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Model, Sabot Design and Free-Flight Tests of the DRDC-ISL A1, A2 and A3 Models

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Model, Sabot Design and Free-Flight Tests of the DRDC-ISL A1, A2 and A3 Models Model, Sabot Design and Free-Flight Tests of the DRDC-ISL A1, A2 AND A3 Models A. Dupuis M. Boivin DRDC Valcartier M. Normand MAETEC Defence R&D Canada – Valcartier Technical Memorandum DRDC Valcartier TM 2003-077 July 2003 Copy No:__________ Model, Sabot Design and Free-Flight Tests of the DRDC-ISL A1, A2 and A3 Models A. Dupuis DRDC-Valcartier M. Normand MAETEC M. Boivin DRDC-Valcartier Defence R&D Canada Valcartier Technical Memorandum TM 2003-077 2003-07-22 Author A. Dupuis Approved by E. Fournier Head, Precision Weapons Section Approved for release by E. Fournier Head, Precision Weapons Section Terms of release: The information contained herein is proprietary to Her Majesty and is provided to the recipient on the understanding that it will be used for information and evaluation purposes only. Any commercial use including use for manufacture is prohibited. Release to third parties of this publication or information contained herein is prohibited without the prior written consent of Defence R&D Canada. © Her Majesty the Queen as represented by the Minister of National Defence, 2003 © Sa majesté la reine, représentée par le ministre de la Défense nationale, 2003 Abstract Preliminary free - flight tests were conducted to verify the integrity of sabots and the A1, A2 and A3 DRDC-ISL model configurations launched from a powdered gun in the velocity range of 200 to 1400 m/s. Projectiles of each configuration were fired as well as a series of slugs for charge determination. The propellant charge mass, muzzle velocity, maximum accelerations and drag coefficient were determined for each shot when fired from a 110-mm smooth bore gun and a 105-mm rifled one with and without a high-low pressure chamber adapter. Résumé Des essais préliminaires ont été effectués pour vérifier le bon fonctionnement des concepts de sabots et des modèles RDDC-ISL A1, A2 et A3 tirés d’un canon à poudre dans la gamme de vitesses situées entre 200 et 1400 m/s. Des projectiles de chaque configuration ont été lancés ainsi qu’une série de balles noyaux pour déterminer les chargespropulsives.Onadéterminéachargepropulsive,lesvitessesàlabouchedu canon, les accélérations maxima et les coefficients de traînée pour chaque tir d’un canon de 110 mm à âme lisse et de 105 mm rayé avec ou sans adaptateur de pression haute-basse situé dans la chambre du canon. TM 2003-077 i This page intentionally left blank. ii TM 2003-077 Executive summary Many options are being considered to improve the performance of existing weapons systems. For example, increasing the range of artillery shells beyond the actual range of 40 km and providing them with some maneuverability on the battlefield to enhance the hit probability on selected high threat targets could be of great advantage to the Canadian Forces. The use of novel controls on missiles as, for example, lateral jets, lattices fins and thrust vector control could increase their performance over classical control surfaces. The available information on how such modifications could improve the aerodynamic performance over the classical projectile or missile shapes is rather limited. As part as a joint effort between DRDC and the French German Institute under the auspices of the Franco-Canadian Accord, a project was set up to study the flight dynamic behavior of a very long range artillery shell with wings and of lattice finned controls on a missile body. The objective was to conduct a fundamental study of the aerodynamic phenomena associated to these type types of control surfaces, their maneuverability, and to compare the results with those furnished by other means such as lateral jets, impulse systems and classical planar control surfaces. Various methodologies available to each establishment such as simulations tools to predict the aerodynamics (CFD and semi-empirical/analytical), and experiments (wind tunnel, aeroballistic range and open range tests) would be utilized in a complementary fashion to avoid duplication of effort. This memorandum presents the projectile and sabot designs as well as the preliminary free-flight trials that are required prior to aeroballistic range firings. The intent of these trials was to conduct a charge determination, to verify the model-sabot integrity at launch and the projectile stability of the models so as not to damage the aeroballistic range instrumentation. Projectiles were fired from a 110-mm smooth bore and a 105- mm rifled gun with and without a Hi-Lo adapter. The propellant charge mass, muzzle velocity, maximum acceleration and drag coefficients were determined for each shot. Dupuis, A., Normand, M., Boivin, M,. 