Design Methodology for a Central Injection Type Supersonic Air Ejector and Diffuser System for Altitude Simulation

Date

2019-08-22

Author

aydoğdu, ataman
sümer, bülent
yazıcı, bora
Ulaş, Abdullah

Metadata

Show full item record

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Item Usage Stats

54
views

0
downloads

Altitude simulation is an important concept in tactical missile systems, especially in terms of aerothermal ground testing and high-speed air breathing engine free-jet testing. Those tests of the tactical missile systems at supersonic speeds need ground test facility, which simulates Mach Number, Total Pressure and Total Temperature of the flow. Testing facilities of this type have free jet nozzle which opens to a test chamber where the test article is mounted, test chamber and a vacuum system. The main objective of conducting the high altitude testing is to test the article under the conditions of free-jet nozzle full-flow without any flow separation. Therefore, High Altitude Test System should create this sufficient low-pressure environment corresponding to the flight situation. One of the mostly used methods to reduce the static pressure in the test chamber to a value lower than the ambient pressure is employing Ejector Diffuser Systems. The Ejector Diffuser Systems are widely used to create static pressure in the test chamber lower than test facility ambient pressure. In the present study, performance of an ejector diffuser system have been investigated together with the free jet nozzle and test chamber by using numerical and experimental methods. Ejector system and test section design is performed separately by ‘Design by Analysis’ method based on CFD analysis and optimization algorithms. Then, two coupled systems are studied together. In order to validate the design procedure, a combined numerical analysis of the High Altitude Test System is performed in three different operating conditions in which the numerical solutions are converged.

URI

https://hdl.handle.net/11511/69521

DOI

https://doi.org/10.2514/6.2019-4355

Collections

Department of Mechanical Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

Design of a test setup for altitude simulation Aydoğdu, Ataman; Ulaş, Abdullah; Department of Mechanical Engineering (2019) Altitude simulation testing is an important concept in missile systems, especially in terms of aerothermal ground testing and high speed air breathing engine free-jet testing. Those tests of the missile systems at supersonic speeds need High Altitude Test System (HATS) which simulates Mach number, total pressure and total temperature of the flow on the test article mounted in the test chamber by using free-jet nozzle. To start the free-jet nozzle operation which simulates high altitude conditions, test cham...
GPS based altitude control of an unmanned air vehicle using digital terrain elevation data Ataç, Selçuk; Platin, Bülent Emre; Department of Mechanical Engineering (2006) In this thesis, an unmanned air vehicle (UAV) is used to develop a prototype base test platform for flight testing of new control algorithms and avionics for advanced UAV system development applications. A control system that holds the UAV at a fixed altitude above the ground is designed and flight tested. Only the longitudinal motion of the UAV is considered during the controller design, hence its lateral motions are controlled manually by a remote control unit from the ground. UAV’s altitude with respect ...
Nonlinear modeling and flight control system design of an unmanned aerial vehicle Karakaş, Deniz; Balkan, Raif Tuna; Department of Mechanical Engineering (2007) The nonlinear simulation model of an unmanned aerial vehicle (UAV) in MATLAB®/Simulink® environment is developed by taking into consideration all the possible major system components such as actuators, gravity, engine, atmosphere, wind-turbulence models, as well as the aerodynamics components in the 6 DOF equations of motion. Trim and linearization of the developed nonlinear model are accomplished and various related analyses are carried out. The model is validated by comparing with a similar UAV data in te...
Towards interoperable and composable trajectory simulations: an ontology-based approach Durak, U.; Oğuztüzün, Mehmet Halit S.; Algin, C. Koksal; Ozdikis, O. (Informa UK Limited, 2011-08-01) Trajectory simulation is a software module that computes the flight path and flight parameters of munitions. It is used throughout the engineering process, including simulations for studying the design trade-offs, to mission simulations for defended area analysis. In this wide application domain, reuse has always been one of the challenges of the trajectory simulation community. We apply an ontology-based simulation development methodology to fulfil the functional requirements of a trajectory simulation whi...
Automatic Landing Flare Control Design by Model-Following Control and Flight Test on X-Plane Flight Simulator Cetin, Ender; Kutay, Ali Türker (2016-07-20) The aim of this study is to design a landing control system and test it on X-Plane flight simulator. Model-Following control and H-Infinity output feedback control methods are used to design the controller. In the flare part of the automatic landing system, it is desired to reduce the rate of descent in order to make aircraft touch down softly. This is accomplished by exponential decay trajectory. The trajectory which is drawn by the referenced model is followed by the linearized aircraft model. The error b...

Citation Formats

a. aydoğdu, b. sümer, b. yazıcı, and A. Ulaş, “Design Methodology for a Central Injection Type Supersonic Air Ejector and Diffuser System for Altitude Simulation,” 2019, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/69521.