A High G, MEMS Based, Deeply Integrated, INS/GPS, Guidance, Navigation and Control Flight Management Unit

Abstract

Integrated Guidance Systems LLC (IGS LLC), a joint venture between Honeywell and Rockwell Collins, has developed the next generation, Deeply Integrated (DI) guidance, navigation and control product which will meet the emerging demands of military applications. The guidance, navigation and control Flight Management Unit (FMU) is based on Selective Availability Anti-Spoof Module (SAASM) and Micro Electromechanical System (MEMS) sensor technology and ishoused in a small, light weight, low power package. In addition to meeting the demands of the military's gun-hardened guided projectile and missile applications, the FMU has applicability in soldier personal navigation systems and military/commercial attitude, heading and reference systems (AHRS). When coupled with Honeywell's second generation C++ based Embedded Computer Toolbox and Operating System (ECTOS™ IIc), the FMU can be utilized easily and effectively for rapid prototyping demonstration (including customer generated guidance and control software), as well as full production systems. Utilizing the latest processor technology, the FMU has been designed to accommodate the next generation INS/GPS Ultra Tightly Coupled (UTC) algorithms. The UTC algorithms, together with the embedded hardware anti-jam electronics, enables the FMU to perform in the otherwise potentially disabling environment of today's battlefield. The FMU has been tested to 20,000 G's (battery backed state), successfully demonstrating the hardware components survive and perform after exposure to the high G environment.This paper presents an overview of the FMU and ECTOS™ IIc software. The hardware architecture and technical specifications of the FMU will be presented, along with a more detailed look at its high G and anti-jam capability. Performance will be reviewed as well as the IGS LLC's approach to providing a deterministic IEEE 1394b bus protocol. Finally, the software architecture, capability, and customer usability / programmability features of ECTOS™ IIc will be described.

Performance Comparison of Deep Integration and Tight Coupling

“…In (9) and (11) the value of T is the predetection integration interval used to generated the correlator outputs in (8), which is 20 ms in this work. An earlyto-late correlator spacing of one chip is assumed.…”

“…The GPS signals are generated at the correlator level for the Monte Carlo simulations. The correlator outputs are then used in (8) and (10) to produce pseudorange and pseudorangerate measurements.…”

“…The correlator outputs in (8) and (10) are generated according to (12) for the Monte Carlo simulations [27].…”

Performance analysis of a federated ultra-tight global positioning system/inertial navigation system integration algorithm in high dynamic environments

“…7 The ultra-tight GPS/INS integration methods are proposed to improve the receiver performance in high jamming and high dynamic environments. 8 In the ultra-tightly coupled (UTC) GPS/INS navigation method, the replica code and carrier generation implementation are directly controlled by the integrated navigation filter, which consequently makes tracking loops of GPS receiver achieve a relative adaptability under high dynamic conditions. 9 Ultra-tight GPS/INS integration is the internal coupling of GPS receivers' tracking loops and INS.…”

Sub-Optimality of the Prefilter in Deeply Coupled Integration of GPS and INS

“…Another work using the same design is presented in [9] where a multiple model EKF is used in the prefilter to estimate and mitigate the multipath effect on the GPS receiver signal. A practical implementation of the ultra tightly coupled filter is presented in [10] where a compact flight management unit based on micro electromechanical INS sensors is shown to perform well under high G and high noise conditions. This paper specifically analyzes the Kalman filter based federated design proposed by Abbott and Lillo [4].…”