SPECIAL NOTICE
16 -- CALL W911W6-15-R-0009 issued under BAA W911W6-15-R-0004
- Notice Date
- 3/17/2015
- Notice Type
- Special Notice
- NAICS
- 541712
— Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology)
- Contracting Office
- ACC-RSA-AATD - (SPS), ATTN: AMSRD-AMR-AA-C, Building 401, Lee Boulevard, Fort Eustis, VA 23604-5577
- ZIP Code
- 23604-5577
- Solicitation Number
- W911W615R0009
- Archive Date
- 3/16/2016
- Point of Contact
- Elizabeth A. Jackson, (757) 878-2100
- E-Mail Address
-
ACC-RSA-AATD - (SPS)
(elizabeth.a.jackson@us.army.mil)
- Small Business Set-Aside
- N/A
- Description
- 1.0Purpose Call W911W6-15-R-0009, Adaptive Engine Exhaust Signature Suppression, issued under Master Broad Agency Announcement (BAA) W911W6-15-R-0004, solicits concept papers for development of an quote mark adaptive quote mark Infrared (IR) engine exhaust signature suppression system capable of meeting anticipated survivability requirements to be levied upon the Army's next generation, Future Vertical Lift (FVL) classes of aviation platforms. The primary focus of the effort will be to explore and demonstrate innovative, advanced engine exhaust signature suppression concepts which can adaptively provide optimized quote mark flight regime or threat regime quote mark defined operational performance characteristics required to meet the needs of the joint warfighter into the next century. While the fundamental focus is toward future vertical lift aircraft systems of various size classes the quote mark Adaptive Engine Exhaust Signature Suppression quote mark concepts explored should implement scalable approaches as to allow exploitation / implementation on legacy rotary wing aircraft systems as well. The adaptive IR suppression concepts shall be designed to operate within a broad range of suppression levels and associated parasitic engine performance losses. The system shall be designed to operate in a minimum of two functional suppression modes. Mode 1 will provide minimal engine and aircraft platform aero/thermodynamic performance impact through configuration in a minimally suppressed configuration (clean aerodynamic flow path). Mode 2 will provide maximized engine exhaust suppression of both hot exhaust components (line of sight exposure) and exhaust plume contributors through integrated reconfigurable flow path components. Significant parasitic engine / airframe parasitic performance impacts associated with the Mode 2 operational configuration are anticipated, however, must be rationally minimized and should be consistent with existing suppression concepts. Developed Mode 2 system attributes shall focus on maximized reduction of engine associated IR signature characteristics (direct line of sight and exhaust plume radiance) within the 1.0 - 12 micron bandwidth. 2.0Background Current engine exhaust signature suppression systems are fixed mode and suffer from significant parasitic thermo / aerodynamic performance losses robbing the aircraft system of power and fuel efficiency throughout the aircraft's entire flight profile and mission duration. Also, since aerothermodynamics engineering tradeoffs are conventionally necessary to balance aircraft performance with signature suppression performance, the ultimate survivability of the integrated aircraft system is not as effective as it could be. As Army aviation looks forward to emerging mission requirements that mandate flying further and faster (ref. JMR / FVL CONOPS) while carrying more functional payload, it has become apparent that novel approaches to reducing the signature attributes of these aircraft are critical in order to improve the survivability of these platforms. In concert, these same technological advances in engine signature suppression and fuel/power performance should be comparably adaptable to existing fleet aircraft and can significantly extend the tactical relevance and performance of these platforms in the modern battlefield. 3.0Scope of Research Effort The solicited research effort encompasses the development of advanced engine exhaust plume and engine hot metal signature suppression concepts which enable quote mark in flight quote mark selection of suppression modes. This effort will focus on the development of technologies which will provide the means to configure the exhaust system for minimal performance decrement when signature suppression is not required (i.e. - non threat environment), and quote mark on command quote mark reconfigure to a high suppression effectiveness configuration, although be it higher engine performance loss, when maximum signature suppression is anticipated (i.e. - threat laden environments). The Government anticipates this effort to be executed in two phases. The Phase 1 will involve conceptual and detailed engineering design; aero / thermo modeling and simulation; and theoretical performance analysis. Phase 2 will focus on the fabrication, assembly, instrumentation, static operational engine tests and performance characterization of a prototype Adaptive Engine Exhaust Suppression system. Offerors shall assume that any operational (ground/flight) demonstrations shall be executed