SOURCES SOUGHT
A -- Request for Information (RFI) For Small Explorer (SMEX) EPPIC Concept Access to Space (Launch Services)
- Notice Date
- 8/5/2016
- Notice Type
- Sources Sought
- NAICS
- 336414
— Guided Missile and Space Vehicle Manufacturing
- Contracting Office
- NASA/Goddard Space Flight Center, Greenbelt, Maryland, 20771
- ZIP Code
- 20771
- Solicitation Number
- NASA-GSFC-RFI-SMALL-EXPLORER-EPPIC-Concept-Access-to-Space-LAUNCH-SERVICES
- Point of Contact
- Peter Spidaliere, Phone: (301) 286-6222, Julie Anne Janus, Phone: 3012864931
- E-Mail Address
-
peter.d.spidaliere@nasa.gov, julie.a.janus@nasa.gov
(peter.d.spidaliere@nasa.gov, julie.a.janus@nasa.gov)
- Small Business Set-Aside
- N/A
- Description
- Request for Information (RFI) ForSmall Explorer (SMEX) EPPIC Concept Access to Space (Launch Services) dated August 5, 2016 1.0INTRODUCTION/SCOPE This RFI is in response to the NASA Announcement of Opportunity (AO), NNH16ZDA003J, for the 2016 Small Explorer (SMEX) element of the Heliophysics Explorer Program. NASA's Goddard Space Flight Center (GSFC) is supporting the Laboratory for Atmospheric and Space Physics (LASP) in developing a mission concept, entitled EPPIC, to be proposed for this AO. This RFI is being issued to determine the feasibility, risks, and cost of non-NASA provided access to space. The proposed mission is currently in pre-Phase A. This phase ends with a (step-1) proposal that is due 3 months after the AO is released. If the proposal is selected, the SMEX-2 mission will proceed into Phase A, per NASA Procedural Requirement (NPR) 7120.5E (e.g. http://nodis3.gsfc.nasa.gov/main_lib.html), to produce a step-2 Concept Study Report (CSR) and Site Visit. If the step-2 CSR is selected, the mission will proceed into Phase B for implementation. The following schedule should be used as a basis for responses to this request for information: RFI releasedAug 5, 2016 Responses dueAugust 25, 2016 SMEX AO ReleasedJuly 15, 2016 Proposal submittal in response to 2016 SMEX AOOctober 15, 2016 Step-1 Selections Announced (target)Spring 2017 Initiate Phase A Concept Studies (target)Spring 2017 Phase A Concept Study Reports Due (target)Spring 2018 Down-select for Flight (target)Fall 2018 Launch Readiness dateNET March 31, 2022 NLT August 31, 2022 The no earlier than (NET) date is the date that the EPPIC mission wishes to launch; the NLT date is the limit set by the AO. If the EPPIC proposal wins, it will be managed by the LASP. The spacecraft buses will be provided by GSFC. At this time it is not been decided if the procurement of a launch service will be through LASP, GSFC, or NASA's Launch Services Program (LSP); that decision will likely occur during the step-2 process. 1.1DESIRED MISSION SERVICES NASA's GSFC is interested in information regarding the feasibility, risks, and cost of non-NASA provide access to space; including pre-launch mission planning, mission design, integration to launch vehicle, post-integration aliveness testing, and launch support for the two EPPIC spacecraft. All interested parties are requested to respond to this RFI in accordance with Section 5. 2.0MISSION OVERVIEW The SMEX EPPIC mission is planned to be a NPR 7120.5 Category 3 mission with NPR 8705.4 Class D spacecraft and payloads. The figures below show the EPPIC concept in a small launch vehicle fairing and on an ESPA Grande in a 4m fairing. The major dimensions of the spacecraft and the stack are shown below. Each spacecraft will be a major axis spinner and well balanced (inertia matrix in work) and will weigh >108 kg fully margined. Two orbit options are under consideration by the science team. Option 1 is a circular orbit between 450 and 620 km. The higher altitude is preferred, but not required. The two spacecraft will be delivered into slightly different orbits, with inclination ~2 degrees apart in order to allow the orbit planes to evolve as desired by the science team. Option 2 two consists of two circular, polar orbits - one at 500 km and the other as high as 1000 km. In this case there is no inclination change required. It is realized that 1000 km may not be possible in all cases; the highest orbit achievable should be reported. For both option 1 and 2, the minimum allowable orbit inclination is 80 degrees and the maximum allowable orbit inclination is 100 degrees. There are no sun crossing time or other requirements that tie the two orbits together in any way. Conceptual Operational Sequence The following is two operational concepts have been developed by the EPPIC team. Option one consists of two circular, polar orbits with a 2 degree difference in inclination; option two consists of two circular, polar orbits - one at 500 km and the other as high as 1000 km. Different scenarios other than those described are acceptable, as long as the orbits described above are achieved. Option 1 Sequence 1.Launch into a circular polar orbit between 450 and 620 km with an inclination of between 80 and 100 degrees. 