MODIFICATION
A -- PASSIVE MILLIMETER WAVE IMAGER (PMMWI)
- Notice Date
- 7/18/2005
- Notice Type
- Modification
- NAICS
- 541710
— Research and Development in the Physical, Engineering, and Life Sciences
- Contracting Office
- NASA/John F. Kennedy Space Center, Procurement, Kennedy Space Center, FL 32899
- ZIP Code
- 32899
- Solicitation Number
- NNK05109470R
- Response Due
- 9/7/2005
- Archive Date
- 7/18/2006
- Description
- This is a modification to the synopsis entitled Passive Millimeter Wave Imager (PMMWI) which was posted on 11 July 2005. Offerors are notified that the following changes are made: The following SPECIFICATIONS are provided in addition to the Scope of Work (SOW) posted on the original synopsis. The due date for responses is extended to 7 September 2005. Note: This is a tentative date. Offerors should check the official closing date posted on the RFP when it is issued on or about 5 August 2005 (this is also a tentative issue date for the RFP). SPECIFICATIONS: 1. SPECIFICATIONS: These specifications establish the performance, design, development, and test requirements for a Passive Millimeter Wavelength Imager (PMMWI) suitable for monitoring launch vehicles. This specification identifies these requirements only for a single PMMWI which will mount to a Kennedy Space Center (KSC) provided support structure/enclosure. This specification has a scope of a single PMMWI. If this prototype is successful, a future follow-on procurement of one, two or three PMMWIs may be ordered as an option, however there is no guarantee, regardless of prototype performance that the option will be exercised . When multiple PMMWIs are utilized, the system will incorporate two, three or four PMMWIs. 2. APPLICABLE DOCUMENTS The following documents form a part of this document to the extent specified herein: KSC-98203-SW-01 SOW for the Passive Millimeter Wavelength Imager (PMMWI) 3. REQUIREMENTS 3.1 Item Definitions A Passive Millimeter Wavelength Imager (PMMWI) consists of a single imaging unit that detects passive emissions from a launch vehicle and then forms a visual image of the passively emitted radiation. In essence, this imager is simply a camera that operates at millimeter wavelengths instead of at optical wavelengths. Because of this difference in wavelength, however, it becomes possible to image the vehicle through the smoke and steam produced at launch. A PMMWI system may consist of one, two, three, or four Passive Millimeter Wavelength Imagers, arrayed approximately equi-angularly around the launch complex every 90 or 120 degrees to permit real-time viewing of launch vehicles through observing the launch vehicle from independent viewing angles. 3.1.1 Item Diagrams. None 3.1.2 Interface Definitions Three electrical and one mechanical interface are required for proper operation of the PMMWI: a) Control/status interface b) Prime power interface c) Video output interface d) Mechanical mount interface Control/Status Interface The Control/Status Interface provides a remote means to query and control the PMMWI through an IEEE 802.3 10/100 BaseT Ethernet interface (RJ-45 connector) in order to: ?Query Built-In-Test (BIT) status and mode ?Command BIT Modes ?Query operational status and health information ?Command RF gain setting ?Query Ambient Temperature and Humidity levels Prime Power Interface The Prime Power Interface provides power for the PMMWI. US standard power, 120 VAC, 60 Hz, single phase is preferred. Details may be negotiated upon contract award. Video Output Interface The Video Output Interface provides real-time NTSC video, derived from the scanning of the launch vehicle at millimeter wavelengths. This image is a gray-scale television image of the launch vehicle, updated at 10 frames per second, or faster. The output shall interface with a 75-Ohm BNC connector. Mechanical Mount Interface A mechanical interface shall connect the imager to a KSC provided support structure. The structure consists of a support structure and environmentally controlled enclosure which includes a radome window. This PMMWI and support structure will have a fixed look-angle. A tracking mount, in lieu of a fixed mounting bracket, may be added to the PMMWI at a later date. 3.1.3 Major Component List To be supplied by Contractor. 3.2 Characteristics 3.2.1 Performance The PMMWI shall meet the following performance requirements under any combination of the environmental conditions identified in paragraph 3.2.5. 