DELAYED GUIDANCE FOR ROLLING MISSILES WITII BOOST-SUSTAIN PROPULSION MOTOR | ||||
| International Conference on Aerospace Sciences and Aviation Technology | ||||
| Article 7, Volume 6, ASAT CONFERENCE 2 — 4 May 1995, CAIRO, May 1995, Page 75-87 PDF (1.84 MB) | ||||
| Document Type: Original Article | ||||
| DOI: 10.21608/asat.1995.25471 | ||||
 View on SCiNiTO | ||||
| Authors | ||||
| M. Medgawy1; Mohsen S. Aly2; S. Ghoniemy3 | ||||
| 1Graduate student, Algerian Military 'Technical College, Algeria. | ||||
| 2instruc-tor, Guidance Department, Military Technical College, Cairo. | ||||
| 3Professor, Mili-tary Technical College, Cairo, Egypt. | ||||
| Abstract | ||||
| The results of a 6-Degrees-of-freedom (6DOF) simulation model of a short-range homing missile are presented. The missile considered is roll-rate stabilized and is guided by proportional navigation law. The missile motor is of boost-sustain type. In this paper, the effect of the boost acceleration is analyzed. During the boost phase, it is found that the presence of a relatively large incidence angle increases the demanded missile maneuver to correct for the input errors to the guidance loop. Mathematical analysis shows that this large incidence angles couples a considerable amount of the boost acceleration to the lateral plane. This can be regarded as an input acceleration bias that increases the effort done by the guidance loop. In the sustain phase; however, the sustainer acceleration is low and this effect can be neglected. To reduce the demanded effort from the guidance loop, a • delayed guidance scheme is proposed. In this scheme, the guidance and control of the missile starts few moments after launch. The results obtained via numerical computations are in complete agreement with the theoretically obtained conclusions. | ||||
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