NASA/Lyndon B. Johnson Space Center, Houston Texas, 77058-3696, Mail Code: BH

A -- ELECTRO-HYDRAULIC DRIVE UNIT SOL 9-BH2-46-9-EHDU DUE 043099 POC Keith D. Hutto, Contracting Officer, Phone (281) 483-4165, Fax (281) 244-5337, Email keith.d.hutto1@jsc.nasa.gov -- Keith D. Hutto, Contracting Officer, Phone (281) 483-4165, Fax (281) 244-5337, Email keith.d.hutto1@jsc.nasa.gov WEB: Click here for the latest information about this notice, http://nais.nasa.gov/EPS/JSC/date.html#9-BH2-46-9-EHDU. E-MAIL: Keith D. Hutto, keith.d.hutto1@jsc.nasa.gov. NASA/JSC is hereby soliciting information for potential sources for EHDU and Cooling System Concepts for the Orbiter Electric APU Overview: One auxiliary power unit (APU) provides power to each of three Space Shuttle Orbiter hydraulic systems for operation of aerosufaces, controls, and landing devices. The Electric APU is an Upgrade under study at NASA and United Space Alliance / Boeing for replacement of the current hydrazine fuel powered APU with an electric motor and battery power supply. Many tasks are in progress in an effort to reach a prototype EAPU system demonstration test at the end of year 2000. Intent of this RFI is to: (1) Identify interested participants and their capabilities for proving prototype demonstration hardware (2) Obtain ideas and architecture concepts for the Electro-Hydraulic Drive Unit (EHDU), Cooling System, and Electric Power Distribution & Control (EPDC) (3) Identify existing hardware devices or development activities applicable to EAPU. NASA JSC Technical Contact: Brad Irlbeck 281-483-8617 281-483-3704 (fax) bradley.w.irlbeck1@jsc.nasa.gov Descriptions: 1. EHDU -- Electrically driven hydraulic power supply that converts 270 VDC input to 3000 psi hydraulic output. Characteristics of interest include component type trades, efficiency as a function of output power, internal architecture concepts, high current components for controller, heat rejection, and control schemes. 2 . Cooling System -- Hydraulic fluid is envisioned as a coolant for the EHDU. Heat load from the EHDU, other hydraulic system loads, and possibly the batteries must be removed from the hydraulic fluid. Concepts and characteristics for this cooling system are of interest. An integrated effort to design and develop the cooling system in conjunction with the EHDU is a preferred approach to optimize weight. 3. EPDC -- A 270 VDC EPDC system between batteries and the EHDU will include devices for conduction, overcurrent protection, isolation, and possibly interconnection between the 3 systems. Architecture and component concepts to maximize reliability and redundancy are of interest for this 270 VDC system that operates from sea level to space environments. 4. Prototype Demonstration System -- Concepts and architecture for a prototype EHDU, cooling system, EPDC, and Battery are being considered as part of an architecture trades study. A demonstration test is planned using prototype hardware to evaluate functional system performance in an effort to make a decision concerning the use on an EAPU on the Orbiter. Operating and Physical Parameters Output Power: Normal Operating Mode -- 70 gpm (power in kw is based on 3000 psi output) Output Flow = 5 to 70 gpm (6 to 92 kw) Output Pressure = 2900 to 3150 psia Steady State Hydraulic Output = 5 to 15 gpm (6 to 20 kw) Peak Power = 70 gpm (92 kw) for 2 seconds max. Life = 1000 hours Emergency Output Mode (90 gpm) Output Flow = 5 to 90 gpm (6 to 120 kw) Output Pressure = 2900 to 3150 psia Steady State Power = 5 to 20 gpm ( 6 to 26 kw) Peak Power = 90 gpm (120 kw)for 2 seconds max. Life = 40 minutes; 4 times at 10 minutes each Operating Fluid: MIL-H-83282 Hydraulic Fluid Mission Timeline: 91 minutes of operation = 73 minutes nominal + 18 minutes contingency Input Voltage: 270 +/- 20 VDC Physical Size Available Envelope = 18 x 18 x 25 Weight = 250 lb max Operating and Physical Parameters Redundancy: Fail Operational for Each of three EHDU s Fail Operational / Fail Operational for the EAPU System (3 Batteries, 3 EHDUs, and Electric Power Distribution & Control) Output Power from 2 of 3 EHDU s is Necessary for a Safe Landing Reliability: Probability of Failure Less than 1.0 x 10-8 Thermal: Use Orbiter hydraulic fluid as a coolant for the motor and controller. Hydraulic fluid thermal load includes the motor/controller portion in addition to an existing load of 800 BTU/minute due to hydraulic system losses. Response Time: 80 msec max Response for Change in Output between Minimum Steady-State Power and Peak Power. Efficiency: Goal to maximize efficiency for the steady state power range to minimize total energy. External Pressure: 1 x 10-10 torr to 15.23 psia External Temp: -45 deg F to 150 deg F Operating and Non-Operating Vibration & Acceleration Environment Random Vibration -- 3 axis, 80 minutes per axis Frequency (hz) Level 20 to 100 Increase at 9 dB/octave 100 to 700 0.02 g2/hz 700 to 2000 decrease at 9 dB/octave Acceleration = 5 g s in each axis No solicitation exists; therefore, do not request a copy of the solicitation. If a solicitation is released it will be synopsized in the CBD and on the NASA Acquisition Internet Service. It is the potential offerors responsibility to monitor these cites for the release of any solicitation or synopsis. Vendors having the capabilities necessary to meet or exceed the stated requirements are invited to submit appropriate documentation, literature, brochures, and references. Responses must include the following: name and address of firm, size of business; whether they are large, small, small disadvantaged 8 (a), and or womanowned; number of years in business; (highlight relevant work performed, contract numbers, contract type, dollar value of each procurement; and point of contact -- address and phone number). Technical questions should be directed to: Brad Irlbeck @ 281-483-8617. Procurement related questions should be directed to: Keith Hutto @281-483-4165. Please advise if the requirement is considered to be a commercial or commercial-type product. A commercial item is defined in Internet "Note A". This synopsis is for information and planning purposes and is not to be construed as a commitment by the Government nor will the Government pay for information solicited. Respondents will not be notified of the results of the evaluation. Respondents deemed fully qualified will be considered in any resultant solicitation for the requirement. The Government reserves the right to consider a small business or 8(a) set-aside based on responses hereto. All responses shall be submitted to Brad Irlbeck no later than April 30, 1999. In responding reference 9-BH2-46-9-EHDU. Any referenced notes can be viewed at the following URL: http://genesis.gsfc.nasa.gov/nasanote.html. Posted 03/05/99 (D-SN305669). (0064)

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