NASA, Johnson Space Center, BE13, Houston, TX

25 -- MINIATURE COLD GAS THRUSTERS FOR USE ON THE SIMPLIFIED AID FOR EV A RESCUE (SAFER) SYSTEM. SOL 9BE1318519P DUE 042695 POC Contact:YOLANDE HARDEN, Tel:713-483-9953 Contracting Officer:ANN SULLIVAN, Tel:713-483-1863 NASA Lyndon B. Johnson Space Center has a requirement for the fabrication, acceptance testing and delivery of 27 miniature cold gas thrusters for use on the SAFER system developed at NASA/JSC. This set of thrusters wil l be used to upgrade an existing SAFER to flight status and will be flown on STS-76/MIR 03. These units shall be built to identical production dra wings as used for the previous cold gas thrusters delivered under NASA co ntract NAS 9-18881. --The thruster shall be manufactured per the following specifications and p erform at the specified levels and conditions. Thrust: The thrust shall be verified at ambient, such that the vacuum thrust at 230 psia +/- 5 psia with 70 deg F +/- 10 deg F GN2 is .8 +/- .08 lbf. Correlation of ambient and vacuum thrust shall be based on previous development test data. The lsp shall be calculated to be ) 70 Lbf-sec/Lbm. Acceptance test at vacuum is not required. Minimum Stall Pressure: The minimum stall pressure with the coil temperature at 140 deg F +/- 10 deg F and 25 Vdc shall be )325 psig. Internal Leakage: The total leakage of each thruster shall not exceed .1 sccm at 230 psia +/- 10 psia inlet and ( 1 sccm at 65 psia +/- 10 psia inlet GN2 at 140 deg F. The total leakage of each thruster shall not exceed 2 sccm at 230 psia +/- 10 psia inlet and ( 20 sccm at 65 psia +/- 10 psia inlet GN2 at -40 deg F. Leakage caused by a failed o-ring is not considered an ATP failure. The o-ring can be replaced and the test repeated. Power: The valve shall operate on 28 volt +/- 1 volt nominal power supply. The coil resistance be 28 +/- 1.5 ohms at 70 deg F +/- 10 deg F. The thruster shall not be damaged by a maximum voltage of 35 volts. Insulation Resistance: The insulation resistance shall be ) 1 MOhm at 70 deg F +/- deg F. Pull In Voltage: The pull in voltage shall be ( 25 Vdc with 265 psia inlet +/- 10 psia with coil temperature of 140 deg F. Drop Out Voltage: The drop out voltage shall be less than ( 4.5 Vdc with 230 psia +/- 10 psia inlet and the coil at -40 deg F initial temperature. Opening response: The opening response shall be ( 3.5 ms with 230 psia inlet +/- 5 psia with the coil at 140 deg F. Closing response: The closing response shall be ( 3.5 ms with 230 psia +/- 5 psia inlet with the coil at -40 deg F. Cycle Life: The thruster shall be capable of completing a minimum of 20,000 cycles with a 230 psia inlet +/- 10 psia and 140 deg F +/- 10 deg F GN2. A qualification test has already been conducted under the previous contract to verify that the thruster meets specifications at completion of 20,000 cycles. On Time: The thruster shall be capable of completing a total (not continuous) powered on (open) duration of 570 seconds minimum at an inlet pressure of 230 psia +/- 20 psia in a vacuum. The thruster shall be capable of a continuous on time of 240 seconds, with flow at an inlet pressure of 230 psia +/- 20 psia. A qualification test shall be conducted to verify this specification, which may be combined with the test in 3.10. Vacuum heat transfer can be simulated in ambient by using insulation as determined appropriate by analysis. Proof: The minimum proof pressure shall be 1150 PSIA. Burst: The minimum burst pressure shall be 2250 PSIA. A qualifi- cation test shall be performed on a qualification thruster. Weight: The weight shall be less than .05 lbm without the wire leads. Diameter: The diameter shall be less than .6 inches. A chamfer shall be cut on the diameter at the base of the thruster, near the fluid connection, of the following dimension .015 X .015 inches minimum. Total Length (Thrust Axis): The total length along the thrust axis shall not exceed 1.0 inches including the nozzle, excluding the threaded end fitting. --27 units --NASA Lyndon B. Johnson Space Center --Delivery is required by June 23, 1995. --See numbered Note 22. --Moog, Inc. was the sole developer of the miniature cold gas thruster use d on the original SAFER units. No other manufacturere currently has hard ware which satisfy the minimum requirements of this procurement. Moog is the only manufacturer which has qualified for flight the hardware, proces ses and test facilities required for this system. (0089)

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