utilizing a surrogate, Government provided, demonstration powerplant such as the T700-GE-701 engine and a surrogate demonstration platform such as the UH-60 or AH-64 aircraft, as no FVL class aircraft will be available. A Government furnished T700-GE-701D engine will be utilized by the Government for the Phase 2 static engine test and evaluation activities to be executed at the Government's test facility with contractor/recipient providing technical support. A follow on Phase 3, which may be executed strictly at the Government's discretion based upon its assessment of the results of Phase 1 and 2, would involve the fabrication and integration of a flight worthy, adaptive system onto either a Government furnished UH-60, or AH-64, class aircraft platform. Integrated flight test evaluation will focus on demonstration and assessment of quote mark in-flight quote mark operational performance of the Adaptive Engine Exhaust Suppression prototype conceptual hardware. 4.0Performance Objectives and Technical Constraints 4.1Overall Concept of Operations This advanced concept development effort will focus on the development of advanced engine exhaust plume and engine hot metal signature suppression concepts which enable quote mark in flight quote mark selection of suppression modes. This effort will provide the means to configure the exhaust system for minimal performance decrement when signature suppression is not required ( i.e. - non threat environment), and switch to a high suppression effectiveness configuration, although be it higher engine performance loss, when maximum signature suppression is needed ( i.e. - threat laden environments). 4.2Threat Environment Advanced rotary wing aircraft will be required to operate in threat environments rich in sophisticated missile threat systems such as MANPADS and cuing EO/IR sensor systems. This is driving the thrust to significantly reduce the broad spectrum signature of airborne platforms in order to mitigate adversary engagement opportunities, impede the threat systems ability to detect, track the aircraft, while improving the ability of imbedded aircraft survivability equipment (ASE) to protect the aircraft. 4.3Operating Constraints (Current Technology Shortfalls) Current engine exhaust signature suppression systems are fixed mode systems and suffer from significant parasitic thermo / aerodynamic performance losses robbing the aircraft system of power and fuel efficiency. Also, since aerothermodynamics engineering tradeoffs are conventionally necessary to balance aircraft performance with signature suppression performance, the ultimate survivability of the integrated aircraft system is not as effective as it could be and thus survivability compromised. 4.4Desired Objective Capabilities 4.4.1Concept of Operation For conceptual purposes the adaptive suppression can be considered to be an ON or OFF system. Fundamentally when the suppression system is in the quote mark OFF quote mark configuration, the engine system will operate at maximum thermodynamic efficiency with absolute MINIMAL impact on power and fuel efficiency - thus maximizing the aircraft's payload and range capability. In the quote mark ON quote mark configuration adaptive suppression system shall aeromechanically reconfigure the exhaust flow path with a twofold operational objective. First, in the adaptive configuration the system shall perform achieve significant reduction of the engine exhaust gas temperature prior to entering unconstrained flowfield around the aircraft. Second, the adaptive suppression system shall be structured to control direct exposure to quote mark hot quote mark components. Surface exposure control shall assume viewability from all tactical exposure aspect angles. 4.4.2Engine Performance Impacts The adaptive engine suppression shall induce a loss of no more than 0.5% increase fuel consumption across the power spectrum while in the quote mark OFF quote mark condition and shall not exceed 4% while in the actuated quote mark ON quote mark configuration. As conventional engine exhaust suppression systems are utilized to provide engine bay cooling flow, the conceptual suppression systems shall be capable of maintaining adequate engine bay pumping in both configuration modes. For engineering design purposes, the adaptive suppressions system concepts will be derived around the baseline T700-GE-701D flow class engine with platform integration on a UH-60 or AH-64 class aircraft. A Government furnished T700-GE-701D engine will we utilized by the Government for Phase 2 static engine test and evaluation activities. 4.4.3Conceptual Air vehicle Integration Considerations The adaptive engine exhaust concept design shall take into consideration and assess the effects external integrated aerodynamic drag, momentum losses, etc may have a conceptual aircraft in both actuation modes. 4.4.4Scalability In an effort to fully exploit the benefits of an adaptive engine exhaust system across the spectrum of rotary wing aircraft platforms, the conceptual suppression systems shall utilize design concepts which are readily scalable and engineered for turboshaft engines between the 10 - 30 PPS size class engines. 