Vehicle’s Dynamics Performance in Response to Accelerometer Positioning | ||||
| International Conference on Aerospace Sciences and Aviation Technology | ||||
| Article 60, Volume 15, AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 15 – May 28 - 30, 2013, May 2013, Page 1-11 PDF (693.77 K) | ||||
| Document Type: Original Article | ||||
| DOI: 10.21608/asat.2013.22133 | ||||
 View on SCiNiTO | ||||
| Authors | ||||
| M. S. Mohamed1; A. A. El-Ramlawy1; G. A. El-Sheikh2; A. M. Bayoumy1 | ||||
| 1Egyptian Armed Forces. | ||||
| 2Prof. Pyramids Higher Institute for Engineering and Technology. | ||||
| Abstract | ||||
| In an airplane of tail-controlled aerodynamic missiles, when the control surfaces are deflected to provide an elevator angle with trailing edge upward to produce a positive normal acceleration, this creates a downward increment of force on the tail. The result is that the missile c.g. may drop momentarily during the pitch-up, so the normal acceleration may briefly become negative before it builds up positively. If the accelerometer is located at missile c.g., it will sense a negative normal acceleration and the senses a positive normal acceleration in a manner similar to non-minimum phase system. If the accelerometer is located ahead of the c.g., the normal acceleration measured will change and this depends on the pitch acceleration about the c.g., so only a positive normal acceleration may be sensed. This paper represents the physical explanation for the non-minimum phase behavior in tailcontrolled aerodynamic missiles, its source, disadvantages and solution for this problem and finally the optimum location for accelerometer in the vehicle. | ||||
| Keywords | ||||
| Missile flight control; accelerometers; non-minimum phase system | ||||
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