BAA-RQKPD-2015-0001-Call6-NOCA.pdf

Broad Agency Announcement (BAA) BAA-RQKPD-2015-0001 Notice of Contract Action (NOCA)

COMPOSITE AIRFRAME LIFE EXTENSION (CALE)

BROAD AGENCY ANNOUNCEMENT TITLE: CERTIFICATION OF COMPOSITES –

COMPOSITE AIRFRAME LIFE EXTENSION

BROAD AGENCY ANNOUNCEMENT TYPE: This is a NOCA for Call #0006 to the Broad Agency Announcement

BROAD AGENCY ANNOUNCEMENT NUMBER: BAA-RQKPD-2015-0001

TOPIC TITLE: “Predicting Airframe Stresses due to Differential Thermal Strains”

TECHNICAL POC: Dick Holzwarth, AFRL/RQVS, Phone 937-656-8825, email:

richard.holzwarth.1@us.af.mil.

CONTRACTING POC: Susan Lee, (Primary), Contracting Officer, (937) 713-9945, email:

susan.lee.1@us.af.mil; Jodi Alvarez, (Secondary), Contracting Officer, (937) 713-9966, Email:

jodonna.alvarez@us.af.mil. Mailing address: AFRL/RQKPC, Bldg. 45, Area B, 2130 8th St., Wright-Patterson AFB, OH 45433-7801

NOTICE:

This is a Notice of Contract Action (NOCA) informing potential offerors of the upcoming sixth call for the Composite Airframe Life Extension (CALE) BAA-RQKPD-2015-0001. Call #0006 will be titled - Predicting Airframe Stresses due to Differential Thermal Strains. This will be a One-step Call. As such, a full technical and cost proposal will be requested from the upcoming Call announcement.

This notice begins the timeframe required by FAR 5.203(e). The AF anticipates releasing Call #0006 for a period of no greater than 45 days. Do not submit any documentation at this time.

Offerors should continue to monitor fbo.gov and grants.gov for the Call and any BAA or Call amendments.

OBJECTIVE:

The objective of the Call is to develop and demonstrate a method of predicting stresses that develop in structural assemblies of airframe materials having significantly different Coefficients of Thermal Expansion (CTE) when subjected to significant temperature change. Of particular interest to this effort is the joining of advanced composite structure to aluminum structure via mechanical fasteners.

The temperature range of interest is from approximately -70F to approximately 300F, but there are no absolute requirements for temperature range or number of temperature cycles. The specific composite material types and the specific aerospace aluminum and titanium alloy are free for the proposer to select subject only to the requirement that they be those of the identified baseline structure. Said simply, the materials of interest are those of the selected baseline, and the temperature range of interest is the operating environment of the selected baseline aircraft.

mailto:Pat.Marshall@wpafb.af.mil mailto:Pat.Marshall@wpafb.af.mil mailto:susan.lee.1@us.af.mil

The contractor is encouraged to select a baseline structure that represents multiple, contemporary USAF aircraft for this demonstration program.

The contractor shall select a baseline structure, which will be used to both develop and validate the analysis methods developed within this program. The objective of the baseline is to provide both a realistic source of design requirements for wide ranging operational stresses, from maneuver and thermal conditions, and to provide a framework for assessment of the validity of the analysis methods developed through testing. The baseline structure shall be some section of a currently in-service aircraft, and it shall contain at least one mechanically fastened joint joining an advanced composite structural element to an aluminum structural element. Key features of the baseline should be: The structure should include structural elements of advanced composite structure and metallic structure joined together using multiple mechanical fasteners of any type.

The structure should be exposed to significant temperature extremes during operation. These variations may be: global (entire structure sees the same temperature variation); local (at least one part of the structure contains a “hot spot” that results in a different time-temperature variation profile); gradient (the entire structure experiences a temperature variation, but the temperature variation itself varies as a function of location); or a combination such conditions.

The structure should represent structural configurations common to existing and anticipated future aircraft, and experience loading conditions commonly seen during aircraft operations. As much as possible within the baseline, a mix of fastener types is encouraged, as is a mix of loose fit, net fit, and interference fit tolerances. Other characteristics that may be desirable for the technology demonstration effort, but are not strictly required, include, but are not limited to;

multiple metal alloys, including mechanical joints between dissimilar metals (eg, aluminum fastened to titanium) and bonded structural joints between any type of structural material. The physical size of the baseline structure is free with respect to all linear dimensions, weight, and volume, but the offeror is cautioned that the structure should be large and complex enough for significant thermal excursions to produce complex thermal strains and resultant stresses representative of major aircraft structure.

PROGRAMATIC

A Cost-Reimbursement/Fixed Fee contract type is contemplated with one $1,400,000 award for a 18 month effort, 15 months for the technical effort and 3 months for the final report.

The anticipated amount is an estimate only and is NOT a promise of funding. Funding is uncertain and is subject to change. Changes in availability occur at the discretion of the Government.

DO NOT SUBMIT ANY DOCUMENTATION AT THIS TIME. THIS IS NOT A CALL FOR

WHITEPAPERS OR PROPOSALS.