NASA/Goddard Space Flight Center, Code 214.3, Greenbelt, MD 20771

18 -- GEOSYNCHRONOUS SCIENCE SATELLITE REQUEST FOR INFORMATION DUE 071598 POC Billie Smith, Contracting Officer, Phone (301)286-9919, Fax (301)286-0530, Email Billie.D.Smith.1@gsfc.nasa.gov WEB: Click here for the latest information about this notice, http://nais.nasa.gov/EPS/GSFC/date.html#GEOSat-1. E-MAIL: Billie Smith, Billie.D.Smith.1@gsfc.nasa.gov. NASA/GSFC is issuing this Request For Information (RFI) to survey industry in order to obtain information about spacecraft for future Geosynchronous Science (GeoScience) missions. The GSFC STAAC Project Formulation Office, Code 740, is the sponsor this RFI. All satellite vendors are encouraged to participate in this effort to aid the GeoScience investigation team in determining industry's ability to accommodate a GeoScience spacecraft. Multiple submissions are acceptable. Submissions are requested by 15 July 1998. Dr. James Gatlin (NASA GSFC) will be the primary point of contact for this survey and can be reached, by telephone, at 301-286-6680, or by electronic mail at (James.A.Gatlin.1@gsfc.nasa.gov). The following Industry Survey Data Package provides the information concerning the guidelines for responding to this request and the payload requirements. The Industry Survey Data Package is also being released to NASA's Rapid Spacecraft Acquisition vendors through the Rapid Spacecraft Development Office(RSDO). It is NOT necessary for RSDO vendors to respond this CBD RFI announcement if responding to the RSDO RFI, although an RSDO vendor may choose to submit a non-RSDO spacecraft concept through this CBD announcement. As always, this Request for Information does not obligate the US government to a future procurement. The US Government will protect all proprietary information received from the vendors, and distribution of any material will be based on a strict need-to-know basis. ************************************************ INDUSTRY SURVEY DATA PACKAGE 1.0 Introduction This survey is to ascertain if commercial spacecraft vendors can offer a low cost, small geosynchronous satellite capability to meet future needs of NASA. The missions that will utilize these satellites are exploratory in nature and may be envisioned to be precursors to future operational systems. The instrument(s) payload is envisioned to span the range between 50kg/50watts to 150kg/400watts. The study is looking for an on-orbit capability; therefore, it is requested that the orbit delivery method be included. 2.0 Instructions for Response Preparation Please provide the information that is requested in Sections 2.1 thru 2.5 by referencing the specifications outlined in Section 4. 2.1 Mission Overview Describe the launch and geosynchronous orbit delivery method. Identify the selected launch vehicle, as well as any transfer stage (if appropriate). For the purpose of this request, assume a target launch date of 2003. Discuss the operational concept of the spacecraft (not instruments) in a geosynchronous orbit. Identify spacecraft operational modes, such as acquisition, safe hold, and communications. Discuss the potential implementations for autonomous operations. Describe spacecraft operations that might constrain instrument use. 2.2 Spacecraft Overview Describe the spacecraft and show how the objectives will be met as outlined in section 4. Provide a top-level block diagram showing the overall design of the satellite and its subsystems as well as the interfaces to the instrument(s). Provide summary mass and power budgets. Discuss subsystem characteristics including hardware and software required. In addition, describe the volume(s) available for instrument(s) and provide a preliminary description of a thermal control system of the bus as well as a strategy for thermal control of the instrument(s). List any assumptions made where specific objectives or requirements are not stated. 2.3 Trade Studies Identify trade studies that could provide significant cost savings. Describe the spacecraft design approach, particularly as it relates to redundant versus single string hardware. Identify mission requirements that drive the spacecraft design and cost. Specifically address the changes necessary to incorporate the high data rate instrument telemetry, enhanced attitude control performance, and passive instrument cooling options as described in section 4.5 2.4 Related Experience The participant should provide insight into any related work with respect to geosynchronous satellites and geosynchronous payloads. 2.5 Cost Estimate The government is interested in acquiring an on-orbit capability at minimal cost. It is anticipated that the future spacecraft contracts will be Firm Fixed Price. Provide estimated spacecraft, launch vehicle, and transfer stage (if applicable) costs. Include all cost to delivery on orbit except for instrument integration and launch vehicle integration. 3.0 Deliverables The participant should provide 5 copies of a written submission by July 15, 1998 to: Ms. Billie Smith NASA Goddard Space Flight Center Mail Code 401.5 Building 16W, Room N115 Greenbelt, MD 20771 This Request for Information does not obligate the US Government to a future procurement. All written and verbal information provided by the voluntary participants in this survey will be considered proprietary and protected by the US Government accordingly. Distribution of the supplied information will be based on a strict need-to-know basis. 4.0 Geosynchronous Satellite Objectives 4.1 Mission Objectives 4.1.1 Mission Life The on orbit operational lifetime of the satellite bus should be a minimum of 2 years with a probability of success of better than 0.80. 4.1.2 Orbit The orbit will be geosynchronous and longitudinally located over the continental United States with a nominal inclination of 0 degrees bounded by (+/-) 2 degrees. 4.2 Launch Vehicle Objectives Only domestic sources for launch vehicles should be considered. Shared launch capability may be considered. 4.3 Instrument Objectives 4.3.1 General The instrument(s) are envisioned to be earth pointing and require an unobstructed earth viewing capability. 4.3.2 Mass The total mass of the instrument(s) will fall between 50 -- 150 kg. 4.3.3 Power The total power of the instrument(s) will fall between 150 -- 400 W (EOL). In addition, the power system must be capable of supporting full operations during eclipses. 4.3.4 Pointing Control Describe the capability of the spacecraft bus to support Earth viewing instruments from Geosynchronous orbit including: (1) Nadir pointing accuracy in Roll, Pitch, and Yaw (2) Inherent off nadir pointing capability (if any) (3) Off nadir slew rates (if any) (4) Roll & Pitch pointing knowledge (5) Yaw pointing knowledge (6) Jitter amplitude & spectrum in Roll & Pitch (7) Jitter amplitude & spectrum in Yaw (8) Other relevant characteristics 4.4 Additional Bus Objectives 4.4.1 Command & Control Uplink This capability should provide control necessary to operate the satellite as well as a strategy for instrument control. 4.4.2 Telemetry Downlink This capability should provide necessary bus health data as well as a strategy for supplying instrument health and a modest (0.1 to 1.0 Mbit/second) instrument data continuous telemetry rate. 4.4.3 Station-keeping and satellite disposal No north-south stationkeeping is envisioned for these missions. Appropriate east-west stationkeeping is required. Appropriate disposal from operational orbit is also required. 4.5 Additional Options 4.5.1 High Data Rate Telemetry An optional downlink system to provide continuous 150 Mbit/sec instrument data telemetry. 4.5.2 Enhanced Pointing Control Enhanced spacecraft (or instrument platform) pointing to approach any or all of the following performance goals: (1) Nadir pointing accuracy in Roll, Pitch, and Yaw of (+/-) 0.01, 0.01,and 0.025 degrees. (2) Off nadir capability in Roll & Pitch of (+/-) 15 degrees (3) Off nadir slew rates in Roll & Pitch of (+/-) 0.5 degrees/second. (4) Roll, Pitch, & Yaw pointing knowledge of (+/-) 10 micro-radians 4.5.3 Cold Space View Provide instruments that require passive cooling an unobstructed view North or South to cold space. (0138)

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