Department of the navy (don) 18. 1 Small Business Innovation Research (sbir) Proposal Submission Instructions introduction

3. Crow, D. & Coker, C. “Composite hardbody and missile plume (CHAMP 2001) IR scene generation program.” Proc. SPIE 4366, Technologies for Synthetic Environments: Hardware-in-the-Loop Testing VI, 31 August 2001, 320; doi:10.1117/12.438080. http://proceedings.spiedigitallibrary.org/proceeding.aspx?articleid=948312

4. Listing of JANNAF-sponsored Signature Models: https://www.jannaf.org/products/codes

5. Niple, Edward R. “General scattered light (GSL) model for advanced radiance calculations.” Proc. SPIE 2469, Targets and Backgrounds: Characterization and Representation, 2 June 1995, 197; doi:10.1117/12.210591

KEYWORDS: Rotorcraft; Infrared Signature Model; Lidar Signature; Rotorcraft Plume; Plume Impingement; Downwash

TECHNOLOGY AREA(S): Air Platform, Battlespace

ACQUISITION PROGRAM: PMA 272 Tactical Aircraft Protection Systems

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the Announcement. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws.

OBJECTIVE: Develop a high-efficiency, lightweight optical beam homogenizer that can operate in the mid-infrared spectrum.

DESCRIPTION: Fiber-optic cables can be used as a flexible, effective means for delivering high-power infrared (IR) laser radiation from a central high-power laser source and distributing it to dispersed locations on an aircraft platform. Such beam delivery systems are highly desirable and critical for current and future Navy applications. The typical intensity distribution from standard multi-mode fiber optics contains spatial frequency components that are undesirable for many applications. Such applications require, or benefit significantly from, a “Top Hat”/“Flat-top” far-field intensity distribution, wherein uniform illumination can enable advanced system capabilities.

The Navy desires development of a fiber optic beam homogenizer that can be attached to the output of a standard multi-mode fiber operating throughout the IR spectrum (.900 micron thru Mid-IR) and that operates with 95 – 97% optical efficiency to produce a “Top Hat” illumination profile in the far field. The proposed equipment must be able to withstand the environment as specified in MIL STD 810G [Ref 5] experienced by high-performance, maritime aircraft such as the H-60 or F/A-18, while maintaining the ability to operate at multi-Watt optical power levels.

A uniform intensity distribution of a laser beam is usually required by many applications such as optical information processing, precise measurements, laser radar, additive manufacturing, etc. Laser beams from most sources are Gaussian-like in nature, which limits their ability to form a uniform irradiation pattern. A Diffraction Optical Element (DOE) is desired for transforming a rotationally symmetrical Gaussian-like beam into a nearly diffraction-limited flat-top beam profile.

Shaping a laser beam into a small flat-top with steep edges and no sidelobes is desired (e.g., Top-Hat). A beam homogenizer that could accommodate laser energy from a spectral window of 0.900 microns to less than 6.0 microns would be ideal; otherwise technical solutions for separate spectral regions will be considered that combine the capability in a single form factor. This design as a proof-of-concept should be optimized to handle greater than 10 Watts of IR laser radiation, with a spectral range of .9 to 6 microns. Respondents should detail their methods for accommodating the full spectral range.

Power handling capabilities of the beam homogenizer should accommodate tens of Watts of optical power from either a Continuous Wave (CW) or a modulated laser source. Sources are coupled to the homogenizer by either fiber or free space. The aggregate loss of the beam homogenizer should be less than 10%. Respondents should describe loss modalities of the beam homogenizer.

The laser source may be of multiple varieties, including but not limited to fiber, Quantum Cascade, Vertical Cavity Surface Emitting Laser (VCSEL). The laser sources will be linearly polarized with a linewidth that can be less than .001 microns. Respondents should describe how they will measure the beam profile and how to specify the flatness to top hat beam. The respondent should discuss the capability of its homogenizer to accommodate multiple spectral lines in a specific range, and the effects of changing the laser spectral input ±5% from a central wavelength with .001 linewidth. The proposed homogenizer should also be able to take variations in laser power input, and should be able to work under high power without damage during operation.

