Missile Design Research Articles

Conceptual Design Process of a Missile Model and Production Using Additive Manufacturing Method

This study focuses on air-to-ground missile systems, which are widely used in Turkey and around the world and are becoming increasingly important. The development of missile systems takes into account various requirements defined by the end user. It is important to identify a system and its subcomponents that fully meet the requirements. This study analyzes an air-to-ground missile system and its main subcomponents identified through the conceptual design method based on the systematic design approach proposed by Pahl and Beitz. The aim is to determine the feasibility of obtaining an optimal solution that meets the requirements set by the conceptual design method. The missile design’s optimal solution was modeled using SolidWorks software. A three-dimensional (3D) printer with FDM production technology was used to produce a prototype of the computer-modeled design. ABS and ABS-plastic blend filaments were preferred due to their material properties in the FDM production process. During the printing stage, the filament and output settings of the model were determined using the 3D printer’s interface program. The filaments were then extruded through a nozzle, following the cross-sectional geometry of the part. The resulting model was printed in pieces and assembled with a tolerance of 0.1mm. This process resulted in a 3D model of the missile, which was created to represent the system structure in different colours. The study demonstrates that the conceptual design method can be used to develop innovative and meaningful missile models.

Aerodynamic Modeling of a Missile Combining Transfer Learning and Dendritic Net

During the initial stages of missile design, finding an efficient method for analyzing aerodynamic characteristics is crucial. This paper proposes a novel aerodynamic modeling method based on a limited computational fluid dynamics (CFD) dataset, combining transfer learning (TL) with Dendritic Net (DD). Initially, we employ CFD-calculated aerodynamic data to establish a pretrained model using DD. Subsequently, the model is adapted to the target domain by TL, predicting aerodynamic parameters under specific conditions. The overall aerodynamic parameters are utilized to generate a relational spectrum through DD’s white-box features, from which primary features are extracted to establish an aerodynamic polynomial model. Finally, the model’s practicality is validated by ballistic flight simulations. The innovation lies in leveraging DD to generate a relational spectrum of aerodynamic parameters, leading to a high-precision polynomial model. Research shows DD outperforms traditional cell-based networks in predicting aerodynamic parameters, and TL reduces the CFD computation workload in the target domain by 3/4 while maintaining prediction accuracy. The polynomial model exhibits superior accuracy compared to the empirical fitting formulas. The method reduces the computational workload for aerodynamic data collection, and through system identification, a high-precision polynomial model is obtained, which provides a reliable basis for missile controller design.

Adaptive control law based integrated guidance and control design for missile with the radome error compensation

This paper presents an integrated guidance and control design for the homing missiles with the radome error compensation to address the guidance problems caused by radome. Firstly, a mathematics model of the integrated guidance and control system with the compensation for the radome error is built by integrating the missile dynamics and the engagement kinematics between the missile and ground target on the longitudinal motion. Secondly, the model is transformed into a normal form by nonlinear coordinate transformation because the system is a time-varying system with mismatched uncertainties. Thirdly, an adaptive control law of the system is designed by adopting the sliding mode control theory, and the stability of the closed-loop system is also conducted. Finally, the simulation proves that the proposed integrated guidance and control scheme can effectively compensate for the radome error and ensure the hit-to-kill attack to the target.

Fixed Time Cooperative Scheme Design for Missiles Salvo Attack

This paper proposes a fixed-time cooperative control strategy for multiple missiles with impact angle constraints to accomplish the salvo attack guidance scenario on maneuvering targets. A fixed-time extended state observer (ESO) is proposed to estimate the target accelerations. In order to execute the salvo attack, along the line of sight (LOS) direction guidance law and the LOS normal direction guidance law are the two components of the proposed fixed time guidance scheme. The efficiency of the designed method is demonstrated through simulation results.

Aero-spike and aero-disk effects of on wave drag reduction of supersonic flow past over blunt body

PurposeThe purpose of this study is to explore the effects of aerospike and hemispherical aerodisks on flow characteristics and drag reduction in supersonic flow over a blunt body. Specifically, the study aims to analyze the impact of varying the length of the cylindrical rod in the aerospike (ranging from 0.5 to 2.0 times the diameter of the blunt body) and the diameter of the hemispherical disk (ranging from 0.25 to 0.75 times the blunt body diameter). CFD simulations were conducted at a supersonic Mach number of 2 and a Reynolds number of 2.79 × 106.Design/methodology/approachICEM CFD and ANSYS CFX solver were used to generate the three-dimensional flow along with its structures. The flow structure and drag coefficient were computed using Reynolds-averaged Navier–Stokes equation model. The drag reduction mechanism was also explained using the idea of dividing streamline and density contour. The performance of the aero spike length and the effect of aero disk size on the drag are investigated.FindingsThe separating shock is located in front of the blunt body, forming an effective conical shape that reduces the pressure drag acting on the blunt body. It was observed that extending the length of the spike beyond a specific critical point did not impact the flow field characteristics and had no further influence on the enhanced performance. The optimal combination of disk and spike length was determined, resulting in a substantial reduction in drag through the introduction of the aerospike and disk.Research limitations/implicationsTo predict the accurate results of drag and to reduce the simulation time, a hexa grid with finer mesh structure was adopted in the simulation.Practical implicationsThe blunt nose structures are primarily employed in the design of rockets, missiles, and re-entry capsules to withstand higher aerodynamic loads and aerodynamic heating.Originality/valueFor the optimized size of the aero spike, aero disk is also optimized to use the benefits of both.

