Statement_of_Work.docx

I. Statement of Work

1.0 Purpose – The objective of this effort is to implement improved thermal vacuum testing capability for ESTA to prepare for the 100 missions of LLB-2 thermal vacuum testing, as well as additional missions requiring thermal vacuum testing in the next 5-10 years.

2.0 Scope – This specification defines the specifications required for the thermal vacuum chamber being procured by NASA Johnson Space Center (JSC). The equipment design shall consider the OSHA, NEC and ASME Code for Unfired Pressure Vessels. Safety interlocks and features shall be provided for the equipment and operating personnel. The equipment shall be tested prior to shipment.

3.0 References:

4.0 The following items are required for the proposed system:

4.1 Dimensions:

4.1.1 The system shall fit within a 15’ x 15’ roll up door to be moved into the test facility.

4.1.2 The system chamber volume shall be no larger than 100 ft3.

4.1.3 The chambers usable internal space shall be approximately 36” wide by 48” long by 36” high.

4.2 Construction:

4.2.1 The outer structural shell of the environmental simulator will be designed to resist one atmosphere of external pressure while under vacuum.

4.2.2 Penetrations and other fittings will be designed in accordance with accepted structural design techniques and good high vacuum practice.

4.2.3 The shell will be designed of Type 304 stainless steel plate and will refer to the ASME Code, Section VIII, for Unfired Pressure Vessels.

4.2.4 Penetrations and nozzles shall be of Type 304 stainless steel conforming to ASTM Specification A240-58T.

4.2.5 The system will use a non-contaminating style pumping system such as a turbomolecular UHV pump for vacuum operations.

4.2.6 The system door closure shall be able to support pressure generated from pressure strength with active over pressure protection.

4.2.7 The door will be hinged on the left side when facing the front of the chamber and be capable of opening a full 180 degrees swing to allow maximum access.

4.2.8 The top of the Platen will be approx. 32” from customer finished floor.

4.2.9 The system shall be able to support greater than or equal to 100 lbs of test hardware. Ideally, the system shall be able to support greater than 500 lbs of test hardware.

4.2.10 The platen will easily support 100 lbs. mass load.

4.2.11 The platen will be capable of being extended out of the chamber 48”. It will include flexible fluid hoses, shelf slide guides, and a guided docking lock in place support cart with locking casters which is moved out of the way during normal operation. The docking cart assures the shelf is held firmly in place while product is being loaded/unloaded on the extended shelf.

4.2.12 The vacuum chamber shall be provided with a fixed in place thermal conditioned shroud. The shroud surface will be traced with passages to accommodate a temperature-controlled medium which will perform the thermal conditioning function. The shroud will fully encapsulate the test specimen area, including the ends.

4.2.13 The portions of the shroud facing the customer product are coated in a high emissivity aerospace black paint to absorb product heat load.

4.2.14 The exterior portion of the shroud is polished.

4.2.15 All corresponding customer port holes and vacuum equipment access will be detailed on the approval drawing prior to construction.

4.2.16 The chamber shall include a minimum of two 6” CF Spare ports not utilized by any instruments or feedthroughs.

4.2.16.1 The vendor will provide 2 blank 6” flanges installed and two additional 6” flanges precut with a minimum of four 1” instrumentation ports and populated with 1” plugs. To be used by NASA as needed.

4.2.17 The thermal shroud and platen will be designed with special fluid shut off valves to allow for ease of removal and replacement with a stainless-steel version purchased separately at a later time. This work can be performed at the customer site.

4.2.18 Thermal conditioning system requirements for the chamber will be self-contained to the system, not requiring any chilled water commodities from NASA facility.

4.2.18.1 If an outdoor conditioning system is required, it must be designed to be weather-tight. The system will include the main power connections, the fluid circulation system and the cascade refrigeration system with an integral outdoor air cooled condenser.

4.2.18.2 This system would reside on a NASA supplied concrete pad on the exterior of the facility within 50 linear feet from the main vessel.

4.2.18.3 Vendor will provide two fluid interconnect lines, GN2 interconnect line, electrical conduit for the controls system, etc.

4.2.18.4 Vendor will advise as to the footprint and weight of the system at time of order so the customer can provide an adequate support pad.

4.2.19 The system shall utilize 480VAC, 3-phase, 50/60kHz power at less than or equal to 200A. The system may utilize power less than 480 VAC, 3-phase, at 200A.

