US Army ARDEC, AMSTA-AR-PC, Picatinny Arsenal, New Jersey 07806-5000

12 -- INERTIAL NAVIGATION SYSTEM (INS) SOL DAAE30-99-R-0203 DUE 010799 POC Patricia A. Regelski, Contracting Officer, 973-724-3832 WEB: US ARMY TACOM-ARDEC Procurement Network, http://procnet.pica.army.mil/cbd/SRCSgt/120819980/120819980.htm. E-MAIL: Robert McMinn, rmcminn@pica.army.mil. The US Army TACOM-ARDEC intends to award a sole source contract to Kearfott Guidance and Navigation Systems, Totowa, New Jersey for the purchase of two Inertial Navigation Systems (INS) for use with the 155mm Automated Howitzer (155AH). The INS shall be capable of interfacing with the 155AH without modification of the 155AH in any manner. The two units shall be direct replacements for the INS currently used in the 155AH Digital Fire Control System (DFCS). That is the two INS shall meet the same mechanical, electrical, and communication interface requirements, as well as functional, operational, and performance requirements of the current 155AH INS. The INS shall consist of a Vehicle Reference Unit, Vehicle Motion Sensor, and associated interconnect cable. Overall characteristics for the INS are: Position and attitude accuracy's stated herein shall be met for missions up to 24 hours long and distance traveled up to 100 Km at any latitude within the range of 84o N to 80o S, unless specified otherwise. The INS shall make use of Global Positioning System (GPS) signals as an aid to improve the inertial accuracy. The INS shall interface with standard U.S. Army Precision Lightweight Global Positioning System Receiver (PLGR). It shall also utilize Vehicle Motion Sensor aiding to improve survey accuracy as well as Zero Velocity Updates (ZUPTs) when the vehicle is stopped. The INS GPS aided accuracy requirements shall be met when GPS aiding is enabled and signals from four GPS satellites having characteristics suitable for obtaining GPS position solutions, at a rate of one per minute or higher, with accuracy of 10 meters CEP, horizontal, and 10 meters PE, vertical, or better, are incident at the GPS antenna. The position accuracy requirements specified herein apply at any time after position was initialized, INS completed alignment, and the weapon system has been stopped for 30 seconds or longer. The INS horizontal position error shall not exceed 10.0 meters CEP. No more than 1.0 percent of the radial errors may exceed 26 meters. The INS altitude error shall not exceed 10.0 meters PE. No more than 1.0 percent of the absolute values of altitude errors may exceed 39 meters. The INS shall accept and indicate position in Universal Transverse Mercator (UTM) coordinates with a resolution of 1 meter in Easting, Northing, and Altitude, At any latitude within the range of 65o S or 65o N, grid or geodetic azimuth error for the INS shall not exceed 1.0 mils RMS and no more than 1.0 percent of the absolute values of azimuth errors shall exceed 2.6 mils. The INS cannon Quadrant Elevation (QE or pitch) error shall not exceed 0.5 mil RMS, and no more than 1.0 percent of the absolute value of QE or pitch errors shall exceed 1.3 mils. The INS cannon cant (or roll) error shall not exceed 0.5 mil RMS and no more than 1.0 percent of the absolute value of cant or roll errors shall exceed 1.3 mils. The INS shall accept and indicate azimuth referenced to grid north with a resolution of 0.1 mil, and a QE and cant referenced to the local gravity vector, each with a resolution of 0.1 mil. The INS shall interface with the 155AH DFCS in accordance with EIA Standard RS- 232. The DFCS shall be the bus master which initiated communication with the INS (slave). The INS shall not initiate a message without a request from the DFCS. The INS shall operate from a power source functioning at the worst case limits of MIL-STD-1277A, excepting initial engagement surges and cranking. The INS shall remain on when the steady power supply voltage is +16.5 to 32.0 Volts dc. INS power draw shall not exceed 48 Watts. The VRU shall be located on the Assistant Gunner side trunion of the 155AH in the position formally occupied by the M172 Telescope and Quadrant Mount. The VMS shall be located on the inside portion of the Assistant Gunner side road wheel assembly. See Numbered Notes 22 and 26. Posted 12/08/98 (D-SN278316). (0342)

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