic forces for a specific UAV wing configuration at various AoA. Here, NACA 4412 airfoil is used as a baseline wing configuration and the camber morphing mechanisms which are derived through Eel fish and Eagle are analysed. The model with Eagle wing morphing (EWM) mechanism is considered as a primary case of VCM and Eel fish’s corrugated structure is taken as a secondary case of VCM model. The coefficient of lift ( C L ), coefficient of drag ( C D), coefficient of pressure ( C p) and endurance factor are estimated for both morphed and baseline wing configurations through high fidelity numerical simulations. Interestingly, it is observed that the EWM wing configuration has excellent surface flow control characteristics than the CSM wing configuration and the results are presented with a detailed discussion.

Economical Design Perspective for Aircraft by Optimizing Airfoil S1223

Geographical positioning system based end computer control technology are utilized in the air modelling based dynamics models. Unmanned aircraft have the potential to significantly increase their coverage and flying precision. The observation area is effectively controlled if traditional continues pest control algorithms are used. Calculating the path phones take a long time. It is not ideal for aircraft control in real time, when Bezier curves are used to calculate the planning path point allow to minimize the calculation time in easiest way, but producing an expected target becomes difficult. When linear and circular interpolation devices which are frequently utilized in numerical, control system aid applied to the aircraft turning path control algorithm, the calculation time is reduced and the flight path becomes accurate as per objectives of this research discussed in section two. This paper combines flight course control and effects of flying speed an angle of attack on aircraft height to explain how the turning path control algorithm is implemented. The outcome results demonstrate that path control is accurate and the algorithm straight forward. Finally air photography and flight tests confirm the rationality of the design.

Improving Pilot Competence Through Flying Practice Learning Using Flight Simulator at the Indonesia Civil Pilot Academy of Banyuwangi

Objective: Indonesia Pilot Academy of Banyuwangi uses simulators to improve pilots' capabilities and maintain their skills. The pilot training process includes theoretical study, flight simulator and practical training. A total of eight simulators are available, including two ALSIMs and three each of the Redbird TD2 and FMX 1000. Using a simulator reduces the risk of flying in realistic conditions. Therefore, the purpose of this study is to measure the degree of effectiveness of practical flight learning, assess students' perceptions of practical flight learning, and analyze the impact of practical flight learning using a flight simulator on students' decision-making and processing abilities. Improving school pilot skills during aviation emergencies. The career of a pilot is Indonesia Pilot Academy of Banyuwangi. Method: As part of our research, we chose a quantitative research approach to objectively analyze the improvement of pilot capabilities through practical flight courses on a flight simulator at the Indonesia Pilot Academy of Banyuwangi. The main data sources are 23 flight instructors and 34 students at the Indonesian Pilot Academy in Banyuwangi. Secondary data sources, on the other hand, consist of sources that go beyond words and actions, such as written notes. These written sources can be divided into book and scholarly journal sources, archival data sources, personal documents, and official documents. In this study, the authors used a variety of documents, including documents that provide information on the number of flight instructors and student pilots currently using simulators. Results: Pilot skill development is progressing well through direct practice on flight simulators at the Banyuwangi Pilot Academy in Indonesia. This can be seen through metrics related to key improvement areas that increase flight simulation proficiency. Analyzing the previous discussion, if one considers the impact of various other factors in the questionnaire results on improving pilot abilities through practical flying courses, it can be concluded that helping to improve abilities through flight simulators is a commendable simulator. Conclusions: Improving pilot skills through direct hands-on flight simulator training at Indonesia Pilot Academy of Banyuwangi has proven successful. This success is measured by several criteria such as: good institutional management, pleasant training experience, qualified flight instructors, suitable flight simulators, suitable courses, discipline and achievement of flight objectives. Additionally, implementing a flight simulator training device (FSTD) helps maintain flight authorization and skills. The Indonesian Banyuwangi Aviation Academy uses FSTD for educational, research and community purposes. While simulator training has its benefits, it's worth noting that certain pilot skills require compliance with applicable regulations and actual flight experience.

G-Induced Loss of Consciousness Prediction Using a Support Vector Machine.