PHASE I: Design, develop and demonstrate feasibility of an optical beam homogenizer that meets the requirements and specifications as outlined in the Description section. The Phase I effort will include the development of prototype plans for Phase II.

PHASE II: Further develop and fabricate the prototype optical beam homogenizer designed in Phase I. Perform a demonstration of a prototype system in a test or lab environment that can measure and validate the requirements and specifications listed in the Description including, but not limited to power, linewidth, spectral range, and illumination profile.

PHASE III DUAL USE APPLICATIONS: Perform final testing and update the design according to results obtained from lab and field testing; incorporate findings from test results gathered in an operational environment, if available. Transition the optical beam homogenizer to appropriate Navy platforms and for commercial use. The commercial sector can use fiber-optic beam delivery with engineered illumination for several applications, including but not limited to advanced chemical sensors, environmental monitoring, communications, material cindering, additive manufacturing, and cutting.

REFERENCES:

1. Dickey, F. and Holswade, S. “Nearly Diffraction-Limited Size Flat-top Laser Beam.” Proceedings of SPIE, Laser Beam Shaping, Volume 4095, 2 August 2000. http://proceedings.spiedigitallibrary.org/proceeding.aspx?articleid=916060

2. Hendriks, A., et al. “The generation of flat-top beams by complex amplitude modulation.” Proc. of SPIE, 2012, Vol. 8490 849006-1. https://webcache.googleusercontent.com/searchq=cache:Sz9eIgQTBbEJ:https://researchspace.csir.co.za/dspace/bitstream/handle/10204/6219/Hendriks_2012.pdf%3Fsequence%3D1+&cd=2&hl=en&ct=clnk&gl=us

3. Linang, J. “1.5% Root-Mean-Square Flat-Intensity Laser Beam Formed using a Binary-Amplitude Spatial Light Modulator.” Applied Optics, 01 April 2009, Vol. 48, No. 10. https://www.osapublishing.org/ao/abstract.cfm?uri=ao-48-10-1955

4. Voelkel, V. and Weible, K. “Laser Beam Homogenizing: Limitations and Constraints.” Proceedings of SPIE, 25 September 2008, Volume 7102. http://spie.org/Publications/Proceedings/Paper/10.1117/12.799400

5. MIL-STD-810G, Environmental engineering considerations and laboratory tests. http://everyspec.com/MIL-STD/MIL-STD-0800-0899/MIL-STD-810G_12306/

KEYWORDS: Flat-Top; Top-Hat Beam Homogenizer; Mid-Infrared; Laser; Additive Manufacturing; Beam Shaping

N181-012

TITLE: Low Cost Persistent Environmental Measurement System

TECHNOLOGY AREA(S): Battlespace

ACQUISITION PROGRAM: PMA 290 Maritime Surveillance Aircraft

OBJECTIVE: Develop an air-launched persistent ocean environment measurement system that is capable of gathering and transmitting water column information at a low cost per profile.

DESCRIPTION: In order to properly model sensor performance, accurate year-round ocean environment data is required. Currently either a ship is deployed to make profile measurements or an expendable buoy is launched from an airborne platform to make a single profile measurement. Both of these methods are costly, on the order of thousands of dollars per measurement.

A persistent, profiling system is required to gather high-density measurements of the ocean environment. If a single system can perform hundreds of profiles over the course of many months, the cost per profile would be on the order of tens of dollars vs the current thousands of dollars. The Navy is well equipped to air deploy A-sized buoys anywhere in the world and therefore the profiling system will need to be rugged enough and of the proper form factor to be certified for airborne buoy launching systems. In general, the envelope of the system cannot exceed 4 7/8 inches in diameter and 36 inches in length, and the system must weigh less than 40 pounds. An example of the launch envelope and environmental factors for an existing air-launched A-sized buoy can be found in Reference 1.

Due to the diverse nature of the Navy’s sensor systems, a variety of environmental measurements are required, and therefore a modular approach should be taken when considering the incorporation of multiple instruments into the profiling vehicle. The profile measurements currently of high interest are temperature, pressure, salinity, and diffuse attenuation coefficient.

