Design Optimization of the HEMi Booster

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Authors
  1. Lestage, R.
  2. Wong, F.C.
  3. Harris, P.
  4. Lesage, F.
  5. Farinaccio, R.
  6. Lauzon, M.
Corporate Authors
Defence R&D Canada - Valcartier, Valcartier QUE (CAN)
Abstract
The objective of the design work for the HEMi booster was to determine the missile configuration that provides the lightest system while achieving performance and payload objectives. The equations governing the kinematic performance of the missile were integrated into an aerodynamic prediction tool, a structural design module and a solid rocket motor performance model in order to perform an integrated analysis of the performance of the HEMi booster in its baseline configuration. Following the results obtained from the baseline configuration, several parametric analyses were performed to investigate design sensitivity and to develop a method of improving the performance of the design. Results of variations in mass, radius, length, motor chamber pressure and nozzle exit radius are presented. Analysis of the design space using parametric analysis showed that simultaneously achieving the length, mass and speed (lethality) requirements is challenging. To drive the design to a concept that meets these requirements, an optimization algorithm was used to adjust independent variables while keeping dependent values like velocity constant. This restricted the concept investigation to concepts that met the requirements. The integrated analysis tool indicated that the current HEMi configuration cannot achieve the initial specification of total missile length 1.25 m, mass 23.0 kg and velocity Mach 7 in 0.4 s. However, it is possible to reach Mach 7.0 if both the length and the mass of the

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Keywords
optimisation;analysis;aerodynamics;simulation;HEMi (High Energy Missile)
Report Number
DRDC-VALCARTIER-TM-2006-675 — Technical Memorandum
Date of publication
01 Mar 2007
Number of Pages
51
DSTKIM No
CA029141
CANDIS No
527358
Format(s):
CD ROM

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