3.2.1.1 Imaging Resolution The imaging resolution of the PMMWI shall permit the detection of an object 12-inches (0.31 meters) or greater in diameter at a fixed operating distance of 500 feet + - 75 feet (152 meters +/- 23 meters). 3.2.1.2 Frame Update Rate The video scan update rate shall be 10 frames per second, minimum, of processed black and white NTSC video. 3.2.1.3 Image Latency The processing time between collecting a complete scan and subsequently processing the scanned data to produce an NTSC video image and then providing a frame of processed scanned video on the NTSC video output shall not exceed 0.150 second. 3.2.1.4 Focus Range 500 feet (152 meters), nominal, fixed, + - 75 feet (23 meters). 3.2.1.5 Depth of Field The PMMWI shall provide a clear image of launch vehicles within the range of 425 feet to 575 feet (130 meters to 175 meters) from the PMMWI, minimum. A clear image over a wider range of distances from the PMMWI is desirable if possible, provided that the focal length of the PMMWI is not varied in real-time. 3.2.1.6 Video Resolution The PMMWI shall provide a resolution within the processed output NTSC video of 640 x 480 pixels, or higher resolution, while meeting the imaging latency requirement of paragraph 3.2.1.3, the imaging resolution of paragraph 3.2.1.1, and the frame update rate of paragraph 3.2.1.2. The Contractor shall provide cost for optional vertical and horizontal indicators on video output. 3.2.1.7 Exposure and AGC/Dynamic Range Automatic exposure control through the use of both fixed and Automatic Gain Control (AGC) shall be employed within the PMMWI's internal RF (Radio Frequency) processing section design. The static RF dynamic range provided by the PMMWI internal electronics shall be 25 dB, minimum, centered on the nominal received signal levels observed for 5-second time-averaged signal levels. This static RF dynamic range (for setting up the initial image) shall be controlled via the Control/Status interface. The value of the gain setting shall be reported back via the Control/Status interface. The purpose of this feature is to manually adjust the gain settings through the RF electronics prior to launch. The instantaneous RF dynamic range automatically provided by the PMMWI internal electronics shall be 120 dB minimum, + 40 dB to ? 80 dB, relative to the 5-second time-averaged signal level imaged through dry air that existed just prior to pad deluge water start, and rocket motor ignition. The PMMWI design shall be capable of providing a clear image despite an increase of up to a 40 dB in nominal signal level above that propagating through dry air prior to launch and despite up to a 80 dB decrease in nominal signal level for imaging through condensing water mist within the air. The reason for this dynamic range specification is based on experimental studies conducted at the Kennedy Space Center. 3.2.1.8 Frequency of Operation The frequency of operation shall be fixed within the range of 20.100 GHz to 100 GHz. Preferably, frequencies that limit the operational capability of the device such as the water vapor absorption frequency around 22.2 GHz and oxygen absorption frequency around 60 GHz shall not be used. Other millimeter wave frequency bands commonly used for communication shall not be used (e.g. ISM 24 GHz, etc.). The operational bandwidth of the PMMWI shall be kept as small as practically possible, not to exceed a bandwidth of 100 MHz, in order not to introduce sensitivity to unintended interference from narrow-band emissions from other terrestrial communication systems. The Contractor shall verify dynamic range characteristics for propagation through steam and provide data at the Preliminary Design Review. 3.2.1.9 Horizontal Field of View Horizontal field of view shall be a minimum of 10.4 degrees. Wider fields of view are preferable. 3.2.1.10 Vertical Field of View Vertical field of view shall be a minimum of 26 degrees. Taller fields of view are preferable. 3.2.2 Physical Characteristics 3.2.2.1 Weight The weight of the PMMWI shall not exceed 800 lbs (363 kg). 3.2.2.2 Size The nominal size of the imaging aperture shall be 1 meter, nominal. The size of the PMMWI shall not exceed 6 feet (H) x 4 feet (W) x 6 feet (D). (1.83m x 1.22m x 1.83m) 3.2.2.3 Heat Dissipation The heat dissipated by the PMMWI shall not exceed 1500 Watts. 3.2.3 Reliability A Mean-Time-Between-Failure of 10,000 hours, minimum, shall be provided by the PMMWI design, as computed in accordance with normal reliability engineering practices. 