Tehnika smanjenja opterećenja na unutrašnjim aerovagama tokom supersoničnih prelaznih pojava

Design of slender supersonic missiles requires a comprehensive experimental support in the form of wind tunnel data for a wide range of flight parameters (angle of attack and Mach number). However, in supersonic wind tunnel testing, the problem exists of transient loads at the times of the starting and stopping of the supersonic flow. In the environments of pronounced transient loads, characteristic of blowdowin wind tunnels like the T-38 of the Military technical Institute in Belgrade, it is necessary to provide control of the use of internal wind tunnel balances in the permitted design load ranges. The presented technique is related to the definition and implementation of a methodology for reducing the transient loads on wind tunnel balances in supersonic wind tunnel tests. By limiting the clearance between the model and its tail support (sting) to a magnitude which permits normal tests, but results in model-support contact during the excessive loads, part of the loads is transferred to the support sting, relieving the balance. The technique improves control over the wind tunnel test process, improves measurement accuracy and prevents damage to sensitive instrumentation (wind tunnel balances).

Configuration Optimization of a Skippable Anti-Ship Missile Considering Initial Kinematic Parameters

Skimming the sea at ultralow altitudes can be achieved by repeatedly touching and bouncing off water surface (commonly referred to as skipping), thus giving birth to skippable anti-ship missiles. However, the high impact load during skipping poses a safety hazard to the structure. Whether a missile can rebound primarily depends on the initial kinematic parameters, which also influence the impact load along with the configuration parameters. Therefore, it is important to optimize both of them. Due to the differences in types and complicated coupling of these parameters, the optimization problem becomes highly complex. In this paper, the grouped sequential quadratic programming (GSQP) algorithm is proposed to reduce the nonlinearity and nonconvexity of the problem. By bringing together the global search capability of cooperative co-evolutionary algorithm and the local search strength of GSQP, a combined optimization framework using decomposition strategies is constructed. With the support of fluid–structure interaction models, the optimization is performed to reduce impact load for the missile. The results demonstrate that simultaneously optimizing the configuration and initial kinematic parameters yields a reduction of 12.2% in the impact load on the premise of successful skipping. This research provides a valuable reference for the design of future skippable anti-ship missiles.

Визначення програми керування кутом тангажа твердопаливного ракетно-го об’єкта

This paper analyzes the trends in the improvement of the performance characteristics of guided missiles with solid-propellant sustainer engines and identifies the features and requirements for flight trajectories, design parameters, and control programs. Within the framework of the optimal control theory, the comprehensive problem of simultaneous optimization of a missile’s design parameters and control systems is formulated. An approach to the formation of missile flight control programs in the form of polynomials is developed further, thus making it possible to reduce the optimal control theory problem to a simpler problem of nonlinear mathematical simulation. The proposed approach to control program development is used at the initial design stage to form a wide range of guided missile trajectories. Use is made of a methodology for the ballistic and aeroballistic flight range optimization of the design parameters and flight control programs of a canard missile. The missile flight range depends essentially on the values of the design and trajectory parameters and control programs chosen for optimization. Because of this, the optimization of the chosen parameters (maybe, other parameters too) in the solution of specific target problems seems to be the indispensable initial stage of missile design. For the considered missile trajectories with a vertical launch where the Mach number takes different values, optimal programs of pitch time variation that maximize the flight range are determined. The analysis of the optimization results for different trajectories shows that the optimal program in active flight with a vertical launch is the linear time dependence of the pitch angle. The application package developed allows one to determine flight control programs optimal in a given class of functions and advisable design parameters and basic performance characteristics of guided missiles for various aerodynamic designs and flight schemes as early as at the initial design stage to an accuracy required for design studies. This makes it possible to analyze design alternatives, thus improving the quality of solution of problems arising at the initial design stage and reducing the time and the cost of design work on new missiles.

