Missile Launch Research Articles

Ionospheric effects of the missile destruction on 9 December 2009

AbstractWe report on ionosonde and meteor radar observations made in Sodankylä Geophysical Observatory (SGO, 67°22′N, 26°38′E, Finland) on 9 December 2009, during a test launch of the Russian solid propellant military missile. Due to a technical problem, the missile was self‐destroyed around 07 UT at an ionospheric height (near 200 km altitude) over the Kola Peninsula (Russia), at a distance about 500 km to east from the observatory. Products of the explosion were spread into a large area and reached the region of SGO meteor radar observations in about 2 h (around 09 UT). After about 3 h (around 10 UT), a sporadic E layer presumably composed of the remains including long‐lived metallic (aluminum and its oxides) ions, was observed near the zenith of the SGO ionosonde. We discuss possible mechanisms accounting for transport of the remains. (1) Since the event occurred during a long‐lasting period of extremely low solar and magnetic activity, the ionospheric electric field was unlikely to play a substantial role in the transport of the remains and sporadic E layer formation. (2) The horizontal transport of the remains cannot be explained by the neutral winds based on empirical models. (3) Theoretical estimations suggest that the observed transport could be due to thermospheric turbulence.

Realization of Information Model in a Virtual Maintenance System for some Missile Launch Guidance Equipment

This article starts with basic features of assembly-disassembly model of a virtual maintenance system, and hierarchical organizational structure necessary for virtual maintenance of the model is established. Further, method for establishing hierarchical information model is defined in light of the characteristics of hierarchical structure and necessary information for this purpose. And said method is employed to construct the model for launch guidance of some missile warhead.

단계 분리형 최소 자승법을 이용한 탄도 미사일의 발사지점 예측 연구

This paper presents a method of ballistic missile launch point estimation using phase division least squares. The proposed algorithm employs smoothing to enhance estimation accuracy and generates functions of time for total velocity, flight path angle and heading angle, allowing extrapolation to estimate the launch point. Performance of the proposed algorithm is tested in conjunction with the extended Kalman filter and the Kalman filter.

Simulation analysis on air-to-air missile allowable launch envelope about cooperative air combat of multi-fighter formation

Simulation analysis on air-to-air missile allowable launch envelope about cooperative air combat of multi-fighter formation

Life Extension of F/A-18 LAU-7 Missile Launcher Housings Using Rework Shape Optimisation

LAU-7 missile launcher housings, which are fitted to most Royal Australian Air Force (RAAF) F/A-18A/B aircraft, can experience cracking in the guide rail. This paper covers the design, manufacture and validation of a life extension repair for cracked launcher housings. The repair development uses DSTO's rework shape optimisation technology and fatigue testing capabilities. The rework design reduces peak stresses by 33 %, resulting in significant fatigue life enhancements, as demonstrated by representative coupon testing. A special manufacturing jig has been designed and transitioned to the RAAF, which has used it to repair housings. These housings have performed well in flight tests, with no cracking detected.

Simulation Analysis of Wave Effect on Exceeding Water Gesture and Load of Submarine Launched Missile

In this study, we have a research on wave action on the submarine launched missile water trajectory and gesture angles during the process between launch and exit from water. Infinite water depth plane wave was used as the wave model, mathematics models of missile exceeding water under different wave conditions were established based on ideal potential flow theory. The flow field velocity potential was obtained by solving the Laplace equation, thus can obtain missile surface pressure. Considering free surface effects, simple Green's function was introduced to solve boundary value problems. Three-dimensional Fortran program and finite software ABAQUS were combined to complete the fluid-structure interaction simulation. The rules that wave level and phases effects on submarine- launched missile were finally obtained, which shows wave affect cannot be neglected. Simulation methods and results of this study have a certain reference value for the submarine-launched missile launching.

Analysis of a Missile's Initial Disturbance

In this paper, a certain type of vehicle missile launching system is the research object, which uses CAE technology to make a flexible coupling system dynamics simulation and analysis to provide a reference for similar tests. Since the complex structure of the vehicle missile system, reasonable assumptions and simplifications are made in establishing the dynamics model. Pro/E is used to build the three-dimensional model, and then it is imported to the ABAQUS to establish its dynamics model. Finally, in a complete virtual prototyping system model, we make a simulation of working conditions, and draw conclusions and analysis. The results show that the use of independent dynamics rigid-flexible coupling model dynamics simulation based on ABAQUS can be more realistic simulation of the process of vehicle missile launch, and it verifies the results of different working conditions, which provides a reference for the vehicle missile launching systems simulation .

