NASA/George C. Marshall Space Flight Center, Procurement Office, Marshall Space Flight Center, AL 35812

58 -- GLOBAL POSITIONING SYSTEM (GPS)RADIO FREQUENCY (RF)SATELLITE SIGNAL SIMULATOR (SSS)SYSTEM SOL 8-1-9-EB-C2859 POC Randy M. Sacks, Contract Specialist, Phone (256) 544-0334, Fax (256) 544-4400, Email randy.sacks@msfc.nasa.gov -- George E. Pendley, Contracting Officer, Phone (256) 544-2949, Fax (256) 544-9080, Email george.pendley@msfc.nasa.gov WEB: Click here for the latest information about this notice, http://nais.nasa.gov/EPS/MSFC/date.html#8-1-9-EB-C2859. E-MAIL: Randy M. Sacks, randy.sacks@msfc.nasa.gov. NASA/MSFC plans to issue a letter Request for Offer (RFO) for a Dual-Frequency P/Y-Code GPS Simulator System with two RF Outputs, with option for Four-Antenna Single-Frequency Attitude-Determination Test Applications. Requirements for this system are as follows: (1) Shall be 100% Software-, Hardware- and Interface-compatible with NASA/MSFC's existing GSSI GPS Simulator System, such that integration with this existing system will allow for testing of single-vehicle, four-antenna, dual-frequency P/Y-Code, Attitude determining test applications. (2) Shall correctly model the effects of Vehicle Position, Vehicle Velocity and Vehicle Attitude on the arriving GPS Satellite Signals. (3) Shall be capable of simulating host-vehicle velocities commensurate with Low Earth Orbits, i.e., capable of generating Doppler shifts caused by relative motion in excess of 120,000 meters/second, minimum, with maximum acceleration of 3,600 m/sec2, minimum, and maximum jerk of 5000 m/sec3, minimum. (4) Signal Accuracy shall be (or better than) 10.1 meter for Pseudoranges, 11 mm/sec for Pseudorange Rates, 15 mm for Delta-Pseudoranges, 10.5 m Code Phase Interchannel Bias, and 10.265 mm Carrier Phase Interchannel Bias. (5) Two (32-channel) Simulator Hardware Chasses are required, each with the following characteristics: (a) Shall be physically compatible with U.S. Standard Rack-Mount Cabinets (b) Shall be electrically switchable between either 115 VAC/60 Hz (5 Amps Max per chassis), or 230 VAC/50 Hz (2.5 amps Max/Chassis). (c) Shall posses a minimum of two separate 'standard' RF Outputs, for Dual-Vehicle, Single-Freqency Simulations. RF Signal Output Power Levels shall be nominally -130 dBm for L1 C/A Code, -133 dBm for L1 P-Code, and -136 dBm for L2 P-Code, with a dynamic range of +20/-36 dB Offset, minimum, a resolution of 0.1 dB, minimum, and an accuracy of 10.7 dB RSS. The output signals shall have spurs no larger than -30 dBc, harmonics no larger than -40 dBc, and a phase noise no larger than 0.02 radians RMS, with a 1 Hz -- 10 kHz offset. (d) Shall have a 'calibration output port' for each 'standard output port', with signal levels at least 50 dB above the nominal 'standard' output signal level. (e) Shall have its own suitable internal Temperature-Stabilized Oscillator (or better), with a frequency stability of 15E-10 per day, maximum, after a 24-hour warm-up period. (6) Two Simulator Control Workstations (computers) are required, such that each Simulator Hardware chassis can be controlled independently, in different physical locations. That is, it is required that the system be able to be split into two separate and independent GPS Simulator Systems, with each system limited to 32 hardware channels. (7) Each Simulator Control Workstation shall come with a minimum of two removable SCSI Hard Drives, each with a minimum capacity of 9 GB, for classified data storage. Thus, a minimum of four 9 GB Hard Disk Drives are required. (8) The Simulator Control Computers shall posses the ability to receive external vehicle trajectory data (Time, Position, Velocity, and Attitude, at 10 Hz or faster) in near-real-time, via an IEEE-488 Data Interface, for closed-loop, real-time Hardware-In-The-Loop Simulations. The data latency from the time the data is received by the Simulator Control Computer until the RF output responds shall be no more than 30 mSec. (9) The Simulator System shall have the capability to generate actual classified Selective Availability/Anti-Spoofing (SA/A-S) Signal Characteristics. (10) The Simulator System shall accept and use User-Specified Antenna Pattern Files, for both Amplitude and Phase, for use with dynamic GPS Signal Strength Computations. (11) The Simulator System shall have the ability to generate RF Interference signals, with the following characteristics: (a) A minimum of 6 interference-signal-generator-channels are required (in addition to the 64 GPS-Signal-Generator-Channels) (b) The RF Interference Generator shall be automatically controlled by the GPS Simulator Control Computer, to determine and set Jammer