Pyrotechnic Devices Research Articles

큐브위성용 힌지 구동형 분리너트식 구속분리장치의 실험적 성능검증

전개형 우주 구조물의 구속 및 분리를 위해 일반적으로 적용되는 폭발식 분리장치의 경우, 극초소형 위성으로 분류되는 큐브위성에는 적용불가가 설계요구조건으로 규정되어있다. 큐브위성의 제한된 장착 공간과 이로 인한 저충격 요구조건, 저가의 개발비 등의 요구조건으로부터 일반적으로 적용이 용이한 나일론선 열선절단방식이 적용되고 있다. 하지만 나일론선 적용에 따른 낮은 체결력과 복수 구조물의 구속/분리를 위해 복수의 체결부와 열선을 필요로 하는 등 시스템 복잡화 및 신뢰도 저하의 문제점이 존재한다. 본 연구에서는 상기의 문제점 해결을 위해 힌지 구동형 분리너트를 적용한 구속분리장치를 제안하였으며, 인증시험 온도범위에서의 분리장치 동작 기능시험, 정하중 시험, 충격레벨 측정시험을 통해 설계의 유효성을 입증하였다. Pyrotechnic devices are widely used for space appendages. However, a cube satellite requirements do not permit the use of explosive pyrotechnic device. A nichrome burn wire release has typically been used for holding and release of deployable appendages of the cube satellite due to its simplicity and low cost. However, relatively low mechanical constraint force and system complexity for application of multi-deployable systems are disadvantages of the conventional mechanism. To overcome these drawbacks, we developed a hinge driving segmented nut type holding and release mechanism based on the nichrome burn wire release. The functional performance of the mechanism has been verified through release function test, static load test and shock level measurement test.

Nondestructive prediction of point source pyroshock response spectra based on experimental conditioning of laser-induced shocks

Pyroshock can easily cause failures in electronic and optical components that are sensitive to high-frequency energy. Pyroshock is generated during explosive-based pyrotechnical events, such as the separation of boosters from a space shuttle and the separation of satellites from a space launcher. Therefore, the prediction of high-frequency structural response, particularly the shock response spectrum (SRS), is important for safe operation of pyrotechnical devices. In general, real explosive testing using distributed accelerometers is widely used. This paper proposes a technology to replace the expensive, dangerous, low-repeatability explosive test with a laser-induced shock test based on a laser beam and in-line filter conditioning. This method does not use any special numerical signal processing. Two different experiments based on explosive and laser excitation were performed with a 2-mm thick aluminum plate. The optimum laser-induced shock experimental conditions to predict real pyroshock were investigated while considering the size, energy, and fluence of the laser beam as parameters. The similarity of the SRS of the laser-induced shock to that of the real explosive pyroshock was evaluated based on the mean acceleration difference (MAD, %). The experimentally determined optimal conditions were also applied to four points on the path of a pyroshock propagation. To match the SRS at each point, the laser-induced shock was amplified, for which three different gain concepts are proposed: the initial gain, optimized gain, and constant gain. The proposed technology enables nondestructive pyro SRS prediction by conditioning the laser-induced shock to obtain an SRS with high similarity to the real pyroshock.

Impact of nano particles on safety and environment for fireworks chemicals

Pyrotechnic devices, commonly known as fireworks, have a huge popularity. The sonic effect produced by the fireworks mainly depends upon the chemical composition of the mixtures and the particle size. Specifically this means that the larger the particle size, the more the quantity of powder mixture is to be used. Therefore, a high quality product which can produce the expected noise level with lesser quantity of chemicals is a major challenge faced by the pyrotechnic industry. This can be achieved by adopting either of the two approaches namely, one, by changing the chemical composition or, the other, by changing the particle size. At present the particle size of the chemical composition is at the micron level. However, by converting the composition into nano size, the volume of mixture used will be greatly reduced without compromising the sound level produced. The major advantage of using nano size powders is that it is essentially environmental friendly, producing less pollution and ensuring a cleaner environment. Concurrently, the major risk in using nano size powders is that it is a fire hazard. In this paper, the pros and cons of using nano powders in the manufacture of fireworks have been analyzed, collecting data from various research works and presenting the same as a review article.