Differential geometric guidance law design for varying-speed missile

A unified differential geometric guidance law (DGGL) design framework for varying-speed missiles against stationary targets is proposed in this paper. The varying-speed missile guidance model is established in the arc-length domain with the help of the classical differential geometry curve theory. It is strictly proven that DGGL is a natural and intuitive choice for varying-speed missiles when intercepting stationary targets since the influence of missile speed is directly eliminated in the guidance model and also during the guidance law design process. Hence, the guidance performance of DGGL will remain the same, no matter how the missile speed changes. After that, the error dynamics approach, which is widely used in the guidance law design field for constant-speed missiles in the time domain, is extended to the arc-length domain for DGGL design. Besides, the nonlinearity of the guidance model is fully considered when designing DGGL, hence the guidance errors caused by linearizations and small-angle assumptions are avoided. Then, taking the representative optimal error dynamics (OED) as an example, the corresponding OED-based DGGLs for zero-effort-miss-control, impact-angle-control, and flying-range-control are respectively derived. Finally, the derived illustrative guidance laws are simulated and compared with their time-domain counterparts to verify the effectiveness and superiority of the proposed unified DGGL design framework.

Study on Cable Network Design of Small Tactical Missile

This paper studies the cable network design of small tactical missile from two aspects: hardware design and soft design. The hardware design of cable network mainly includes the design of electrical connector, transmission line, cable sheathing and other accessories, while the soft design involves signal redundancy design, error prevention design and electromagnetic compatibility design. The research results set up a framework for the subsequent design and manufacture of cable network, which has a certain guiding significance.

Discussion On Low-cost Design of Ammunition Electrical System

Facing the demands of future battlefield, it is necessary to realize the low-cost design of missiles to meet the large demand for small missiles in the future battlefield. Based on this condition, this paper systematically studies the low-cost optimization design of missile safety scheme and the implementation of the low-cost design of cable network, and puts forward the scheme that can achieve the low-cost design of ammunition electrical system.

Key Technology Research of Autonomous Attack Tactical Missile

The autonomous attack tactical missile is not only an important development direction of the army’s precision strike equipment in the future, but also the only way to achieve spanning development of the army’s anti-tank missiles. With the advancement of technological progress, the technical breakthroughs made in the fields of multi-source information fusion, autonomous identification, autonomous guidance and controllable damage will be directly applied to the autonomous attack tactical missile to realize autonomous attack. They will lead the army’s equipment to develop from informatization to autonomy and intelligence. Through the combat capacity design for autonomous attack tactical missiles, we put forward the three-ring design method, constructed the combat capacity support elements, sort out the main technical characteristics of autonomous attack level by level, summarized the key technologies from “reconnaissance-strike-evaluation”, the all-element kill chain of autonomous attack, and proposed solutions that may represent the future development direction based on the current research status at home and abroad.

Lazer Arayıcılar için Test Sistemi Tasarımı ve Modellemesi

Flight tests carried out during missile design and development involve high costs. Simulating these tests in a laboratory environment saves companies significant resources and labor. The Electro-Optical Measurement and Test System, where laser seekers are tested, is one of them. In this article, studies have been carried out on designing and modeling a system that can generate the target image required for testing the laser seeker in the laboratory environment. The necessary components for the test system were determined, and their information was given in detail. Labview was used for simulation studies, and the functionality of the designed system was examined with the simulations.

Utilization of two‐equation model for analysis of flow over a moving needle in the presence of magnetic field

AbstractMany applications of the ocean and aerodynamic engineering, like the design of submarines, missiles, aircraft, rockets, and jet engines, involve flow over surfaces. Moreover, several experimental propulsion methods for seagoing ships, submarines and aerospace crafts are based on magnetohydrodynamics (MHD). This research explores the MHD boundary layer flow over a moving needle (shaped like a paraboloid of revolution). Governing equations are modelled in cylindrical coordinates under axial symmetry constraint, which is then simplified by employing order of magnitude analysis. In the absence of a magnetic field, these equations are self‐similar, and this analysis is already available in the literature. We have applied the local non‐similarity method to derive the boundary layer equations up to the second level of truncation to compute the solutions of non‐similar boundary layer equations. The built‐in MATLAB routine bvp5c is used to solve these equations numerically. This analysis will assist in predicting flow quantities that are important in designing the objects mentioned above.