3.2.4 Maintainability The PMMWI shall be maintainable through regular preventative maintenance, as identified in a maintainability document prepared for the operational use of the PMMWI. The Imager shall have a design for a lifespan of 10 years. 3.2.5 Environmental Conditions 3.2.5.1 Temperature/Humidity The PPMWI will be utilized at the Kennedy Space Center, located in a sub-tropical climate, in proximity to the ocean. When feasible, the Contractor shall utilize corrosion-resistant materials in the PMMWI. The PMMWI Contractor shall identify the following in the Preliminary Design Review package: ?Operating heat load ?Maximum operating temperature ?Minimum operating temperature ?Operating humidity requirements ?Maximum storage temperature ?Minimum storage temperature ?Storage humidity requirements 3.2.5.2 Vibration The PMMWI shall produce a clear image for 15 seconds, minimum, while the KSC support structure is exposed to 8g (rms) vertical, and 2g (rms) horizontal vibration, with a tested dwell in the vicinity of 1 kHz. The support structure is mounted to a floor with a vertical vibration of 63 Hz to 125 Hz on the horizontal plane. The Contractor shall identify the maximum design vibration loads for their PMMWI in the PDR package. Contractors should consider loop bandwidths of around 8 to 10 kHz for local oscillator control systems (used, perhaps, for frequency down conversion within the Passive Millimeter Wavelength Imaging system) which are necessary to reduce in-band acoustic energy peaked around 1 kHz by multiple tens of dB to best preserve the image quality. Vibration levels could also be moderated electrically by mechanically designing for the acoustic noise environment and selecting an electrical synthesizer loop bandwidth around 8 to 10 kHz for any frequency converter stage. 3.2.5.3 Acoustic Noise The PMMWI shall be capable of producing a clear image for 15 seconds, minimum, while the KSC support structure is exposed to an acoustic vibration having a peak frequency at 1000 Hz, with an overall Sound Pressure Level of 151 dB. The KSC provided support structure will include an enclosure (radome) over the PMMWI to protect partially against acoustic buffeting in excess of 150 dB at a peak frequency of about 1 kHz. The Contractor shall identify the maximum design acoustic noise loads for their PMMWI and shall specify any special properties for the radome window at the PDR. 3.2.5.4 Mounting and Installation The PMMWI shall be suitable for mounting on a KSC provided support structure. The Contractor shall identify lifting points, CG, mounting loads and dimensions on the Interface Control Drawing (ICD). 3.2.6 Transportability The KSC provided support structure, with the PMMWI attached, shall be designed for transport on a small trailer over normal roadways. The Contractor shall design the PMMWI with a method of lifting by an overhead crane for unpacking and installation on the support structure. The PMMWI shipping container shall be designed for forklift operations. The PMMWI design shall include, where necessary, quick-acting locking or stow pins for safe transport purposes. 3.3 Design and Construction 3.3.1 Materials, Processes and Parts Materials, processes and parts shall be in conformance with best commercial practices. All metal surfaces shall be passivated or otherwise protected against salt-fog and coastal weather conditions for location near the sea, for an expected lifetime in excess of 10 years, without excessive refurbishment and repair being required. 3.3.2 Electromagnetic Radiation The PMMWI shall emit no un-intentional radiation while imaging or when in stand-by operation. Radiation from the imager for test calibration and sensitivity purposes shall be below 2.0 microvolt/meter over 20.1 GHz to 100 GHz. Temporary radiation signals for test calibration purposes are permitted, upon manual command via the Control/Status interface. 3.3.3 Nameplates and Product Marking A corrosion-resistant nameplate shall be attached on a permanent visible portion of the PMMWI. As a minimum, this nameplate shall contain the following: ?Specification number ?Contract number ?Serial number ?Manufacturer name and address ?Date of manufacture ?Voltage ?Amperage ?Power Frequency ?Weight 3.3.4 Interchangeability The PMMWI unit shall be interchangeable in the future with similar units with a minimum of operations by the user. The PMMWI shall support assignment of the Internet Protocol (IP) address of the Control/Status interface. 