2.LV orients first spacecraft with solar arrays toward the sun, spins upper stage to ~1 rpm about the spacecraft Z axis. 3.LV closes spacecraft battery relay ~1 min before sep 4.LV Deploys the first EPPIC spacecraft. 5.LV backs away to avoid contamination of the first EPPIC spacecraft. 6.LV executes a delta inclination burn to change the orbit plane by ~2 degrees 7.LV orients the second spacecraft with solar arrays toward the sun, spins upper stage to ~1 rpm about the spacecraft Z axis. 8.LV closes payload battery relay ~1 min before sep 9.LV deploys the second EPPIC spacecraft 10.LV backs away to avoid contamination of the second EPPIC spacecraft. Option 2 Sequence 1.Launch into a circular polar orbit of 500 km with an inclination of between 80 and 100 degrees. 2.LV orients first spacecraft with solar arrays toward the sun, spins upper stage to ~1 rpm about the spacecraft Z axis. 3.LV closes spacecraft battery relay ~1 min before sep 4.LV Deploys the first EPPIC spacecraft. 5.LV backs away to avoid contamination of the first EPPIC spacecraft. 6.LV raises the orbit to 1000 km (or as high as the upper stage can achieve, but without exceeding 1000 km) 7.LV orients the second spacecraft with solar arrays toward the sun, spins upper stage to ~1 rpm about the spacecraft Z axis. 8.LV closes payload battery relay ~1 min before sep 9.LV deploys the second EPPIC spacecraft 10.LV backs away to avoid contamination of the second EPPIC spacecraft. Standard Services A list of services required by EPPIC is provided below. It is expected that EPPIC requires no particularly difficult or unusual services; however, if any cannot be provided, or are particularly costly, they should be identified. Mechanical Interface 15" bolt circle adapter required Electrical Interface Four 15-pin In-Flight Disconnect (IFD) separation connectors used for Payload operation on the pad, LV-monitored separation breakwire loops, and open/close command to battery relays. Battery charging Battery charging on the pad. Launch Site Processing: - Office Space An air-conditioned shared office space with desks, chairs, file cabinets, internet access, telephone, fax machine, and a conference facility will be provided to accommodate five people per Payload. - Facility space 60' x 50' x 24'H, to be shared among up to six ESPA-Grande class Payloads and propulsive ESPA-Grande (if required), Payload GSE to be located in this facility or in control room space. - Facility Environment Temperature Control - 22.5° ± 2.8° C (72° ±5° F), Humidity Control - 50 ± 10%, Cleanliness - Class 100,000 - Control Room space 34' x 24' x 10'H, to be shared among up to six ESPA-Grande class Payloads and propulsive ESPA-Grande (if required) - Clean Room Purge None, any required purge capability to be supplied by Payload - Clean Room Garments: > 5 garments per week - Crane Capability Crane capacity 25 tons, 73' hook height - Facility Power Standard - SV Fueling None LV Purge GN2 Purge on Pad Power to SV after IPS Integration Power on pad. Launch unpowered. Payload access on LV No access is required for the Payload after integration to the LV, Separation System: Separation system provided by the Payload owner, standard 15 inch lightband, Telemetry Telemetry to support powered operation and LV separation confirmation. Command LV to provide battery relay open and close commands LV provides two separate commands to deploy stacked spacecraft SV to LV Integration Payload requests to accomplish integration of Payload or to be present during integration. 2.1LAUNCH VEHICLE A proven access to space approach, or one which will be certified before 2018, should be demonstrated in the response to this RFI. The launch and related launch services are included in this RFI. The respondent should show heritage and previous launch experience for the access to space. Plans for certification, if the launch vehicle has not already been certified by NASA, should be described. The integration flow and launch environmental test levels (e.g. Launch loads and acoustic levels) should be provided. The mechanical, electrical, and thermal interfaces between the access to space method and spacecraft should be provided as ICDs. Historic and predicted costs for the observatory access to space shall be provided in response to this RFI. The Launch vehicle proposed for access to space shall be consistent with the AO requirements and the launch vehicle characteristics and capabilities provided in the "Expendable Launch Vehicle (ELV) Launch Services Information Summary" found in the Program library http://explorers.larc.nasa.gov/HPSMEX/SMEX/programlibrary.html 2.2LAUNCH MANIFEST The RFI respondent should provide a letter indicating that they could manifest the NASA's GSFC SMEX-2 mission commensurate with the requirements of the 2016 SMEX AO for the satellite access to space requirements. The SMEX-2 mission will be ready for launch on Dec 1, 2021 and is required to be launched no later than (NLT) August 2022. The vendor should also include separately costs associated with month-to-month delays in a launch date for up to 9 months, if a rideshare with another Primary payload is proposed.   