The Effect of Thrust Eccentric and Erection Cylinder Anchor Position on the Initial Disturbances

A certain type of vehicle missile launch system is selected as the research object in this paper. The dynamic model is established on the base of reasonable hypothesis and simplification and by using of PRO / E software. In this paper, we find out the most dangerous thrust eccentric position of the missile and a better anchor position between the erection cylinder and the landing gear by using ADAMS software simulation of different conditions. The research is to provide a reference for the design of relevant weapons systems.

某型发射架检测仪方案设计与实现

某型发射架检测一直是与武器系统联机后加电进行检测，本方案设计使某型发射架能够在脱离实装武器系统情况下进行独立检测。不受场地、环境限制，并能够快速定位发射架故障通路，检测一个发射架所需时间约是过去的1/8，使用方便，安全可靠。按本方案研制的某型发射架检测仪，通过实际使用，取得较好的效果。 The missile launcher needs to be connected to the weapon system on helicopter if a test for the launcher is performed by an old tester. This scheme designs a new type of tester which is able to test the missile launcher without connecting the real weapon system. The testing is not subjected to the constraints of sites and environment. It can quickly locate the fault pathway of launcher. The required time for testing is about 1/8 of the past. It is easy to use, safe and reliable. According to this design, a new launcher tester is developed and has achieved the good effect through practice.

Obwód Kaliningradzki a bezpieczeństwo Polski

The Kaliningrad Oblast of the Russian Federation (RF) is significant for the security of Poland, Lithuania and the Baltic countries. This westernmost region of Russia is surrounded by EU and NATO states and does not have a direct contact with the RF. Considerable military potential is concentrated in this region, including medium and long range missile launchers that may be armed with nuclear warheads. The government in Moscow treats the military potential of this region as an element of pressure to influence public opinion and discourage the Polish authorities from building the US anti-missile system in Poland.

Межкорейские отношения и политика региональных держав

Missile launches and nuclear tests by DPRK in 2013 undermined inter-Korean cooperation and regional stability. The primary purpose of these activities was to strengthen legitimacy of Kim Jong Un’s administration. South Korean president Park Geun-Hye’s trustpolitik policy focused on improving mutual understanding and developing step-by-step inter-Korean cooperation. Regional powers jointly opposed North Korea’s missile and nuclear programs, but failed to elaborate common understanding on policies to promote security in the Korean peninsula as well as on prospects for the unification of Korea.

Research on Initial Disturbance Influenced by Adapter Combined with Guide Rail

Initial disturbance is the chief factor that affects missile launch accuracy and divergence while using orientation devices could reduce it effectively. In this paper, adapter combined with guide rail will be mainly studied. Modeling and simulation for missile systems will be done by virtual prototyping technology, focusing on deflection, pitch angle, and pitch angular velocity and so on to analysis initial disturbance. Results show that by mean of adapter combined with guide rail initial disturbance could be greatly reduced and launch accuracy has been improved.

탄도미사일 하층 방어 수행을 위한 발사대 배치 효과도 분석

For a lower tier defense, the distance between a launcher and an engagement control station is quite important to estimate the proper defense area and to effectively arrange missile launchers. In this paper, we have analyzed an effectiveness of anti-ballistic missile launcher arrangement for the lower tier defense against the ballistic missile. The operation concept, specific configuration and aerodynamic characteristics of the ballistic missile such as SCUD-B/C, Nodong are considered in order to develop a realistic engagement simulation. The diverse engagement results through numerical simulations are provided to conduct the effectiveness analysis of anti-ballistic missiles.

Study on Effect of Shipborne Missile Launch Position Based on Fast Fourier Transform

In allusion to the problem of launching precision, it carried on the research of the effect of shipborne missile launch position based on the spectrum analysis technology. A rigid-flexible coupling integrative model of ship movement and missile launch was built by use of virtual prototype technology. Simulation analyses on a variety of conditions were automatic conducted by launch time parameterized scripting language, and missile muzzle attitude parameters of different launch position were gained. By using of spectrum analysis which is based on FFT, the missile dynamic responsive was analyzed, and the relationship between launch position and accuracy was established. Then the position of the weapon system can be designed according to the specific motion characteristics of ship. The research result is also constructive to the selecting of suitable launch position.