INTRODUCTION: Gravity-induced loss of consciousness (G-LOC) is a major threat to fighter pilots and may result in fatal accidents. The brain has a period of 5-6 s from the onset of high +Gz exposure, called the functional buffer period, during which transient ischemia is tolerated without loss of consciousness. We tried to establish a method for predicting G-LOC within the functional buffer period by using machine learning. We used a support vector machine (SVM), which is a popular classification algorithm in machine learning.METHODS: The subjects were 124 flight course students. We used a linear soft-margin SVM, a nonlinear SVM Gaussian kernel function (GSVM), and a polynomial kernel function, for each of which 10 classifiers were built every 0.5 s from the onset of high +Gz exposure (Classifiers 0.5-5.0) to predict G-LOC. Explanatory variables used for each SVM were age, height, weight, with/without anti-G suit, +Gz level, cerebral oxyhemoglobin concentration, and deoxyhemoglobin concentration.RESULTS: The performance of GSVM was better than that of other SVMs. The accuracy of each classifier of GSVM was as follows: Classifier 0.5, 58.1%; 1.0, 54.8%; 1.5, 57.3%; 2.0, 58.1%; 2.5, 64.5%; 3.0, 63.7%; 3.5, 65.3%; 4.0, 64.5%; 4.5, 64.5%; and 5.0, 64.5%.CONCLUSION: We could predict G-LOC with an accuracy rate of approximately 65% from 2.5 s after the onset of high +Gz exposure by using GSVM. Analysis of a larger number of cases and factors to enhance accuracy may be needed to apply those classifiers in centrifuge training and actual flight.Ohrui N, Iino Y, Kuramoto K, Kikukawa A, Okano K, Takada K, Tsujimoto T. G-induced loss of consciousness prediction using a support vector machine. Aerosp Med Hum Perform. 2024; 95(1):29-36.

An Investigation into the Informational Teaching Design of the Principles of Flight Course

With the rapid development of information technology, the education teaching mode has gradually stepped into the era of informatization. In the field of higher education, the principle of flight course, as an important theoretical course, provides solid support for cultivating the basic quality and ability of aviation students. Taking the principle of flight course as an example, this paper analyzes the current problems in the teaching design of the principle of flight course and discusses in depth the application strategies of informatization teaching design in improving the teaching effect and enhancing the practical ability of students, aiming to provide a reference for the promotion of the reform of informatization in education and teaching.

Influence of behavioural and morphological group composition on pigeon flocking dynamics.

Animals rely on movement to explore and exploit resources in their environment. While movement can provide energetic benefits, it also comes with energetic costs. This study examines how group phenotypic composition individual speed and energy expenditure during group travel in homing pigeons. We manipulated the composition of pigeon groups based on body mass and leadership rank. Our findings indicate that groups of leader phenotypes show faster speeds and greater cohesion than follower phenotype groups. Additionally, we show that groups of homogenous mass composition, whether all heavy or all light, were faster and expended less energy over the course of a whole flight than flocks composed of a mixture of heavy and light individuals. We highlight the importance of considering individual-level variation in social-level studies, and the interaction between individual and group-level traits in governing speed and the cost of travel.

A deep learning analysis of Drosophila body kinematics during magnetically tethered flight

Flying Drosophila rely on their vision to detect visual objects and adjust their flight course. Despite their robust fixation on a dark, vertical bar, our understanding of the underlying visuomotor neural circuits remains limited, in part due to difficulties in analyzing detailed body kinematics in a sensitive behavioral assay. In this study, we observed the body kinematics of flying Drosophila using a magnetically tethered flight assay, in which flies are free to rotate around their yaw axis, enabling naturalistic visual and proprioceptive feedback. Additionally, we used deep learning-based video analyses to characterize the kinematics of multiple body parts in flying animals. By applying this pipeline of behavioral experiments and analyses, we characterized the detailed body kinematics during rapid flight turns (or saccades) in two different visual conditions: spontaneous flight saccades under static screen and bar-fixating saccades while tracking a rotating bar. We found that both types of saccades involved movements of multiple body parts and that the overall dynamics were comparable. Our study highlights the importance of sensitive behavioral assays and analysis tools for characterizing complex visual behaviors.