4.4.5Non- Conventional Technology Considerations While the core area of interest focuses on advancement of more conventional aero / mechanical configurations, consideration will be provided for non- conventional or hybridized concepts such as innovative energy recuperative or recovery concepts, specialized material systems, etc. All concepts must however be shown to be shown to be meritorious from the standpoint of total signature suppression capability as well as fuel consumption / weight / power parametrics. 4.4.6Size and Weight While not to be specified at this time, concepts should be weight competitive with conventional suppression systems utilized on current fleet rotary wing aircraft systems and shall be minimally intrusive to the aerodynamically flow field around the aircraft. 4.5System Performance 4.5.1Mission Scenarios This effort will provide the means to configure the exhaust system for minimal performance decrement when signature suppression is not required (i.e. - non threat environment), and switch to a high suppression effectiveness configuration, although be it higher engine performance loss, when maximum signature suppression is needed (i.e. - threat laden environments). 4.5.2Compatibility and Interoperability In an effort to fully exploit the benefits of an adaptive engine exhaust system across the spectrum of rotary wing aircraft platforms, the conceptual suppression systems shall utilize design concepts which are readily scalable and engineered for turboshaft engines between the 10 - 30 PPS size class engines. Extrapolation of developed concepts towards adaptation to a quote mark common core quote mark system which could readily exploited by multiple aircraft system will be considered. 4.5.3Air vehicle and Human Interface Considerations For the purpose of the concept development and engineering performance evaluation, the suppression configuration modes may be tested in fixed, however, adjustable actuation presets. Ultimately the adaptive system shall be configured with interactive actuation mechanisms capable of reconfiguration between the quote mark OFF quote mark and quote mark ON quote mark configuration modes and shall be manually controlled. 5.0Application and Submission Information Call Specific: This call will use the Two-Step, White paper/Proposal Submission Process as described in Section 5.1 of the BAA quote mark Solicitation Number: W911W6-15-R-0004 quote mark and as further supplemented below: 5.1Due Date for White Papers: White Papers are due 6 April 2015 by 2:00 P.M., EST. Submissions shall be marked with the Solicitation call number W911W6-15-R-0009 and shall be submitted to the Army Contracting Command, Aviation Development Directorate, Aviation Applied Technology Directorate, ATTN: CCAM-RDT Elizabeth (Beth) Jackson, 401 Lee Boulevard, Fort Eustis, VA 23604-5577. Facsimile and electronic white papers/ proposal submission is not authorized under this BAA. Proposals submitted after the closing date will be handled in accordance with FAR 52.215-1, Instructions to Offerors - Competitive Acquisition. Offerors can contact ADD-AATD to ask for solicitation clarification. All questions must be emailed to the Contracting Officer at elizabeth.a.jackson.civ@mail.mil. Questions received less than one week prior to the proposal receipt date may not be addressed. Oral explanations or instructions given before the award of any agreement/contract will not be binding. Any information given to a prospective Offeror concerning this BAA, which is necessary in submitting an offer or the lack of which would be prejudicial to any other prospective Offeror(s), will be published as an amendment to this BAA. Offerors should be alert for any amendments to this BAA. 5.2Two-Step, White paper/Proposal Submission Process A Call using the two-step white paper/proposal submission process will require interested parties to submit a white paper for Government evaluation. For those white papers the Government evaluates as being scientifically meritorious and affordable, the Government will invite the offeror to submit a full proposal. The request may ask for either a portion of the proposed research effort or the full effort based upon the Government's evaluation of the white paper. 5.2.1First Step. Individual Calls will establish the desired research and development topics along with a date for submission of a white paper. Each white paper shall address only a single topic area and proposed research effort. Offerors may submit more than one white paper, but as stated each white paper can only address a single proposed research effort. The white paper shall follow the following format: Paper size: 8.5-by-11-inch paper Spacing: Single-spaced Margins: One-inch margins Font: Times New Roman, not smaller than 12 point Number of pages shall be limited to 10 pages including text and graphics. Sources can include a one page cover letter that will not count towards this page limitation. Pages in excess of the page limitations will not be read or evaluated. 