The depth profile, from near surface to 1,000 feet, measurement of interest is directional acoustic background noise, in the range of a few Hertz to a few kilo-Hertz. However, the priorities and needs will evolve over time and will require a flexible architecture so that individual sensors can be replaced with minimal non-reoccurring expenses.

Finally, the data taken by the profiling vehicle will need to be recovered remotely, and using Iridium or another worldwide communication system, processed and delivered to the Navy. A web-based methodology would help keep the per profile cost to a minimum.

PHASE I: Develop and demonstrate a system concept for an air-launched, persistent ocean environment measurement system that can remotely deliver profile measurements from near surface to 1000 feet to the Navy. Identify technological and reliability challenges of the design approach, and propose viable risk mitigation strategies. Develop modular measurement approach to ensure current and future flexibility. The Phase I effort will include the development of prototype plans for Phase II.

PHASE II: Design, fabricate, and test a prototype system and demonstrate open-water measurement capability with at least two different measurement types based on the design from Phase I. Work with the Navy to certify the prototype design for air-launch capability [Ref 1].

PHASE III DUAL USE APPLICATIONS: Produce multiple copies of the low-cost, persistent measurement system; produce multiple copies of the system with sensor variants; conduct in-situ testing and deliver data products. There are several potential commercial applications for this technology. The commercial fishing industry could use this tool to track ocean conditions favorable to the type of fish to be netted. The climate and weather prediction industry could use this tool to track evolving ocean conditions, a key factor for their analyses.

REFERENCES:

1. MIL-S-81478C Military Specification for AN/SSQ-57A http://everyspec.com/MIL-SPECS/MIL-SPECS-MIL-S/MIL-S-81478C_24751/

2. "Next-Generation Unmanned Undersea Systems." Defense Science Board Report, Oct 2016. http://www.acq.osd.mil/dsb/reports/2010s/Next-Generation_Unmanned_Undersea_Systems.pdf

KEYWORDS: Profile; Buoy; Persistent; Ocean Measurement; Water Column; Modular

TECHNOLOGY AREA(S): Air Platform, Space Platforms, Weapons

ACQUISITION PROGRAM: PMA 263 Navy and Marine Corp Small Tactical Unmanned Air Systems

OBJECTIVE: Develop a lightweight, compact, drop-in and highly efficient integrated fuel cell-based hybrid propulsion and power system.

DESCRIPTION: Navy energy action goals, as released by SECNAV [Ref 1], include developing more efficient systems, reducing greenhouse emissions, eliminating/reducing fossil-fuel usage, and increasing the use of alternative green energy sources in the fleet. Therefore, future power sources must extend operational range and lower maintenance cycles [Ref 2].

Currently, combustion engines that use petroleum fuels are relied upon to provide thrust and drive motors to propel the aircraft. The fuel-to-power conversion efficiency of the combustion process is low (i.e., can be as low as 15%), resulting in high fuel consumption and harmful gas emissions. The use of batteries is attractive as an alternative energy source for unmanned aircraft systems (UAS), where geometric limitations prohibit the use of combustion engines. However, their low energy density (less than 200 Watt-Hour/Kilogram) prevents the widespread use of battery power sources as the primary mover for the aircraft.

Fuel cell technologies (FCT) allow the reformation of jet fuel into hydrogen-rich gas, resulting in usable electric power with high conversion efficiencies (i.e., 60-70%). FCTs are solid-state devices with the following characteristics: high energy-density; clean fuel burn resulting in water, heat, and air as byproducts; contain no movable parts which enable quiet operations; maintenance free over the lifecycle; and are scalable. These characteristics translate to improved mission performance and warfighting capabilities, including potentially doubling endurance time to 44 hours in some cases, and reduced weight (<135 pounds) [Ref 3].