Aerodynamic Study of Various Fins for Missile Body

Abstract: This study aims to analyse the flow characteristics and drag profiles of six different fin geometries - clipped delta, swept, trapezoidal, elliptical, rectangular, and triangular - for subsonic, transonic, and supersonic flow at different Mach numbers. By comparing the aerodynamic characteristics of these fin variants, the research aims to identify the most efficient fin geometry for each Mach regime. This study will benefit missile designers in selecting the most suitable fin geometry for their mission by providing information on the efficiency of each fin geometry at different Mach numbers. The findings of this research will enable the development of more efficient and effective fins for missile models

Research on the Integrated Design of Missile Guidance Control Considering the Angle of Attack Constraint

The integrated guidance and control design of missile considering the attack angle constraint can effectively improve the guidance accuracy and damage effect of the missile, which has become one of the hot spots in current research. In this paper, we review the problem of integrated guidance and control design of missile considering attack angle constraint. First, the steps to construct the ensemble model are described. Second, combining with the fact that modern control theory has been successfully applied to the design of missile weapon systems, the integrated design approach for missile guidance and control in recent years is summarized and summarized in this paper. Finally, the analysis and discussion of the problems and trends that need to be addressed in the integrated design of missile guidance and control can break through the constraints of traditional missile design concepts and methods and serve as a reference for the development of a new generation of missiles.

Integrated design and analysis of inlet and missile with two side layout

Abstract Based on the flow field characteristics of the missile body, an integrated design method for missile and inlet with two side layout is proposed under asymmetric inflow. The result of numerical simulation shows that shock waves hit on cowl lip on the symmetry plane at the design condition, which verifies the method of integrated design. And the flow characteristics of inlet under the influence of the missile body are analyzed. Under the influence of asymmetric incoming flow and missile body, the first shock wave surface of the two-dimensional inlet presents the characteristics of a three-dimensional concave surface, and there is a pair of asymmetric vortex structures in the inner flow path. Finally, a bleed cavity of self-adaptively adjusting bleeding by vortex is proposed to improve the performance of inlet and broaden the inlet start and attack angle boundary. The minimum Mach number of the inlet start is reduced from 2.8 to 2.3 at ɑ = 6° and the maximum attack angle of inlet start is widened from ɑ = −1° to ɑ = 3° at Ma = 2.1.

A numerical interfacial approach to investigate the melting heat diffusion in the conical flow of hydrodynamic Casson Ferro liquid

The conical flow has its significance in the thermal design of high-speed missiles and shock jump conditions. Buoyancy-driven melting heat transfer in hydrodynamic Casson ferroliquid flow over a conical surface is assessed numerically. The buoyancy force, uneven heat sink/source, radiative heat, melting heat, and Ohmic heat are considered physical relevance. The water-based cylindrical-shaped cobalt (Co) nanoparticles are measured. The thermal conductivity of ferrofluid is measured by assessing the Hamilton-Crosser, and interfacial layer approaches. A mathematical model was established and resolved computationally using the Lobatto-IIIA-based Matlab scheme. Simultaneous results are explored and explained with the help of pictorial and mathematical outcomes. The Hamilton-Crosser model reported a higher thermal conductivity than the interfacial layer approach for Casson ferrofluid flow.

Research on construction method of modular missile family general components based on self-organizing mapping

-As far as the missile family is concerned, the general components are an important part of the missile types in the missile family. At the same time, they are also a major advantage and feature of collaborative design of multiple missile types to form the missile family. In view of the poor universality of modules in traditional missile design, this paper proposes a general components construction method based on self-organizing mapping, which aggregates the components with similar structure and little difference in performance parameters as general components, so as to maximize the proportion of general components in the component library under the condition of meeting the performance index, and then improve the efficiency of missile equipment system while reducing the design cost.

Numerical study of freestream turbulence effects on the nose cones in supersonic flow

PurposeThis paper aims to numerically investigate the influence of shock wave and freestream turbulence interaction on the parabolic and spherically blunted nose cones at supersonic speed.Design/methodology/approachUsing density-based solver, the three-dimensional steady-state simulation is carried out. The working fluid is calorically perfect that obeys ideal gas law and the no-slip boundary conditionis given to the surface of the nose cone. Pressure far-field boundary condition is imposed at the boundary of the computational domain by giving freestream Mach number, freestream static pressure and temperature.FindingsThe growth rate of the boundary layer is faster on the spherically blunted nose cone, hence, the overall drag force is higher than the parabolic nose cone. Temperature at the edge of the boundary layer is increased due to the early ampli-fication of instabilities by the upstream disturbance. In this sense, the effects of freestream turbulence depend on its level, freestream conditions, strength and type of shock wave and zone of influence.Research limitations/implicationsSimulations are carried out for the flow Mach number 2.0 at zero angles of attack for the freestream conditions of the flow at an altitude of 10,000 m.Practical implicationsThe phenomenon of shock wave–turbulence interaction occurs in flow regimes from transonic to hypersonic speeds and finds a wide range of applications, especially in the design of aircraft and missiles configurations.Originality/valueThe phenomenon of compression wave and freestream turbulence interaction around the commonly used nose cones in the case of aircraft, missiles, etc., is investigated. The performance characteristics such as aerodynamic drag, boundary layer dynamics and the nature of flow around the different nose cones at zero angle of attack are illustrated.