Development of a Numerical Model for an Expanding Tube with Linear Explosive Using AUTODYN

Pyrotechnic devices have been employed in satellite launch vehicle missions, generally for the separation of structural subsystems such as stage and satellite separation. Expanding tubes are linear explosives enclosed by an oval steel tube and have been widely used for pyrotechnic joint separation systems. A numerical model is proposed for the prediction of the proper load of an expanding tube using a nonlinear dynamic analysis code, AUTODYN 2D and 3D. To compute a proper core load, numerical models of the open-ended steel tube and mild detonating tube encasing a high explosive were developed and compared with experimental results. 2D and 3D computational results showed good correlation with ballistic test results. The model will provide more flexibility in expanding tube design, leading to economic benefits in the overall expanding tube development procedure.

Pyrotechnical timing devices for objects of space technology

The article presents results of developments of pyrotechnical timing devices charged with quick- and slow-burning low-gas compositions of the new generation. The devices provide a wide range of time intervals from milliseconds up to tens of minutes and are highly resistant to conditions of the launch and space flight.

Study on Mechanical Materials with Overview of Connection and Separation Devices

Different kinds of mechanical materials in connection and separation devices have been widely used in spacecraft engineering and keep on innovating and improving. Pyrotechnic and non-pyrotechnic devices have their own advantages and drawbacks and the application of new materials such as SMA (shape memory alloy) and low-melting point materials has become a new and striving issue. Different kinds of connection and separation devices and their prime mechanical materials will be presented in details in this paper.

A review of the benefits of electronic detonators

Computerized drilling and the electronic timing of detonations are two technological breakthroughs which have had an important role in updating drilling and blasting excavation methods, although the electronic timing of detonators is still a comparatively infrequent technical solution to precision blasting problems. On the basis of an extensive collection of published cases, this paper reviews the successes achieved and the main expected advantages from the electronic ignition devices. After describing the primary characteristics of these detonators, some elements will be considered, in order to better understand their applications in different conditions, both in open pit and underground sites: extension of the time delay number, freedom in the choice of time intervals between detonations, timing accuracy, reduction of vibrations, control of back-break and fragmentation. The results are compared to those obtained by pyrotechnical timing devices, and summarized in the concluding remarks.

핀풀러 신뢰도 예측

핀풀러의 신뢰도를 몬테카를로 시뮬레이션을 통해서 예측하였다. 예측방법은 응력-강도 간섭 모델에 근거한다. 이 모델은 강도가 응력보다 작을 경우를 고장으로 간주한다. 본 연구에서 강도는 핀을 예정된 거리까지 후퇴시키는데 필요한 에너지로, 응력은 이 핀의 운동을 방해하는데 소요되는 에너지로 간주하였다. 전자는 주로 화약량에 의해 결정되고 후자는 여러 가지 마찰력과 반발방지장치에서 소모되는 에너지에 의존한다. 응력과 강도 변수들은 해석적 성능 모델로부터 계산하였다. 본 연구에서 제시된 방법은 많은 시료가 필요하지 않기 때문에 유사한 종류의 파이로 장치 신뢰도 계산에도 적용될 수 있다. Reliability of a pin puller was predicted by Monte Carlo simulation. The prediction method is based on the stress-strength interference model that failure occurs if the stress exceeds the strength. In this study, the strength is considered as the energy delivered by combustion of pyrotechnics to retreat the pin to a predetermined position, whereas the stress is regarded as the energy required to resist the pin movement. The former mainly depends on the amount of pyrotechnic charge and the latter is governed by several friction forces and the energy dissipation within locking mechanism. Both the variables of stress and strength were computed using an analytical performance model. The method presented here, not depending upon a large number of test item, can be applicable to predict the reliability of other kinds of pyrotechnic devices.