There are four key components in a fuel cell system: (1) reformer converting logistic fuel (i.e., JP-5/JP-8) into usable hydrogen (H2) gas; (2) fuel cell stack that produces electrical power output upon receiving a fuel such as H2 gas as an input; (3) balance-of-plant consisting of burners and heaters for combined heat and power to improve efficiency; and (4) electronic firmware with hardware components and software algorithms along with controls. There is a need for integrating the above key components to develop an integrated fuel cell system (IFCS) to leverage the full potential of fuel cell technologies. The current market lacks such IFCS that are highly dense (i.e., power and energy density), and operationally suitable for aircraft applications.

The goal is to develop a baseline IFCS that produces a minimum electrical power output of 0.5-1 kilowatt (kW). The design concept must be scalable up to 5-10 kW as well as be modular and plug-and-play in nature. Based on the fuel source, a polymer membrane (PEM) fuel cell or solid-oxide fuel cell stack can be used. The fuel cell stack must be fully compatible with current industry and state-of-the-art onboard (e.g., reformer and H2 storage system) and off-board hydrogen technologies (i.e., electrolysis). The developed IFCS must have a total weight threshold of 35 pounds (lbs) {15.9 kilograms (Kg)} with an objective of 19lbs (8.6Kg). The IFCS must also be fully compatible for Groups I-IV UAS vehicles [Ref 4].

The developed IFCS must be compatible with all current operational aircraft, electrical and environmental requirements [Ref 2, Ref 3], and must meet other requirements that include (but are not limited to) the following: sustained operation over a wide ambient temperature range (e.g., -40°C to +71°C), capability to withstand carrier-based shock and vibration loads, altitude range up to 65,000 feet per MIL-STD-810G [Ref 5], electromagnetic inference (EMI) up to 200V/m per MIL-STD-461F [Ref 6], and electrical power quality per MIL-STD-704 [Ref 7].

PHASE I: Develop a baseline IFCS that produces a minimum of 0.5-1 kW of electric power. Leverage modeling and simulation tools for proof-of-concept. Show feasibility for air vehicle integration to unmanned aircraft system. The Phase I effort includes the development of prototype plans for Phase II.

PHASE II: Build a prototype system that is compact and lightweight, and then demonstrate the functionality of the IFCS suitable for a UAS meeting its propulsion and power needs. Demonstrate the scalability of the IFCS to 10kW.

PHASE III DUAL USE APPLICATIONS: Fully develop a functional and airworthy IFCS with performance specifications satisfying the targeted acquisition requirements coordinated with Navy technical points of contacts. Complete testing per military performance specifications and transition to appropriate platforms.

Commercialize the fuel -cell and IFCS technologies. Leverage the advantage of scalable manufacturing processes to develop a cost-effective manufacturing process for technology transition to various system integrations for both DoD and civilian applications. The potential for commercial application and dual use is high. Beyond the Navy application, there are applications for electric vehicle, consumer portable electronics, and commercial aviation sectors.

REFERENCES:

1. Paige, Paula. “SECNAV Outlines Five Ambitious Energy Goals.” Navy News Service. 16 Oct 2009. Story Number: NNS091016-30. Corporate Communications ONR. http://www.navy.mil/submit/display.asp?story_id=49044

2. FY15 Navy Programs. RQ-21A Blackjack Unmanned Aircraft System (UAS). http://www.dote.osd.mil/pub/reports/FY2015/pdf/navy/2015rq21a_blackjack.pdf

3. Naval Air Systems Command-Small Tactical Unmanned Aircraft Systems. “RQ-21A Blackjack”. http://www.navair.navy.mil/index.cfm?fuseaction=home.displayPlatform&key=5909B969-2077-41C2-9474-C78E9F60798C

4. “Unmanned Aircraft System Airspace Integration Plan”, Version 2.0. Department of Defense UAS Task Force, Airspace Integration Integrated Product Team. March 2011. http://www.acq.osd.mil/sts/docs/DoD_UAS_Airspace_Integ_Plan_v2_(signed).pdf

5. MIL-STD-810G. “Department of Defense Test Method Standard: Environmental Engineering Considerations Laboratory Tests”. 31 Oct 2008. http://quicksearch.dla.mil/qsDocDetails.aspx?ident_number=35978

