Real Time Data Acquisitions of Missile Position Using Spacecraft Passive (Infrared) Sensor and GPS Integrated Angular Rate Positioning System

Akira Murakami

Abstract:	An idea is proposed to measure the missile position using spacecraft passive infrared (IR) sensor (SPASS) and GPS angular rate positioning system (GARS)[ I][Figures 1 - 21. Here the range is determined using the sensor spacecraft (SC) velocity and range trigonometric sign equation [2] as follows: l Range (LOSl) = (SIN(I32) x BL) /(SIN(TA)), in kilometers where: LOS1 = a range to a missile position on the first line of sight-l , in kilometers SIN (B2) = sine of triangle base angle B2, in Degrees BL = a triangle base Line of SC velocity, in kilometers SIN (TA) = Sine of triangle top angle TA, in degrees The range provides 3- dimensional (3-D) positions of missile. The derivation of the above range equation is described using the forward way process [Figures 3- 4 and g-101. The feasibility of this idea is hypothetically tested by the reverse way process figures 5-81 using the data from missiles launched in the past.
Published in:	Proceedings of the 1996 National Technical Meeting of The Institute of Navigation January 22 - 24, 1996 Loews Santa Monica Hotel Santa Monica, CA
Pages:	475 - 491
Cite this article:	Murakami, Akira, "Real Time Data Acquisitions of Missile Position Using Spacecraft Passive (Infrared) Sensor and GPS Integrated Angular Rate Positioning System," Proceedings of the 1996 National Technical Meeting of The Institute of Navigation, Santa Monica, CA, January 1996, pp. 475-491.
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