5.2.2Second Step. Upon completion of Government evaluation of the white papers, the Government will request full proposals from only those offerors whose white papers were evaluated as meritorious under the evaluation criteria and funding is anticipated to be available. The offerors that receive such a request for full proposals will provide a proposal that is consistent with the format specified in paragraph 5.2.2 and 5.2.3 of the Master BAA. The Government will only award upon determination that sufficient Government funding is available and agreement with the offeror upon an acceptable technical approach, terms and conditions, and an affordable cost. 5.3Period and Place of Performance. The period of performance for this effort will not exceed 20 months from the date of contract award. All engineering design, analysis, and prototype manufacturing will be performed at the contractor-designated site(s). Phase 2 activities involving operational testing of prototype suppression system hardware will be conducted at the Government's Countermeasures Test Facility located at Fort Eustis, Virginia. The Government will provide test cell facilities (including a T-700 engine and related support), test cell instrumentation data acquisition (pressure, temperature, and radiometric) and nominal integration support. Anticipated award for the Phase 1 and 2 activities is expected during 4th quarter of Government FY14, subject to the availability of funds. 5.4Funding. Award of selected concept proposal(s) will be subject to availability of funds. The Government anticipates multiple awards of phase 1 and phase 2 design, fabrication, and test efforts, however, reserves the right for awards to only one or none, based upon the technical merit and affordability of received technical proposals. The government anticipates fully funding the Phase 1 and 2 efforts under FY-15 6.2 RDT&E funding and have estimated a contract execution cost $1,188,400 per contract action. The Government prefers Offerors propose a Technology Investment Agreement (TIA) (Cooperative Agreement in accordance with 10 U.S.C 2358) and Chapter 1, Subchapter C of Title 32, Code of Federal Regulations Section 37 (Reference (b)) and Chapter XI of Title 2, Code of Federal Regulations (Reference (c)), which is more flexible than traditional Government funding instruments. This does not preclude other funding instruments from being used. A variety of funding instruments are available pursuant to this announcement depending upon the proposed effort, the entity submitting the successful proposal(s), and statutory and regulatory requirements the Government must satisfy. Such instruments include conventional Cost-Plus-Fixed-Fee (CPFF) contracts subject to the Federal Acquisition Regulation, as supplemented. Other Transaction (OT) for Research (10 U.S.C. 2371) is also an acceptable funding instrument. TIAs are more flexible than traditional Government funding instruments. 10 U.S.C. 2371 requires recipients to cost share at least 50% of the estimated cost of OTs. For TIAs or OTs, it is DoD policy to obtain, to the maximum extent practical, cost sharing of at least half the cost of the project to ensure the recipient has a vested interest in the project's success. Cost participation may be in the form of cash or in-kind contributions, where cash is considered of significantly higher quality in demonstrating commitment to the project. Cost participation will be considered in accordance with the 32 CFR CH I, Section 37.530. No fee or profit is allowed with this type of instrument. The type of funding instrument is a subject for negotiation, but the Offeror's desire shall be clearly stated in the cost proposal. The Government reserves the right to select for award all or part of any proposal received. Partial awards are conditioned upon the Government and the offeror reaching mutually agreeable terms for such partial awards. 5.5Required Government Facilities, Property, and Data. Identify, other than Government aircraft and test facilities any required Government data, test facilities, and/or property to support the proposed research effort. 5.6Security. Contractors interested in participation in this effort must either have a facility clearance or be able to obtain one. Dependent upon the nature of the technologies identified to address the signature reduction objectives a DD 254 may be required for support of design and analysis activities, however, shall be required in the event Phase 3 efforts are pursued. Access to or generation of classified data will be limited to Secret. The Joint Multi-Role (JMR) Technology Demonstrator Security Classification Guide will be utilized for those design and analysis activities requiring classification oversight. 5.7Data Rights The Government desires, quote mark Unlimited Rights quote mark, but at a minimum requires, quote mark Government Purpose Rights quote mark as defined by DFARS Part 227, to all technical data, deliverables, and computer software developed under this program, and no limitations on the use of delivered and/or residual hardware. It is the Offeror's responsibility to clearly define the proposed data rights for technical data, computer software and each deliverable. Ambiguities will be negatively evaluated against the Offeror. 