Application of Integrated Neural Network Information Fusion in Fault Diagnosis of one Missile Launching Control Unit

Research and development of fault diagnosis system in application of integrated neural network information fusion is based on information fusion technology, with which preliminary analysis of equipment fault is made in different perspectives in terms of neural network, so as to identify the fault on the basis of fusion outcome. This technique is applied in fault diagnosis of one type of missile launching control unit, leading to sufficient use of various information and substantially increased fault diagnosis rate.

Ionospheric disturbances induced by a missile launched from North Korea on 12 December 2012

AbstractIonospheric disturbances caused by a missile launched from North Korea on 12 December 2012 were investigated by using the GPS total electron content (TEC). The spatial characteristic of the front edge of V‐shaped disturbances produced by missiles and rockets was first determined. Considering the launch direction and the height of estimated ionospheric points at which GPS radio signal pierces the ionosphere, the missile passed through the ionosphere at heights of 391, 425, and 435 km at 0056:30, 0057:00, and 0057:30 UT, respectively. The observed velocities of the missile were 2.8 and 3.2 km/s at that time, which was estimated from the traveling speed of the front edge of V‐shaped disturbances. Westward and eastward V‐shaped disturbances propagated at 1.8–2.6 km/s. The phase velocities of the westward and eastward V‐shaped disturbances were much faster than the speed of acoustic waves reported in previous studies, suggesting that sources other than acoustic waves may have played an important role. Furthermore, the plasma density depletion that is often observed following missile and rocket launches was not found. This suggests that the depletion resulting from the missile's exhaust was not strong enough to be observed in the TEC distribution in the topside ionosphere.

Application of Fuzzy Neural Networks on Missile Launcher Fault Prediction

In order to improve the reliability, security and validity of such type Missile Launcher, The faults prediction theory is introduced based on fuzzy neural network. The faults prediction analysis model is built, and an advanced training algorithm is proposed. Such algorithm is tested by using in the fault prediction of the missile launcher. The Experiment results illustrate that by using the proposed model, the faults prediction speed is faster 80% than ever, the prediction veracity is advanced, and the cost is reduced to 50%.

Projectile-Borne Meteorological Information Detection Dropsonde Integrating Micro-Sensors

The projectile-borne meteorological information detection dropsonde is designed to be launched by a missile and dropped at altitude as the missile reached its peak to detect real-time meteorological information as the device falls to the surface. The high acceleration shock deriving from missile launch, violent changes of atmospheric parameter and stochastic disruptions from external environment are the main difficult to design this device. To deal with those problems, we apply sensors based on MEMS technology as their high performance in accuracy, anti-overload and easy integration, we explore best locations on the dropsonde body for sensors based on simulation, we develop effective arithmetic for data processing. At last, the performance of dropsonde is verified by some ground static experiments.

Ballistic Measurement and Parameter Estimation of Ballistic Missile with Early Warning Satellite

Space infrared early warning satellite is an important platform for detecting ballistic missile launch and trajectory. This paper established observation satellite motion model, and the motion state of the satellite at any time was gotten based on its initial information by numerical integration methods. According the theory of double satellites location and satellite observation data of ballistic missile, the observation trajectory of ballistic missile was fitted. The trajectory was used to build the motion model of ballistic missile, and the position, speed and other parameters of the ballistic missile can be inferred. Finally, simulation experiment was conducted.

Multiple Tank Explosions in an Edible‐Oil Refinery Plant: A Case Study

AbstractMultiple explosions occurred when five workers were acting on a footbridge structure at the top of crude olive pomace oil tanks. Welding on the tank roofs was performed without previously cleaning the tanks stopping their operation. First, one of the several ∼ 650‐m3 reservoirs exploded, provoking a pool fire that spread throughout the tank farm. Roughly 1 h later, two other reservoirs exploded causing the launching of missiles to a distance of 60–80 m and a huge fire that extended throughout the entire tank farm. Four workers were killed instantaneously. The explosion was caused by the unusually high content of hexane in the crude olive pomace oil and, hence, by the inefficiency of the desolventization process which creates a flammable and explosive oil from a combustible one.