6. MIL-PRF-461F. “Department of Defense Interface Standard: Requirements for the Control of Electromagnetic Interference Characteristics of Subsystems and Equipment”. 10 Dec 2007. http://quicksearch.dla.mil/qsDocDetails.aspx?ident_number=35789

7. MIL-STD-704F. “Department of Defense Aircraft Electrical Power Characteristics” 30 Dec 2008. http://quicksearch.dla.mil/qsDocDetails.aspx?ident_number=35901

KEYWORDS: Compact; Lightweight; Power Dense; Integrated Fuel Cell System; Propulsion and Power; Unmanned Aircraft System

N181-014

TITLE: Controlled Payload Release Mechanism for Pyrophoric Air Expendable Decoy

TECHNOLOGY AREA(S): Air Platform, Materials/Processes

ACQUISITION PROGRAM: PMA 272 Tactical Aircraft Protection Systems

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the Announcement. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws.

OBJECTIVE: Develop and produce a controlled (timed) payload release mechanism for multiple stacks of pyrophoric foils in a single decoy device cartridge.

DESCRIPTION: Pyrophoric decoys are part of a family of advanced Infrared (IR) decoys designed for use by Department of the Navy fixed-wing and rotary-wing aircraft to successfully decoy advanced-threat missile systems in current and future operational environments. Pyrophoric decoys utilize a special, high surface area metal foil, which rapidly oxidizes when exposed to oxygen. When dispensed from the host aircraft, the special pyrophoric alloy material payload reacts with air to emit intense IR radiation that is not visible to the naked eye. The IR radiation diverts or decoys IR-seeking missiles away from the host aircraft [Ref 1]. The current pyrophoric decoy is composed of pyrophoric iron coated onto steel foil. Several hundred pyrophoric foils comprise the payload of a typical decoy and are currently dispensed simultaneously from an airtight casing via the action of a single impulse cartridge which incorporates Hazard from Electromagnetic Radiation to Ordnance (HERO) Safe features. The Navy seeks a pyrophoric payload release mechanism that can either bind or contain multiple (3 or more) discrete sub-payloads of pyrophoric foils upon dispense from a device and then release the material in a controlled, timed manner such that multiple discrete bursts of infrared energy are produced from the dispense of a single cartridge. The candidate mechanism should not be susceptible to HERO within the sealed aluminum cartridge; should make efficient use of volume as the total volume available for payload is approximately 5 inches in length by approximately 1.3 inches in diameter; should utilize the force and/or flame from the CCU-136 impulse cartridge to initiate the dispense/release sequence [Ref 2]; should function reliably after significant shock from the impulse cartridge; should provide consistent and controllable timed release of the pyrophoric material payload, and should be variable to optimize the timing of the release of the individual stacks of pyrophoric material.

Work produced in Phase II may become classified. Note: The prospective contractor(s) must be U.S. Owned and Operated with no Foreign Influence as defined by DOD 5220.22-M, National Industrial Security Program Operating Manual, unless acceptable mitigating procedures can and have been implemented and approved by the Defense Security Service (DSS). The selected contractor and/or subcontractor must be able to acquire and maintain a secret level facility and Personnel Security Clearances, in order to perform on advanced phases of this contract as set forth by DSS and NAVAIR in order to gain access to classified information pertaining to the national defense of the United States and its allies; this will be an inherent requirement. The selected company will be required to safeguard classified material IAW DoD 5220.22-M during the advance phases of this contract.

PHASE I: Design and demonstrate feasibility of prototyping and manufacturing a controlled payload release mechanism for application to multiple inert sub-payloads dispensed from a single decoy cartridge. The decoy cartridge must be a standard Navy round 36mm MJU-49/B decoy form-factor compatible with the AN/ALE-47 Airborne Countermeasure Dispenser System. The Phase I effort will include the development of prototype plans for Phase II.

PHASE II: Manufacture and demonstrate a representative prototype countermeasure payload release mechanism utilizing non-reactive payload material and Government-furnished reactive payload material in both ground tests and flight tests.