2003. Model, Sabot Design and Free-Flight Tests of the DRDC-ISL A1, A2 and A3 Models. TM-2003-077 Defence R&D Canada Valcartier. TM 2003-077 iii Sommaire Plusieurs options sont entrain d’être examinées pour améliorer la performance des systèmes d’armes existants. Par exemple, augmenter la portée d’un obus d’artillerie au-delà des 40 km actuels en leur donnant une certaine manœuvrabilité sur le terrain pour accroître la probabilité de frappe sur certaines cibles menaçantes pourrait représenter un avantage énorme pour les Forces canadiennes. L’utilisation de contrôles novateurs sur des missiles, comme, des jets latéraux, des ailettes en treillis et de contrôle de la poussée vectorielle pourraient augmenter leur performance sur les surfaces de contrôle classiques. L’information disponible pour comprendre comment ces modifications pourraient améliorer la performance aérodynamique sur les projectiles et missiles classiques est très limitée. Dans un effort conjoint entre le RDDC et l’Institut de recherches franco-allemand sous les auspices de l’Accord franco-canadien, un projet a été amorcé pour étudier la dynamique du vol d’obus d’artillerie de très longue portée avec des surfaces portantes et des ailettes en treillis sur un corps de missile. L’objectif était l’étude fondamentale des phénomènes aérodynamiques associés à l’usage de ce type de gouverne, leur pilotage par l’utilisation des connaissances nouvelles acquises et la comparaison des résultats obtenus avec ceux fournis par d’autres moyens conventionnels de pilotage tels que jets latéraux, dispositifs impulsionnels et surfaces portantes classiques. Des méthodologies existantes aux deux centres de recherche comme les outils de prédiction de coefficients aérodynamiques (calculs numériques et semi- empiriques/analytiques) et les moyens expérimentaux (soufflerie, corridor aérobalistique et champs de tirs) ont été utilisés d’une façon complémentaire pour éviter la duplication des travaux. Ce mémorandum présente la conception des sabots et des projectiles ainsi que les essais préliminaires requis avant d’effectuer des essais au corridor aérobalistique. Le but de ces essais était de déterminer la charge propulsive, vérifier l’intégrité du modèle et du sabot lors du lancement et de la stabilité des modèles en vol afin de ne pas endommager l’instrumentation du corridor aérobalistique. Les projectiles ont été tirés d’un canon 110 mm à âme lisse et d’un canon de 105 mm rayé, avec ou sans un adaptateur de pression haute-basse, situé dans la chambre du canon. La charge propulsive, les vitesses à la bouche du canon, les accélérations maxima et les coefficients de traînée ont été déterminés pour chaque tir d’un canon. Dupuis, A., Normand, M., Boivin, M. 2003. Model, Sabot Design and Free-Flight Tests of the DRDC-ISL A1, A2 and A3 Models. TM 2003-077 Defence R&D Canada Valcartier. iv TM 2003-077 Table of contents Abstract/Résumé ............................................................................................................. i Executive summary.......................................................................................................iii Sommaire ...................................................................................................................... iv Table of contents ............................................................................................................ v List of figures ............................................................................................................... vii Acknowledgements ........................................................................................................ x 1. Introduction ........................................................................................................ 1 2. Projectile Configuration ..................................................................................... 2 2.1 Model A1 - Artillery Shell with Wings ............................................................2 2.2 Model A3 - Missile with Grid Fins...................................................................2 2.3 Model A2 - Artillery Shell with Grid Fins........................................................3 3. Experimental Site and Instrumentation.............................................................. 4 3.1 Test Particularities ............................................................................................4 4. Model, Sabot Design and Tests for A1 Model................................................... 6 4.1 Model Design for A1 Configuration.................................................................6 4.2 Sabot Design for A1 Model ..............................................................................7 4.3 Sabot-Model Integrity Trials 1 (Oct. 99) for A1 Model ...................................8 4.3.1 Comments and Discussions ...............................................................10 4.4 Sabot-Model Integrity
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