Study on Enhancement of Missile Turbojet Engine’s Start Control Discipline

doi:10.3969/j.issn.1000-1093.2012.03.011

Acta Armamentarii ›› 2012, Vol. 33 ›› Issue (3): 313-317.doi: 10.3969/j.issn.1000-1093.2012.03.011

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Study on Enhancement of Missile Turbojet Engine’s Start Control Discipline

YANG Xin-yi¹, WANG Yong-hua¹, DONG Ke-hai¹, ZHOU Yuan², LI Guan-jun³

(1. Department of Aircraft Engineering，Naval Aeronautical and Astronautical University，Yantai 264001，Shandong，China；2. Department of Strategic Missile Engineering，Naval Aeronautical and Astronautical University，Yantai 264001，Shandong，China；3. Naval East China Sea Fleet 19 Division，Ningbo 315122，Zhejiang，China)

Received:2011-03-28 Revised:2011-03-28 Online:2014-03-04
Contact: YANG Xin-yi E-mail:jimyang2008@163.com

Abstract

Abstract: The missile turbojet engine’s start tests are performed on ground test system, major engine parameters and some performance parameters such as start time and surge margin are obtained. Engine’s fuel supply curve is redesigned. It is divided into three segments: fill, ignition and acceleration segment. Suitable range on fill segment and ignition segment are determined from ground tests. The results show that acceleration segment affects engine’s start performance the most. Improving fuel supply of acceleration segment will shorten start time, at the same time, reduce surge margin.

Key words: experimental technology of aerocraft, turbojet engine, start, control discipline

CLC Number:

V235.1

YANG Xin-yi, WANG Yong-hua, DONG Ke-hai, ZHOU Yuan, LI Guan-jun. Study on Enhancement of Missile Turbojet Engine’s Start Control Discipline[J]. Acta Armamentarii, 2012, 33(3): 313-317.

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Study on Enhancement of Missile Turbojet Engine’s Start Control Discipline

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