Performance investigation of variable damping shock absorber combined with conventional semi-active vibration control logics

The shock induced by a rocket lift-off and pyrotechnic device actuation for interstage separation can cause damage to the on-board instruments of a spacecraft when the acceleration generated by the input shock exceeds their allowable acceleration value. The shock can be attenuated by mounting a shock absorber. In this paper, we propose a variable damping shock attenuation strategy combined with conventional semi-active vibration control laws derived from a two elements model composed of variable damping and spring stiffness that would attenuate the shock such that the main instrumentʼs input acceleration does not exceed the allowable acceleration value. The analysis results indicate that the combination of shock and conventional semi-active control logic attenuates the shock level better than an optimal passive and conventional semi-active control system. The strategy is also effective for suppressing the consequent vibration induced by the shock event.

터보프롭 항공기의 스핀/실속 회복장치 설계

본 논문은 KC-100 소형민항기의 스핀시험을 위해 장착될 스핀회복장치의 설계 및 지상활주 전개 시험에 대해 기술하였다. 스핀회복장치에 대한 상세 설계 단계에서 공력, 구조, 안정성, 조종성 등에 대한 해석적 결과를 토대로 낙하산 단위면적당 라이저 길이, 낙하산 다공성, 낙하산 펼침 시간, 및 전개방법 등의 설계 변수를 결정했다. 본 시스템의 검증을 위해 항공기에 스핀회복장치를 장착한 상태에서 기능점검 후 KC-100 고속활주 중 스핀슈트 전개를 수행했다. This paper deals with Spin/Stall Recovery Parachute System from design to ground taxiing stage which would be deployed on the high speed taxi of turbo-prop airplane. In detail design phase, design parameters- riser length, parachute type, size, porosity, parachute canopy filling time, and deployment method- were considered based on the analytical disciplines such as aerodynamics, structures, and stability & control. Before the installation of Spin/Stall Recovery System of turbo-prop airplane, all control functions of this system were validated by the SBTB(System Breakout Test Box) in the laboratory. SBTB was used to confirm if it can detect faults, and simulate the firing of pyrotechnic devices that control the deployment and jettison of it. Once confirmed normal operation, deployment of parachute on the high speed taxiing were performed.

Modeling of Heterogeneous Propellant Combustion: A Survey

H ETEROGENEOUS solid energetic materials are widely used in the aerospace and defense industries in rockets, explosives, and diverse pyrotechnic devices. Their basic microstructure consists of oxidizer particles embedded in a polymeric binder. Two important classes of energeticmaterials are solid propellants and plastic bonded explosives. A typical composite solid propellant is composed ammonium perchlorate (AP) particles embedded in a polymer such as hydroxyl-terminated polybutadiene (HTPB) or polybutadiene acrylonitrile. A common variation is the addition of metal particles (e.g., aluminum) to raise the combustion temperature. Plastic bonded explosives consist of a heterogeneous mixture of high-explosive crystals (such as cyclotetramethylenetetranitramine or cyclotrimethylenetrinitramine) and a polymeric binder. Here, the discussion is restricted to composite solid propellants. The intent of the present survey is to provide a highlighted discussion of relevant work on the multidimensional computational simulation of heterogeneous solid propellant combustion. Routine numerical simulations are now being carried out, in which many of the physical characteristics of real propellants are mimicked, including random packing of oxidizer particles in a fuel binder, unsteady three-dimensional heat conduction within the solid, unsteady regressionof thenonplanar propellant surface, andcoupling with an unsteady three-dimensional combustion field sustained by reactantfluxes from the surface. Such computations require the use of massively parallel supercomputers, and even then there are limitations onwhat physics can be included. The ultimate goal is to develop a truly predictive simulation tool that can assist in design and optimization of propellant microstructures and propellant grain designs for internal solid rocket motors. Modeling and simulation of composite propellants will remain a vital task because solid rocket motors are critical to national defense, communications, space exploration, and eventually space tourism. The value of computational combustion is eloquently presented in a recent review paper [1]. II. Modeling

Design and testing of the KC-100 Spin Recovery Parachute System (SRPS)

