CS_TVC_Circ_Pump_Qual_Environmental_SOW.docx

Statement of Work for Environmental Qualification Testing of Space Launch System Core Stage Thrust Vector Control Circulation Pump

Scope The supplier shall perform the testing as described in this Statement of Work (SOW) and identified in the applicable Purchase Request.

This Statement of Work defines Space Launch System (SLS) Program delta Qualification Random Vibration and Shock testing on (1) one Boeing 201-025205-1 circulation pump for reuse as flight hardware in the SLS Core Stage (CS) Thrust Vector Control (TVC) hydraulic system.

The circulation pump, shown in Figure 1 below, measures approximately 18” X 9” X 8” and, with hydraulic fluid, weighs approximately 37.5 pounds. Four 0.25” fasteners on a 8.125” X 5.5” hole pattern are used to secure the circulation pump. It provides flow for thermal circulation through the TVC system flow paths to actuators and components. Maximum pressure is limited to 350 PSID by an internal relief valve. Flow per pump is ~2.8 GPM with an input power of 2344W. The circulation pump is a two stage gear pump driven by an AC induction motor with inverter supplied with 28 VDC power. The motor is immersed in hydraulic fluid to warm fluid for circulation and for protection against excessive electronic component temperature. The circulation pump will operate on the ground only during pre-launch operations. During liftoff/ascent the circulation pumps will be off. At the end of the mission, the circulation pumps, along with the entire SLS core stage, will burn up as it descends through the atmosphere. The circulation pumps may also be used to conduct various TVC system level ground checkouts.

Figure 1. SLS Core Stage TVC Circulation Pump

Work to be performed by the Supplier shall consist of providing personnel, materials, services, facilities, logistic support, data and management required to test, document, deliver on schedule, and support the equipment defined herein. Work shall be performed by an ISO9001/AS9100 or approved equivalent certified supplier who shall provide NASA right of entry, verification of test setup and verification of equipment calibration.

Random Vibration, Non-Operating With inlet and outlet pressure at 200 ±25 psig, the circulation pump shall meet external leakage and structural integrity requirements during and after exposure to random vibration as specified per Table 1. The random vibration levels shall be applied in each of three mutually perpendicular directions for a minimum duration of 300 seconds. Accelerometers shall be located as shown in the figures below. Any changes/variations to accelerometer locations shall be coordinated through NASA engineering.

Table 1. Random Vibration Qualification Test Levels SLS Random Vibration Qualification Levels

Shock, Non-Operating With inlet pressure at 200 +/-25 psig, the circulation pump shall meet external leakage and structural integrity requirements during and after exposure to flight shock environment as specified per Table 2. The shock levels shall be applied in each of three mutually perpendicular axes. Three shocks per axis in both the positive and negative directions for a total of six shocks per axis.

Table 2. Flight Shock Environment

Random Vibration Test Accel Locations By Low Press Outlet By Neg By Hi Press Outlet By Inlet By CG On Fixture ❸ ❸ ❸ ❸ ❸ ❸ ❸

❸ ❸

By Hi Press Outlet ❸

Shock Test Accel Locations By CG ❸ ❸ By Low Press Outlet By Neg By Hi Press Outlet By Inlet On Fixture ❸ ❸ ❸ ❸ ❸ ❸ ❸

❸ ❸

By Hi Press Outlet ❸

Figure 2. Accelerometer Locations

Test Verification Process Nasa Marshall Space Flight Center (MSFC) shall hand carry and deliver the circulation pump to the supplier for initial testing. Upon completion of the Random Vibration Test, the supplier shall notify MSFC to retrieve the circulation pump for a Functional Operating Test to be performed by MSFC in the on-site TVC Lab, Building 4205, Room 110. The supplier shall verify test data completeness prior to test tear down for the Functional Operating Test. MSFC will return the circulation pump to the supplier for Shock tests. The supplier shall verify test data completeness and acceptability in accordance with the test tolerances in MIL-STD-810G prior to final test tear down. Upon completion of the Shock Test, MSFC will retrieve the pump from the Supplier.

NASA will provide the necessary equipment and personnel support to pressurize the pump inlet.

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