Output Power Level based upon simulated Jammer Location and current GPS Receiver Host Vehicle Location. (c) Maximum Output Power: Not less than -35 dBm (d) Minimum Output Power: Not Greater than -110 dBm (e) Capable of the following Output Signal Types: i) Continuous Wave (CW) Sinusoid, at either 1575.42 MHz or 1227.6 MHz, each 1 20.46 MHz. ii) Swept CW, per frequencies above, maximum sweep rate not less than 10 kHz. iii) Frequency Modulated, per frequencies above, maximum FM Deviation range not less than 1 100 kHz, maximum FM rate not less than 10 kHz. iv) Amplitude Modulated, per frequencies above, Modulation Percentage not tighter than 10% to 90%, maximum AM Rate not less than 10 kHz. v) Pulse Modulated, Pulse Width Range not narrower than 1ms to 10 ms, Pulse Repetition Rate range not narrower than 0.1 to 10 ms, with the option to sweep both Pulse Width and Pulse Repetition Rate. vi) Noise Interference, user-selectable bandwidths of 0.1, 2, 10, 20 MHz, and RF Output Power Level not narrower than -45 dBm to -115dBm. (12) System shall include a Maintenance Agreement, lasting 2 years from the date of delivery. This agreement includes telephone and e-mail technical support, hardware repairs and replacement, calibration assistance, periodic Hardware, Firmware, Software, and Documentation upgrades/updates, as necessary. (13) The System shall be supplied with a user calibration manual, documenting the specific steps required by the user to fully calibrate the Simulator System signal characteristics. (14) The entire system being procured herein shall be user-configurable to support the following configurations: (a) One Vehicle with Four Antennas, Single-Frequency Attitude Determination. 16 Single-Frequency Satellites per antenna. (b) One Vehicle with Two Antennas, Dual-Frequency Position Determination. 16 Dual-Frequency Satellites per antenna. (c) Two separate Vehicles, each with one Dual-Frequency Antenna Position Determination. 16 Dual-Frequency Satellites per antenna. (d) Two separate Vehicles, each with two Single-Frequency Antennas Position Determination. 16 Single-Frequency Satellites per antenna. (e) Four Separate Vehicles, each with one Single-Frequency Antenna Position Determination. 16 Single-Frequency Satellites per antenna. (15) Upon combination with NASA/MSFC's existing GPS RF SSS System, the system being procured herein shall be user-configurable to support the following configurations: (a) One Vehicle with Four Antennas, Dual-Frequency Attitude Determination. 10 Dual-Frequency Satellites per antenna. (b) Two Vehicles with Two Antennas each, Dual-Frequency Position Determination. 10 Dual-Frequency Satellites per antenna. NASA/MSFC intends to purchase the items from Global Simulation Systems Incorporated pursuant to FAR 6.302-1. The original procurement of NASA/MSFC's GPS RF SSS System was under a full and open competition. Under this open competition, Northern Telecom, Inc. (Nortel) was selected to provide MSFC's GPS RF SSS System. Since that time, Nortel has changed their name to Global Simulation Systems, Inc.(GSSI). The equipment being sought herein must be fully hardware- and software-compatible with MSFC's existing GSSI GPS RF SSS System, such that the entire test system (old and new hardware) may be electronically interfaced together to provide for four-antenna dual-frequency attitude-determination test capability for spacebourne applications and for four-vehicle, dual-frequency, single-antenna-per-vehicle test capability (formation flying/Relative GPS) for spacebourne applications. The Government intends to acquire a commercial item using FAR Part 12. An Ombudsman has been appointed. See Internet Note "B". Interested firms have 15 days from the publication of this synopsis to submit in writing to the identified point of contact, their qualifications/capabilities. Such qualifications/capabilities will be used solely for the purpose of determining whether or not to conduct this procurement on a competitive basis. Responses received after the 15 days or without the required information will be considered nonresponsive to the synopsis and will not be considered. A determination by the Government to not compete this proposed effort on a full and open competitive basis, based upon responses to this notice is solely within the discretion of the Government. Firm date for receipt of offers will be stated in the letter RFO. All qualified responsible sources may submit an offer which shall be considered by the agency. Any referenced notes can be viewed at the following URL: http://genesis.gsfc.nasa.gov/nasanote.html. Posted 04/15/99 (D-SN320832). (0105)

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