Quadcopter Main Board Design with PID Algorithm as Controller

Kontes Robot Terbang Indonesia (KRTI) Flight controller division has a mission to independently make an unmanned aerial vehicle (UAV) controller. UAV controllers are usually made by non-local manufacturers, who have a package between the controller and the aircraft. Due to limited pins and specific functions, most controllers cannot adapt to user requirements. For this reason, in this study, we made a UAV controller with a more significant number of pins that can be programmed independently. Main Controller is a master board device used to control the stability of the UAV when flying. The main controller has been designed specifically for certain products so that the UAV cannot be modified. In this study, it is proposed to make the main controller that is specifically designed to fly a Quadcopter UAV. Movement control for quadcopter stability when flying using the Proportional Integral Derivative (PID) method. The main controller has a function that is to regulate the entire course of flight on unmanned vehicles. PID control can adapt to changes so that the system becomes stable. The PID control on the Main Controller is intended to balance the quadcopter concerning its orientation angle. The Main Controller is also tasked with recording data from sensors such as the Inertial Measurement Unit (IMU) and reading data from the remote. The controller successfully flew the quadcopter with a P value of 0.245, an I value of 0.0139, and a D value of 0.0085.

Weighting of Celestial and Terrestrial Cues in the Monarch Butterfly Central Complex.

Monarch butterflies rely on external cues for orientation during their annual long-distance migration from Northern US and Canada to Central Mexico. These external cues can be celestial cues, such as the sun or polarized light, which are processed in a brain region termed the central complex (CX). Previous research typically focused on how individual simulated celestial cues are encoded in the butterfly's CX. However, in nature, the butterflies perceive several celestial cues at the same time and need to integrate them to effectively use the compound of all cues for orientation. In addition, a recent behavioral study revealed that monarch butterflies can rely on terrestrial cues, such as the panoramic skyline, for orientation and use them in combination with the sun to maintain a directed flight course. How the CX encodes a combination of celestial and terrestrial cues and how they are weighted in the butterfly's CX is still unknown. Here, we examined how input neurons of the CX, termed TL neurons, combine celestial and terrestrial information. While recording intracellularly from the neurons, we presented a sun stimulus and polarized light to the butterflies as well as a simulated sun and a panoramic scene simultaneously. Our results show that celestial cues are integrated linearly in these cells, while the combination of the sun and a panoramic skyline did not always follow a linear integration of action potential rates. Interestingly, while the sun and polarized light were invariantly weighted between individual neurons, the sun stimulus and panoramic skyline were dynamically weighted when both stimuli were simultaneously presented. Taken together, this dynamic weighting between celestial and terrestrial cues may allow the butterflies to flexibly set their cue preference during navigation.

Comparative Analysis of Single-View and Multi-View Airborne SAR Positioning Error and Course Planning for Multi-View Airborne SAR Optimal Positioning

Airborne synthetic aperture radar (Airborne SAR) can accurately locate key targets and regions by using the flight parameters of the aircraft and the relative position information between the aircraft and the target which can be obtained from the airborne positioning and orientation system (POS). In the course of flight, the aircraft will deviate from the ideal flight path due to atmospheric turbulence, which results in the calculation deviating from the actual target position. In order to improve the target positioning accuracy, it is necessary to study the influence of aircraft motion error on the target positioning error. This study discusses the positioning accuracy of single-view airborne SAR from the perspective of linear Range-Doppler algorithm (RDA), and deduces the multi-view airborne SAR positioning error transfer model based on the multi-view airborne SAR positioning model. Based on these, we analyze the main factors that affect the positioning accuracy of the two positioning methods in detail and quantitatively reveal the mechanism by which the multi-view airborne SAR positioning method can improve the target positioning accuracy compared with the single-view airborne SAR positioning method; we also solve the problem of course planning for multi-view airborne SAR optimal positioning. The research results can provide theoretical support for the analysis of factors influencing positioning error and the positioning error correction of airborne SAR.

Metrological Validation of Pixhawk Autopilot Magnetometers in Helmholtz Cage

The use of drones is very extended for multiple applications. Some of them impose attitude and navigation requirements that need appropriate measurements. Pixhawk is an open-source autopilot used on board drones that includes a magnetometer as part of its inertial measurement unit. A testing facility based on a Helmholtz cage is used to evaluate the metrological features of different magnetometer units. The first test induces a magnetic field rotation around six different Pixhawk magnetometers, simulating changes in attitude and course for a drone. The data show a standard deviation higher than 250 mG, in comparison with the standard deviation of 30 mG in the standard gaussmeter model HMR2300. The second test is focused on the stability of the magnetometer, where the Helmholtz cage simulates a certain flight altitude and course. Values obtained from Pixhawk magnetometers range between 25 mG and 116 mG for the highest peak-to-peak magnetic field amplitude, while the standard gaussmeter range is only between 1.3 mG to 5.4 mG. Considering these results, it is possible to determine the limitations of the Pixhawk autopilot magnetometer, both in terms of manufacturing tolerances and measuring stability. Therefore, users should be very careful when using this type of autopilot in professional applications that require precision and safety.