4.2.19.1 Vendor will provide NASA-defined connector.

4.2.20 The thermal system shall be capable of handling at least 500W of live load.

4.2.21 The system shall have a backfill system capable of using GN2.

4.2.22 The system will have one high vacuum rated safety overpressure relief port. The port will be a one-time burst disc style sized to safely relieve any over pressure conditions caused by the customer test product inside the vessel. The burst disc will need to be replaceable, and the vendor will supply one extra burst disc with the system. The system chamber shall be capable of venting at least 6 liters of gas per 3 seconds without over pressurizing. This port shall be able to be vented to the outside of the test facility.

4.2.23 The system shall have at least one internal 115V-15A receptacle.

4.2.24 The system will include an interior light.

4.2.25 The system instrument panel shall contain locations for at least 32 Type K TC’s, at least thirty-two 20 AWG sense line pairs (banana), at least four 8 AWG terminals, and at least four 12 AWG terminals.

4.2.26 A data system shall be provided for the Type K TC measurements that can be incorporated into the software system used for running and datalogging the chamber operations.

4.2.27 The system shall include 1 flange with sealing gland and closures that will have an RJ45 connector and a coaxial style connector to be used to power and communicate with a customer supplied camera. The system shall have a mounting point inside the vessel for the camera to be specified during the design phase.

4.2.28 The system shall have emergency shutdown `capability in the form of an E-stop switch, a loss of power redundancy, auxiliary relay shutdown (ambient) input, and auxiliary shutdown (ambient) relay output.

4.2.29 The system shall utilize Baratron, Granville Phillips or Cold Cathode vacuum sensing measurements.

4.3 Performance:

4.3.1 The system temperature range shall be at least -45°C to 125°C, ideally capable of -75°C to 125°C measured at Platen.

4.3.2 The internal temperature transition rate shall be approximately 2°C per minute average from 125°C to -60°C or -60°C to 125°C, empty chamber measured at supply to shroud.

4.3.3 The Systems internal temperature control tolerance shall be ±1°C at any steady state temperature condition measured at Platen after stabilization.

4.3.4 The ultimate vacuum of the system shall be less than ore equal to 1.0 x 10-5 Torr.

4.3.5 The system shall be capable of providing a heat and cooling load of at least 500 W.

4.3.6 The system vacuum ramp rate shall be capable of pumping down from 760 Torr to 1.0x 10-5 Torr within approximately 6 hours with no test load based on a clean, dry empty and outgassed system.

4.3.7 The system shall be capable of receiving communication from Arbin BTMP150 and Maccor Series 4000 Battery Test Systems. The system shall be able to take commands for thermal operations and stop commands. ModBus 485 is the current protocol currently being used to control existing thermal chambers from the current Arbin systems.

4.4 Options

4.4.1 The system shroud and platen shall be constructed of Type 304 stainless steel.

4.4.2 The system shall include a breakout panel located within the chamber for TC’s, voltage sense lines, etc.

5.0 Administrative:

5.1 The vendor shall provide data showing past performance with at least three other companies in the aerospace industry.

5.2 The system shall have a lead-time of less than or equal to 9 months.

5.3 Training and installation support shall be included in the total price. There will be a minimum of two days of training. Installation will include all required systems.

5.3.1 NASA will provide rigging services to have all hardware in place prior to installation.

5.3.2 Vendor will provide all necessary hardware for connections to facility power and water connections as described in interface drawings. All connections between vendor supplied chiller (if needed) and Thermal Vacuum system will be provided and installed by vendor).

5.3.3 Demonstration of automated run using current Abrin instruments BTMP150 or Maccor Series 4000 system will be conducted before conclusion of installation.

5.4 In addition to the test chamber, the following shall be provided:

5.4.1 Electrical drawings.

5.4.2 Refrigeration schematic.

5.4.3 Vacuum schematic

5.4.4 Major component vendor literature.

5.4.5 General arrangement drawing or descriptive literature.

5.4.6 Calibration instruction.

5.4.7 Operating instruction.

5.5 The equipment shall have a 1-year warranty on parts and labor.

5.6 Shipping shall be included in the total price.

6.0 Contractor Tasks and Deliverables - The Contractor shall perform the following tasks:

6.1 Milestone 1: Provide written response of contract receipt detailing requirement satisfaction plan and details necessary for planned facility modifications.

6.2 Milestone 2: Deliver an updated requirement satisfaction description and facility modification needs if any need to change. Provide a bill of materials, drawings approved by customer, shipment date, and training plan for the final system.

6.3 Milestone 3: Deliver system to the address below and complete installation and training.

7.0 Period of Performance – required items shall be delivered according to the following schedule unless reviewed and approved by contract modification.

7.1 Milestone 1 shall be delivered within 2 weeks of contract award

7.2 Milestone 2 shall be delivered within 6 weeks of contract award

7.3 Milestone 3 shall be delivered within 9 months of contract award