3.0AO REQUIREMENTS 3.1GENERAL The access-to-space offered shall be compatible and appropriate for the mission described in Section 2.0 and the SMEX AO Rideshare requirements described in Section 3.2. The EPPIC SMEX-2 mission will be a NPR 7120.5 Category 3 mission with NPR 8705.4 Class D spacecraft and payloads. 3.2REQUIREMENTS NASA's Science Mission Directorate (SMD) has released the following guidelines for proposing access-to-space for the 2016 SMEX AO. https://nspires.nasaprs.com/external/solicitations/summary.do?method=init&solId={A0C496AC-9B9D-8F7D-A506-B1695BF9BDE8}&path=open Additional guidance may be issued at any time. Respondents should ensure that their response is consistent with the extant guidance for the 2016 SMEX AO as of the date of their submission. Respond to each guideline extracted (shown in italics) below and provide any additional details. Although NASA-provided launch services continue to be offered, alternative access to space, rather than the use of NASA-provided launch services, may be proposed or considered under this AO. Alternative access to space may include the provision of non-NASA launch services as primary, secondary, or co-manifested payloads on a U.S.- or foreign-manufactured launch vehicle. •Under this AO, purchased launch services must be obtained on a U.S.-manufactured launch vehicle only. The National Space Transportation Policy (Section IV) prescribes the use of U.S.-manufactured launch vehicles for the launch of U.S. Government sponsored payloads. Proposed alternative access to space must be consistent with the National Space Transportation Policy (http://www.whitehouse.gov/sites/default/files/microsites/ostp/national_space_transportation_policy_11212013.pdf) and with any policies or requirements specified in this AO. For proposals submitted in response to this AO, NASA will accept a Launch Vehicle Risk Category 1 (per NPD 8610.7D, NASA Launch Services Risk Mitigation Policy for NASA-Owned and/or NASA Sponsored Payloads/Missions) for non-NASA provided access to space. Non-NASA launch services and hosted payloads will be handled by NASA consistent with existing policy and regulations. The demonstrated reliability and the resultant probability of mission success for non-NASA launch services and hosted payloads will be evaluated by NASA consistent with National Space Transportation Policy (National Space Transportation Policy, Section IV) and NASA's Launch Services Risk Mitigation Policy (NPD 8610.7D, NASA Launch Services Risk Mitigation Policy for NASA-Owned and/or NASA-Sponsored Payloads/Missions). The proposed launch service will be assessed in conjunction with NASA stakeholders as part of the selection process. The functions, operating structure, and policies of the NASA Launch Services Program (LSP) with regards to defining and executing advisory services or consulting for Government or commercial entities are defined in the Launch Services Program (LSP) Advisory Services Plan that can be found in the Program Library. The NASA Flight Planning Board will approve final mission assignments, assuring consistency with Agency risk strategy. Information on the reliability of ELVs may be obtained from the point of contact listed in the AO ELV Launch Services Program Information Summary document. Alternative access to space options involves several complex issues at this stage of project maturity. It is in the proposer's best interest to clearly support the maturity of their plan and access to space possibilities. The minimum expectations for access to space arrangements must be included in the proposal to the level of detail outlined in Requirement 90 (iv). Any additional evidence of maturity or commitment provided will be used to support risk posture. Requirement 90. Proposals that include non-NASA launch services (purchased or contributed) obtained from a U.S. or non-U.S. partner shall meet the following requirements: (i)When flying as a primary, the proposer must demonstrate a commitment from the launch services provider. (ii)When flying as a co-manifested or secondary payload, the proposer must demonstrate a commitment from the proposed co-manifested or primary mission organization(s) to accommodate the proposed payload or demonstrate that the launch services provider has an appropriate process to provide specific launch services; these commitments must be documented