Heading Exposure in Elite Football (Soccer): A Study in Adolescent, Young Adult, and Adult Male and Female Players.

ABSTRACTPurposeThis study aims to quantify heading exposure in real-life elite football at the level of individual male and female adolescents, young adults, and adults.MethodsHeading exposure was determined by video analysis in combination with a structured electronic registration tool and observation training, to comprehensively register heading characteristics. Characteristics of heading events were registered in 116 official matches (96 male, 20 female) of Dutch national teams.ResultsMean exposure for male players based on full match participation was 4.2 headers, with maximum heading exposure at 10.6 headers. Mean heading exposure was higher in adult than adolescent players (P = 0.049), whereas maximum heading exposure was higher for adult than for young adult players (P = 0.045). Maximum heading exposure was higher in male than in female players (P = 0.015). Defenders had the greatest mean and maximum heading exposure (P < 0.001). Longer flight courses of the ball had greater contribution to mean and maximum heading exposure than shorter courses (P < 0.01). Frontal headers had greater contribution to exposure than other points of contact on player’s head (P < 0.001), whereas linear headers had greater contribution than rotational headers (P = 0.016). Defensive headers had greater contribution to exposure than other heading types (P < 0.014). Unintentional head contacts in elite football players were, in most cases (80%), not related to heading situations.ConclusionsThis study provides real-life quantifications of mean and maximum heading exposure in elite football, with strong relevance for policy makers and researchers. The results highlight the roles of player and heading characteristics in heading exposure, informing current discussions on the role of heading in football.

Steering Behavior-based Multiple RUAV Obstacle Avoidance Control

In recent years, the applications of rotorcraft-based unmanned aerial vehicles (RUAV) have increased rapidly. In particular, the integration of bio-inspired techniques to enhance intelligence in coordinating multiple Rotorcraft-based Unmanned Aerial Vehicles (RUAVs) has been a focus of recent research and development. Due to the limitation in intelligence, these RUAVs are restricted in flying low altitude with high maneuverability. To make it possible, the RUAVs must have the ability to avoid both static and dynamic obstacles while operating at low altitudes. Therefore, developing a state-of-the-art intelligent control algorithm is necessary to avoid low altitude obstacles and coordinate without collision while executing the desired task. This paper proposes an Artificial Intelligence (AI) based steering behavior algorithm that generates a smooth trajectory by avoiding static and dynamic obstacles. The proposed method uses an obstacle detection algorithm (ODA) and obstacle avoidance algorithm (OAA). An obstacle detection algorithm is used to detect potential threats that fall in the course of flight while reaching the desired target, and obstacle avoidance algorithms use the steering behavior method to generate avoidance trajectory. A PC104 embedded board-based HIL (Hardware in the Loop) simulation environment is developed to validate the proposed algorithm. The proposed algorithm is evaluated by experimenting with a variety of nontrivial scenarios involving static and dynamic obstacles.

A variable stiffness morphing skin: preparation and properties

In the course of flight, morphing skins play an important role in morphing aircrafts. Shape memory polymer (SMP) with variable stiffness performance is a good candidate material for skin. In this paper, a series of SMP morphing skins were prepared from hydro-epoxy resin, carboxyl-terminated butadiene acrylonitrile (CTBN) and maleic anhydride. By adjusting molecular weight and content of CTBN, in-plane properties and out-of-plane properties of morphing skins can be adjusted. Due to the in-plane tensile stress acting on the skin during flight, tensile test was carried out to study its in-plane performance. After testing, skin can resist maximum in-plane tensile strength of 63.7 MPa. As for the out-of-plane performance of the skin, shape memory test was studied in this paper. All morphing skins have 100% shape fixity rate (Rf) and fast shape recovery rate (Rr). When toughened by CTBN of 10% of 4000 molecular weight with a mass fraction, the skin can recover its out-of-plane deformed shape in 33 s. The SMP skins were proved to be a promising candidate for morphing skins.