This paper presented the design of SRPS, ground function test, and the deployment test on a high speed taxi of KC-100 airplane. KAI has developed a spin recovery system in collaboration with Airborne Systems for KC-100 general aviation airplane. Spin mode analysis, rotary balance and forced oscillation tests were performed to obtain the rotational, dynamic derivatives in the preliminary design phase. Prior to the detailed design process of SRPS, approximations for initial estimation of design parameters- fineness ratio, parachute porosity, parachute canopy filling time, and deployment method- were considered. They were done based on the analytical disciplines such as aerodynamics, structures, and stability & control. SRPS consists of parachute, tractor rocket assembly for deployment, attach release mechanism (ARM) and cockpit control system. Before the installation of SRPS in KC-100 airplane, all the control functions of this system were demonstrated by using SBTB(System Breakout Test Box) in the laboratory. SBTB was used to confirm if it can detect faults, and simulate the firing of pyrotechnic devices that control the deployment and jettison of SRPS. Once confirmed normal operation of SRPS, deployment and jettison of parachute on the high speed taxiing were performed.

Firework displays as sources of particles similar to gunshot residue

In light of past research being targeted to find specific particles which may be similar to gunshot residue (GSR), this project was formulated to detect any possible particulate by random particle fallout onto substrates at firework displays and to assess the impact this may have on GSR evidence. Firework residue was collected at a display site, from amongst spectators as well as from the author's hair 90min after the display. SEM-EDX analysis has detected such particulate in all three scenarios, with the firework particle population at large providing a solid ground for discrimination from GSR. Wind dispersal was found to decrease the particle population and subsequently, the latter's discriminatory power. Some particles, if treated individually were found to be indistinguishable from GSR. Findings also include residues which may mimic strontium based GSR as well as GSR which may be mixed with that from previous firings. The continuous changes made to primer and propellant compositions by manufacturers also call for greater consideration when classifying particles as originating from pyrotechnic devices. Furthermore, authorities such as police forces should be made more aware about the incidence of such particle transfer in firework related periods.

The Station Nightclub Fire - An Analysis of Witness Statements

Pyrotechnic devices activated in a small nightclub ignited a fire that killed 100 people and injured at least 200 others in February, 2003. The National Fire Protection Association (NFPA) and the National Research Council of Canada (NRCC) undertook a research project to study the behavior of building occupants in this incident as they evacuated the building. The analysis was based on an examination of witness statements collected by various police agencies after the fire. Statements were available from 355 survivors present in the building at the time of the fire. This paper summarizes their reactions and responses, exit route choices and travel paths.

The Station Nightclub Fire - An Analysis of Witness Statements

Pyrotechnic devices activated in a small nightclub ignited a fire that killed 100 people and injured at least 200 others in February, 2003. The National Fire Protection Association (NFPA) and the National Research Council of Canada (NRCC) undertook a research project to study the behavior of building occupants in this incident as they evacuated the building. The analysis was based on an examination of witness statements collected by various police agencies after the fire. Statements were available from 355 survivors present in the building at the time of the fire. This paper summarizes their reactions and responses, exit route choices and travel paths.

Shock Response Prediction of a Low Altitude Earth Observation Satellite During Launch Vehicle Separation

Several pyrotechnic devices are employed over the course of satellite's missions, generally for the separation of structural subsystems and deployment of appendages. Firing of pyrotechnic devices results in impulsive loads characterized by high peak acceleration and high frequency content which can cause failures of various flight hardware elements and small components. Thus, accurate prediction of acceleration level in various components of spacecraft due to pyrotechnic devices is important. In this paper, two methods for pyroshock prediction, an empirical model and statistical energy analysis in conjunction with virtual mode synthesis, are applied to predict shock response of a low altitude earth observation satellite during launch vehicle separation. The predicted results are then evaluated through comparison with the shock test results.

Experimental Study on Pyroshock Responses of a Conical Shell

In space engineering, pyroshock (or pyrotechnical shock) environments induced by pyrotechnical devices are severe for space hardware, especially the inner electrical components. Thus pyroshock responses need to be well considered in the design and manufacture of a space structure or system. Because of the lack of efficient analytical technique, laboratory tests are of importance at present. This paper experimentally studies the pyroshock responses of a conical aeroshell. Two experiments were performed by ignitions of true pyrotechnical devices. A number of acceleration histories were measured and the corresponding shock response spectrums (SRSs) were analyzed. The results show that the responses, not only in time domain but also in frequency domain, have significant decaying characteristics along the axial distance from the pyroshock sources. The quantitative results provide us a good understanding of local environments for design of the components and the corresponding installations.

