NASA, Johnson Space Center, BE13, Houston, TX

16 -- PROCUREMENT OF A MILITARY TYPE INERTIAL NAVIGATION SYSTEM WITH AN EMBEDDED GPS, AND ASSOCIATED ENGINEERING TEST SUPPORT. SOL 9BE113516P DUE 040595 POC ANTONIO HUMPHREYS, Tel:713-483-8518 Contracting Officer:ANN SULLIVAN, Tel:713-483-1863 The test article to be purchased is a small, high performance military ai rcraft type inertial navigation system with an embedded Global Positionin g System (GPS). The system shall have all attitude worldwide aircraft na vigation and heading reference outputs simultaneously for GPS P-code/Y-co de or C/A code, pure inertial, and blended GPS/Inertial. The system shal l be capable of Gyrocompass alignment on the ground, or inflight. It is intended that this system be used at NASA/JSC as an engineering test/eval uation article in a variety of laboratory and aircraft environments. The system shall contain provisions for customer unlimited access to memory locations especially related to the coupling/aiding functions between the GPS receiver/processor and the inertial system. --The embedded GPS receiver in an inertial navigation system (EGI) shall be packaged in one line replaceable unit, designed to meet military perform ance and environmental requirements. All attitude worldwide navigation, and heading reference outputs shall be provided simultaneously for P-code /Y-code or C/A code GPS only; pure inertial and blended GPS/INS. The EGI shall contain built-in test equipment with a goal of 98 percent minimum probability of fault detection and fault isolation. False failure detect ion shall be less than one percent of all failure detections. The EGI sh all be modifiable to allow continuous attitude operation during a typical Shuttle mission from prelaunch alignment thru a runway landing. The EGI shall require no periodic calibration to meet the accuracy requirements herein for a minimum of 10,000 operating hours. Honeywell shall provide engineering support for the JSC testing of the EGI over a period not to e xceed 100 days after delivery of the hardware. Performance Requirements: a) RMS alignment accuracy following an automatic static Gyro compass ali gnment at any attitude. _______Pitch, roll, azimuth -0.05 degrees Characteristics: GPS System: The system shall contain as a minimum a single dual redundant 15 53 multiplex data bus interface, a memory loader interface, a data loader interface, an RS422 instrumentation port, and a precision time and time interval (PTTI) interface. The system shall require only passive cooling over the temperature range of -54C to +71C to the parameter compensation process and internal aiding. --One each. --NASA Johnson Space Center. --Three months after award of contract. --See Note 22. --The test article to be purchased is a Honeywell military type inertial na vigation system with an embedded GPS. In addition, there are provisions for a very limited quantity/amount of engineering test support. The test article is an advanced (Block II) version of a system which NASA/JSC pur chased from Honeywell under contract NAS 9-18780. This system (Honeywell H7G4G Serial No. 315) has been used as a test article to evaluate hybrid /blended GPS/INS performance characteristics; however, it was essentially an engineering prototype system. The newer (Block II) system contains m any new and unique features which will facilitate NASA/JSC Engineering's goal of evaluating the synergism of hybrid/blended GPS/inertial navigatio n systems. The system shall contain ring laser gyros, 6 channel minimum GPS receiver/processor, extensive memory, and extensive I/O capability. (0067)

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