3.3.5 Safety The PMMWI shall be designed to avoid the use of elements, compounds, and chemicals known to cause health issues with humans wherever possible. In the event that such risks are not possible to avoid, a warning nameplate shall be placed on a permanent portion of the imager alerting users to the presence of dangerous materials. The Contractor shall identify these materials to NASA for approval at PDR. 3.3.6 Human Performance/Human Engineering The PMMWI shall be designed to maximize the ease of use of the equipment by trained technicians who are not otherwise familiar with millimeter wave equipment. A web-based interface for interrogating the status of built-in-test and operational status shall preferably be provided for the Control/Status interface. 3.4 Logistics 3.4.1 Maintenance Maintenance locations and frequency shall be identified in the O&M manual. Projected maintenance frequency/activity and associated cost information is to be included with the bid. 3.4.2 Supply Critical Parts List shall identify any unique supplies required for the lifetime of the unit. The Contractor shall provide critical spares for the first year of life. 3.4.3 Facilities and Facility Equipment The Contractor shall provide all facilities and equipment necessary to fabricate and perform factory acceptance tests of the prototype unit. 3.5 Personnel and Training 3.5.1 Personnel The PMMWI shall be designed to be operated by a single person. 3.5.2 Training The Contractor shall provide formal training of individuals at KSC to install, operate and maintain the PMMWI which shall not exceed 2 weeks in duration. NASA reserves the right to videotape the training sessions for future training use. 3.6 Major Component Characteristics The major components shall be identified in the top-level assembly drawing. Any unique characteristics shall be identified by the Contractor. 3.7 Precedence In the event of conflict between the Statement of Work, this specification, and applicable documents called out in this specification, the order of precedence shall be the Statement of Work followed by this specification followed by the applicable documents. 4.0 Quality Assurance Provisions 4.1 General As a minimum, a formal acceptance test conducted in accordance with approved test procedures, using test equipment having calibrations traceable to NIST standards, shall be used in the sell-off of each PMMWI. The location for the formal acceptance test shall be as identified in the Statement of Work. Built-in-Test verification of operational status shall be possible to conduct at a government facility through the Control/Status interface. 4.1.1 Responsibility for Tests Contractor is responsible for writing all factory test procedures and functional verification test procedures to prove compliance with all specifications contained herein. The Contractor will also provide a Built-in-Test capability that reports the health of all critical components. 4.1.2 Special Tests & Examinations Factory Acceptance Test. The Contractor is responsible for conducting all factory tests. A factory acceptance test shall be performed with NASA witnesses prior to shipment to KSC. A minimum of two weeks notice shall be given to KSC prior to conducting this test. Functional Verification Test. Upon arrival at KSC, the Contractor shall perform a final acceptance test prior to the system being integrated with the NASA provided support structure/enclosure. NASA will assist in unpacking and performing these tests under the direction of the Contractor. Operations Support Test. The Contractor shall support the initial operations test after the PMMWI has been integrated with the support structure/enclosure. The core of the operations test procedure will be the Contractor provided final acceptance test procedure. End of Specifications. Documents related to this procurement will be available over the Internet. These documents will reside on a World Wide Web (WWW) server, which may be accessed using a WWW browser application. The Internet site, or URL, for the NASA/KSC Business Opportunities home page is http://prod.nais.nasa.gov/cgi-bin/eps/bizops.cgi?gr=D&pin=76 Offerors are responsible for monitoring this site for the release of the solicitation and any amendments. Potential offerors are responsible for downloading their own copy of the solicitation and amendments (if any). Prospective Offerors shall notify this office (preferably via email) of their intent to submit an offer (send email to Tina.M.Landes@nasa.gov).
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