5.8Minimum Required Reporting and Deliverables Any award will require, as a minimum, the following data items or deliverables: (1) Program Management Plan, (2) Bi-Monthly Progress, Cost and Performance Reports, (3) Final Report, (4) Final Briefing Charts (5) Design Review Briefing Charts, (6) Test Plans, (7) Test Reports, (Note: Each of these items shall be delivered in the Offeror's format). Any award under this announcement will require a kickoff meeting following award. All awards will include a requirement to present the results of the work in a final briefing at Ft. Eustis, Virginia upon completion of all technical effort. 6.0Evaluation Criteria The evaluation criteria outlined in BAA, W911W6-15-R-0004, paragraph 6.1 will not be used. The criteria outlined below will be used for this call. The selection of proposals will be based on a peer/scientific review of proposals (both technical and cost as it relates to technical effort) in accordance with the criteria set forth in this section. Proposals will be evaluated on their own merit without regard to others submitted under this announcement. The five evaluation criteria below are of equal weight. Criterion I: The extent to which affordable, comprehensive, efficient, and innovative technologies are proposed within the technology area to satisfy the program objective and BAA requirements. This will include understanding of the problem, current technical barriers, and how the proposed solution eliminates those barriers. Criterion II: The merit of the Offeror's proposed approach to develop and demonstrate the proposed technologies. This includes the reasonableness of the tasks, schedule, and approach to accomplish the proposed technical objectives. Criterion III: The benefit of the proposed technologies and the potential for transition to future and current Army rotary wing aircraft. This includes a clear and reasonable path to implementation of the technology, and the efficiency (e.g. weight, engine aero/thermodynamic performance as well as potential aircraft system performance attributes) of the proposed technologies. Factors affecting transition of the technologies (e.g. Engine power class limitation, aircraft platform integration factors/limitations, and potential signature reduction / susceptibility reduction capabilities) will be evaluated. Criterion IV: The capability of the Offeror to accomplish the proposed effort. This includes the experience and qualifications of the proposed personnel, the suitability of the proposed facilities, and the availability (or the ability to generate) of required technical and test data to validate the technology. Criterion V: The reasonableness and realism of the proposed cost to the Government. The proposed cost will be analyzed to determine whether the proposed cost elements (man-hours, labor categories, materials, travel, and other costs) are realistic for the work to be performed; reflect a clear understanding of the requirements; and are consistent with the unique methods of performance and materials described in the Offeror's technical proposal. Reasonableness of the proposed costs, in their nature and amount, will be evaluated against what would be prudent in the conduct of competitive business. The degree to which the offeror is willing to engage in TIA contractual arrangement with the government will be considered. The Government reserves the right to select for award all or part of any proposal received. Partial awards are conditioned upon the Government and the offeror reaching mutually agreeable terms for such partial awards. 7.0Other Information A draft TIA format is attached with this call. 7.2 Export Control Considerations Performance will require access to and/or generation of technical data the export of which is restricted by the Arms Export Control Act (Title 22, U.S.C., Sec. 2751 e t. seq.) or the Export Administration Act of 1979, as amended, Title 50, U.S.C. App. 2401 et. seq. Prior to award, the successful offeror will be required to provide an Export-Controlled DoD Data Agreement certification number issued in accordance with DoD Directive 5230.25. This certification number may be requested from the Defense Logistics Services Center, ATTN: DLSC-FBA Federal Center, Battle Creek, MI 49017-3084, Telephone 1-800-352-3572. Pre-award access to or submission of a classified proposal is not authorized. This Announcement is limited to U.S. firms as Prime Contractors. 8.0Government Furnished Equipment/Information/Property A Government furnished T700-GE-701D engine will be provided and utilized by the Government for static engine test and evaluation activities. Testing activities will be executed at the Government's test facility at Ft. Eustis, VA with contractor/recipient providing technical support. Appropriate and sufficient engine technical operation and interface data to support aero/thermodynamic design of the suppression system and its interface to the engine and test facility will be provided to any successful offeror.
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