A Research Agenda for Implementing Augmented Reality in Ab Initio Pilot Training

Abstract. Augmented reality applications have the potential to change the learning experience and outcomes for the next generation of pilots. This study aimed at identifying learning issues related to ab initio flight training and exploring the potential of augmented reality in tackling them. A survey was conducted with 43 pilots (31 men, 12 women) and seven flight instructors (six men, one woman). The results show the contents of the ab initio flight course that were most difficult to learn according to the pilots’ and instructors’ experience. In addition, the participants assessed the training conditions they experienced. After familiarization with typical use cases of augmented reality, the pilots and flight instructors indicated flight training elements that could benefit from augmented reality. The results are used to specify a research agenda for developing augmented reality applications for future ab initio pilot training.

Measurement characteristics of an airborne microwave temperature profiler (MTP)

Abstract. The microwave temperature profiler (MTP), an airborne passive microwave radiometer, measures radiances, recorded as counts and calibrated to brightness temperatures, in order to estimate temperature profiles around flight altitude. From these data, quantities such as potential temperature gradients and static stability, indicating the state of the atmosphere, can be derived and used to assess important dynamical processes (e.g., gravity waves or stability assessments). DLR has acquired a copy of the MTP from NASA–JPL, which was designed as a wing-canister instrument and is deployed on the German High Altitude LOng range research aircraft (HALO). For this instrument a thorough analysis of instrument characteristics has been made in order to correctly determine the accuracy and precision of MTP measurements. Using a laboratory setup, the frequency response function and antenna diagram of the instrument were carefully characterized. A cold chamber was used to simulate the changing in-flight conditions and to derive noise characteristics as well as reliable calibration parameters for brightness temperature calculations, which are compared to those calculated from campaign data. The MTP shows quite large changes in the instrument state, imposing considerable changes in calibration parameters over the course of a single measurement flight; using a built-in heated target for calibration may yield large errors in brightness temperatures due to a misinterpretation of the measured absolute temperature. Applying the corrections presented herein to the calibration parameter calculations, the measurement noise becomes the dominant source of uncertainty and it is possible to measure the brightness temperatures around flight level (closely related to the absolute temperature close to the instrument) with a precision of 0.38 K. Furthermore, radiative transfer simulations, using the Py4CAtS package in a pencil-beam approach, indicate that the altitude range of the sensitivity of the MTP instrument can be increased by applying a modified measurement strategy. This is the first time such an extensive characterization of an MTP instrument, including a thorough calibration strategy assessment, has been published. The presented results, relevant for the wing-canister design of the MTP instrument, are important when processing MTP data: knowledge of the relevant uncertainties and instrument characteristics is essential for retrieval setup and is mandatory to correctly identify and interpret significant atmospheric temperature fluctuations.

ANALYTICAL METHODS OF CALCULATION OF POWERED AND PASSIVE TRAJECTORY OF REACTIVE AND ROCKET-ASSISTED PROJECTILES

Context. Within the framework of the accepted simplifying hypotheses, an approximate scheme of calculation of the parameters of the active and passive sections of the trajectory is proposed, which allow to study the trajectory properties of the existing as well as perspective samples of the reactive and rocket assisted projectiles. The object of the study is a model for the calculation of the trajectories of the reactive and rocket assisted projectiles based on a nonlinear system of differential equations of motion of the center of mass of the solid. Purpose. The purpose of the work is to propose for practical apply a new system of corrections in the range and direction for deviation of the flight conditions of the projectiles from the table value, based on the calculations of elements of the trajectory of the projectiles at the end of the active section of the trajectory, which greatly improves the accuracy of preparation of installations for firing and as a result - the effectiveness of hitting the target.Objective. The goal of the work is to propose a new system of corrections in the range and direction for deviation of the flight conditions of the projectiles from the table value, based on the calculations of elements of the trajectory of the projectiles at the end of the active section of the trajectory, which greatly improves the accuracy of preparation of installations for firing and as a result - the effectiveness of hitting the target.Method. The proposed analytical method allows to: determine the set of indicators characterizing the process of approaching the rocket projectile from the guide and clarify the initial conditions necessary to solve the system of equations of motion on the active section of the trajectory; which is regarded as a standalone trajectory that affects the course of the projectile's flight on the active section of the trajectory. The calculation of the passive trajectory plot for rocket projectile and the second passive plot for active rockets projectile is necessary to obtain the trajectory parameters at the point of fall (in the vicinity of the target) which is important for the correction of fire in the subsequent defeat of the target by reactive (active-reactive) projectile's (mortar shells).Results. The developed calculation method was tested in the estimation of the accuracy of the calculation of the elements of the trajectory of projectile movement.Conclusions. The calculations performed on the basis of the developed analytical method confirm the workability of the proposed mathematical support and allow recommending it for practical use in solving problems of external ballistics with the prospect of optimizing the trajectory of motion of controlled and unmanaged flying objects. Prospects for further research are to create consistent methods for calculating tactical and technical indicators of new types of ammunition.