Design and Experimental Research of a Shape Memory Alloy Space Release Device with Segmented Nut Form

Spacecrafts need release devices to realize space release function. The traditional pyrotechnic release devices have the drawbacks of high shock and contamination. NASA-developed release device with shape memory alloy(SMA) column has the disadvantages of long release lasting time and unavailability of reset. Based on the research of NASA,a design scheme of SMA space release device with segemented nut form is proposed,and the corresponding design method is developed for the core part of the release device,i.e. driving unit. Finially,the prototype is developed and the function and synchrony tests are carried out. The results show that under 6V DC power supply,the device can finish release function within 0.3 s,and when two devices are used,they are almost release at the same time. The difference of release lasting time for two devices is less than 0.04 s. The space release device developed has the advantages of small size,short release lasting time,easy reset and synchronization,thus having great potential in engineering application.

Modification and characterization of (energetic) nanomaterials

Nanomaterials are a topic of increased interest, since they have properties which differ from their macroscopic counterparts. Many applications nowadays take advantage of the new functionalities which natural and manufactured nanoparticles possess. Based on these developments, also the research on energetic nanomaterials is receiving more and more attention. Apart from the synthesis of energetic nanomaterials, another area of interest is the coating of energetic (nano)powders, in order to be able to modify their properties or to add new functionalities to these particles. (Modified) energetic materials find applications in explosives, gun and rocket propellants and pyrotechnic devices. The modified energetic materials are expected to yield enhanced properties, e.g. a lower vulnerability towards shock initiation, enhanced blast, enhanced shelf-life and environmentally friendly replacements of currently used materials. An experimental set-up for the coating of existing powders has been designed and constructed. The experimental technique is based on a special plasma application which, contrary to more general plasmas, can be operated at relatively low temperatures and ambient pressure. This allows the handling of heat-sensitive materials, which would otherwise readily decompose or react at higher temperatures. The facility used for the coating of energetic powders in the lower micron range is based on a fluidized bed reactor in which the powder circulates. In this paper, the experimental technique will be described and experimental results will be shown of CuO powders that have been coated with a very thin, nanoscale deposit of a SiO-containing layer.

Phosphorus-based nanothermites: A new generation of energetic materials

Thermites are energetic materials that are classically made of a transition metal oxide mixed with a reducing metal. Contrary to explosives, thermites do not detonate because their combustion is relatively slow and their reaction by-products are often solid or liquid. The use of nanoparticles to prepare superthermites is very promising. The dramatic changes observed in their reactivity were reported by numerous recent papers dealing with the use of aluminium as fuel. Red phosphorus is widely used in pyrotechnic devices. Highly explosive compositions are classically obtained by mixing this substance with strong oxidizers such as oxygenated potassium salts (chlorate, nitrate). But to our knowledge, the idea to prepare P-nanothermites with metallic oxide nanoparticles was never reported before. In order to illustrate this new concept of energetic formulations, P-nanothermites were prepared from nickel oxide (NiO), iron oxide (Fe 2O 3), and copper oxide (CuO) nanopowders. The reactivity of these compositions was studied by thermogravimetric analysis, impact and friction tests, electrostatic discharge and high-speed cinematography. P-nanothermites are very insensitive to thermal and impact stress. Their combustion rates strongly depend on the nature of the oxide (NiO <Fe 2O 3⪡CuO). The SEM observation of the microstructure of the residues produced by the combustion clearly indicates that they were formed by the solidification of molten phases. In other words, the energy released by the combustion of P-nanothermites provokes the melting of the reaction products. The temperatures reached are thus high enough to cause the gasification of phosphoric anhydride produced by the combustion. For this reason, P-nanothermites can be considered gas-generating materials.