SATPC0035397 Tab 04 SOW.pdf
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- Attached to
- Acrylic Altitude Chamber for Cable Test Federal contract opportunity
- Solicitation number
- 80NSSC24873194Q
About this file
The document is a Statement of Work (SOW) for the procurement of an Acrylic Altitude Chamber for cable testing at NASA's Glenn Research Center. The chamber must be composed of non-conductive, non-ferrous materials and consist of 5 interconnected modules, including 3 cube-shaped chambers and 2 cylindrical tubes. The chamber must be capable of reaching a minimum simulated altitude of 60,000 feet and withstand a 10:1 safety factor.
The related federal contract opportunity is a sole-source acquisition from SANATRON, INC under FAR 13.106-1(b)(1)(i), as they are determined to be the sole provider of the required acrylic altitude chamber. The procurement will be for commercial items and services using FAR Part 12 and 13 procedures. Interested parties may submit their capabilities by 3:00 pm CST on 6/20/2024 for the government's consideration of a competitive solicitation. The procuring agency is the National Aeronautics and Space Administration Shared Services Center.
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High-Power Advanced Cable Technology (HiACT) Acrylic Altitude Chamber for Cable Testing
Statement of Work
Background:
To meet the needs of advanced wiring technology for electric aircraft, the High-Power Advanced Cable Technology (HiACT) Rig at NASA’s Glenn Research Center is designed to test the thermal performance of cables for electrified aircraft systems. To further the goals of the project, NASA is seeking procurement of an altitude chamber composed of non-conductive and non-ferrous materials capable of testing cables in a simulated high-altitude environment.
Design and Performance Requirements of the Altitude Chamber:
Chamber Design Requirements:
1) Test chamber shall be principally constructed of Acrylic or similar non-conductive and non-ferrous material.
2) Test chamber shall be constructed of 5 total modules capable of being interconnected to form single volume. The modules will consist of:
a) 3 each - Cube-shaped chambers approximately 16-18 inches (inside dimensions for height, length, and width)
i) Each fitted with appropriate feedthroughs for instrumentation and vacuum connections.
b) 2 each – Cylindrical tubes, 10-12 inch inside diameter, 36-48 inches in length
3) 2 each - Liquid and Gas Vacuum Feedthrough for ½” OD Tube with Swagelok (Steel) Type
Connection
4) 2 each - Power Vacuum Feedthrough, 50 Volt / 1000 Amps
5) 6 each – Power Vacuum Feedthrough, 5000 Volts / 50 Amps
6) 4 each – SMA Coaxial Feedthrough
7) 2 each – D-Sub 50-pin Thermocouple Feedthroughs (Type-T)
Chamber Performance Requirements:
1) Chamber must be capable of reaching minimum simulated altitude of 60000 feet or 7500 Pa at ambient temperature.
2) All Pressure Vessels and Systems (PVS) shall be designed, fabricated, inspected, and tested in accordance with all applicable national consensus codes and standards, federal and state laws, NASA NPR 8715.1 and NASA STD 8719.17.
3) Chamber must be constructed with 10:1 safety factor for the design conditions.
Deliverables:
1. Acrylic Chamber (5 sub-modules)
2. Minimum Supporting Documentation:
a. List of components and materials
b. Analysis of chamber design demonstrating safety factor of 10:1 for the design conditions
Chamber Concept:
Figure 1. Acrylic Chamber Concept - Layout
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