Microtubules and Vimentin Fiber Stability during Parabolic Flights

Adequate mechanical stimulation is essential for cellular health and tissue maintenance, including articular cartilage, which lines the articulating bones in joints. Chondrocytes, which are the sole cells found in articular cartilage, are responsible for matrix synthesis, maintenance and degradation. It is generally believed that chondrocytes require mechanical stimuli through daily physical activity for adequate cartilage homeostasis. However, to date, the molecular mechanisms of cellular force sensing (mechanotransduction) are not fully understood. Among other mechanisms, the cytoskeleton is thought to play a key role. Despite that gravity is a very small force at the cellular level, cytoskeletal adaptations have been observed under altered gravity conditions of a parabolic flight in multiple cell types. In this study, we developed a novel hardware which allowed to chemically fix primary bovine chondrocytes at 7 time points over the course of a 31-parabola flight. The samples were subsequently stained for the microtubules and vimentin network and microscopic images were acquired. The images showed a large heterogeneity among the cells in morphology as well as in the structure of both networks. In all, no changes or adaptions in cytoskeleton structure could be detected over the course of the parabolic flight.

Effect of the magnus force and torque on the projectile flight range

The paper considers the origin of the Magnus force and torque in the course of the projectile flight; analytical dependencies for their determination are given and justified. The mutual orientation of the Magnus force and angular torque vectors with respect to those of the drag and lift forces, as well as with respect to the stalling, polar quenching and equatorial damping torques acting on the projectile in flight is discussed. The effect of the Magnus force and torque on the firing characteristics of artillery systems is assessed. A mathematical model of the projectile flight is presented, as well as constraints that are imposed on it and that do not considerably affect the accuracy of the description of the spatial motion of the projectile. The mathematical model is implemented programmatically on the basis of a standard subroutine for numerical integration of differential equations written in the Maple software and contains the motion equations for the projectile mass center, the motion equations with respect to the projectile mass center and equations that allow one to determine the coordinates of the projectile fall points in the base reference system. To assess the effect of Magnus force and torque on the projectile flight range, the difference method is employed, which consists in solving the system of differential equations of the spatial motion of the projectile such that changing the magnitude of the Magnus force and torque (at the assumption of the constancy of the aerodynamic forces and torques), one obtains the variation in the projectile flight range. A protocol and a scheme for assessing the effect of deviation of the projectile range on the accuracy of determination of the Magnus force strength and torque, as well as the results of numerical simulation of the deviation of the flight range for the ОФ-462Ж projectile of the 122-mm howitzer Д-30 depending on the accuracy of determination of aerodynamic force coefficients and Magnus torque are presented. It is shown that the largest deviations in the projectile flight range are observed when shooting at large launching angles and full charge (projectile speed 690 m / s); the smallest corresponding values are observed for the fourth charge (projectile speed 276 m / s) at small launching angles.

Research on fast switching interception of the real target

In order to distinguish the decoy missile from the real in the middle of the ballistic missile flight, we proposed using image recognition and sliding-mode guidance in the kinetic energy interceptor terminal guidance phase. The paper set background on the kinetic energy interceptor in the middle course of ballistic missile flight. Due to the influence of the dummy target, the preset interception point is out of alignment and interceptors require terminal guidance adjustment. In this paper, two different global fast Terminal sliding modes are used to establish the intercept model equation. By simulink simulation comparison, it is found that the sliding mode guidance proposed in this paper can quickly and effectively switch interception orbit to hit the target.