in a letter from the appropriate organization(s). (iii)The proposal must identify the launch opportunity and must provide evidence in the proposal that the launch service provider agrees to manifest the mission should the proposal be selected and confirmed for flight by NASA. This evidence must include a letter from the launch services provider containing, at a minimum, the following information: a.Evidence that the launch services provider will provide the services described in the proposal under the conditions (cost, schedule) described in the proposal; b.A description of the opportunity (or opportunities, if more than one under consideration) that the launch service provider can offer for consideration by the PI; and c.A description of the process that the launch service provider will use in order to commit to the PI to provide specific launch services for the proposed investigation, should NASA select the proposed investigation; this process description must include a notional schedule for identifying the specific launch opportunity and definitizing the cost. (iv)The proposal must describe the launch services, demonstrate compatibility with the proposed launch vehicle, and show how the provider will fulfill the mission requirements. (v)The proposal must describe the arrangement between the PI and the non-NASA launch service provider to enable the PI's insight for launch services, consistent with NASA Procedural Documents (NPD) 8610.7 and 8610.23. Note that these NPDs allow unique arrangements for payloads able to tolerate more risk. NASA will develop an advisory approach based on the insight the PI is provided from the non-NASA launch service provider. The proposal budget must include $2.0M for the NASA launch vehicle monitoring functions and advisory services that would enable NASA to review and advise the PI on launch vehicle information from the non-NASA launch service provider. 4.0RFI RESPONSE INSTRUCTIONS, FORMAT, AND SELECTION CRITERIA 4.1INSTRUCTIONS Based on the AO requirements, listed in section 3.2 above, the respondent should: •Provide a letter, which may be included in the EPPIC SMEX proposal, addressing the elements of Requirement 90 items i, ii, and iii. •Provide an estimated cost for all the activities including mission design, integration and testing, and launch services. The response shall include a brief discussion of the basis of estimate and any uncertainty in the cost estimate. •Demonstrate compliance to the mission described in Section 2.0 and the requirements in Section 3. Launch margin to a given altitude should be clearly identified. •Describe your rideshare approach, including 1) schedule (with key milestones defined); 2) documentation requirements; 3) analysis requirements; 4) hardware requirements; 5) testing requirements; 6) integration requirements; 7) safety & mission assurance requirements; 8) budget phasing requirements; and any other additional details. •Identify the technical maturity/qualification of the proposed access to space opportunity. If the launch opportunity approach has not already been certified by NASA, the respondent should describe how these items will be demonstrated, including a timeline for this demonstration, before it is required for this mission. •Launch Vehicle or other ICDs should be provided. 4.2FORMAT The RFI response, including any cover letter, title pages, and other supporting material, shall be formatted as a Portable Document Format (PDF) file delivered to the E-mail address in section 5.0. ICDs should be provided as separate PDF files. 5.0POINT OF CONTACT: Questions about this RFI should be directed to Peter Spidaliere (Phone: 301-286-6222, Email: peter.d.spidaliere@nasa.gov). 6.0FINAL DUE DATE OF RFI RESPONSE The response to the RFI is due no later than 5 p.m. ET on August 25, 2016. The electronic PDF document shall be sent to Peter Spidaliere (Email: peter.d.spidaliere@nasa.gov). It is the responsibility of potential respondents to monitor the FBO.gov for further information concerning this POD: http://fbo.gov   7.0ACRONYMS AOAnnouncement of Opportunity CBECurrent Best Estimate CSRConcept Study Report DCDirect Current ELVExpendable Launch Vehicle FYFiscal Year GSFCGoddard Space Flight Center I & TIntegration & Test ICDInterface Control Document LVLaunch Vehicle MLIMulti-Layer Insulation NASANational Aeronautics and Space Administration NLTNo Later Than NPDNASA Procedural Document NPRNASA Procedural Requirement NTENot To Exceed PDFPortable Document Format PIPrincipal Investigator PDFPortable Document Format POCPoint of Contact PODPartnership Opportunity Document ROMRough Order of Magnitude RSRideshare RYReal Year SAASouth Atlantic Anomaly SMEX-2Small Explorer #2 SOWStatement of Work TBDTo Be Determined U.S.A.United States of America
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