Army 17. 1 Small Business Innovation Research (sbir) Proposal Submission Instructions

PHASE I: This phase will focus on determining the technical feasibility to develop materials and/or methods to measure force and strain on individual parachute suspension and control lines. Multiple methods to measure dynamic forces exerted on parachute suspension and control lines during deployment and static state should be investigated to determine suitability for use in an airdrop environment. The smart lines shall be electromagnetic interference (EMI) shielded, lightweight, flexible, and durable to withstand parachute manufacturing, packing, deployment and recovery procedures. It is anticipated the lines incorporating developed materials or sensors will have similar performance, durability and service life expectancy characteristics as current lines with the additional benefit of being able to measure force and sustain an electronic network. Benchtop proof of concept demonstrations of the smart lines should be performed in a laboratory setting. The demonstration should show the strain range and capability of the system. Concepts should be provided for the development of a prototype system useable on small and mid-scale ballistic and ram-air parachute systems. Phase I deliverables include a final report detailing all procedures employed in the research, all results of tests conducted, all potential technologies reviewed and functional material samples or small scale prototypes (if applicable) as well as a detailed description of materials, processes and associated risk for the proposed Phase II effort and a recommended path forward.

PHASE II: During Phase II, further development of the concepts derived in Phase I should be pursued with the ultimate goal to demonstrate the smart cords on a full-scale parachute system deployed from an aircraft. Provide a detailed plan to test and validate Phase I designs. Produce 10 full-scale, prototype smart cord systems for use on either cargo or personnel parachutes in the sub-500lb. weight class. Demonstrate operation of the prototype systems in a relevant environment. This would entail releasing the system from either a fixed or rotary wing aircraft to assess airworthiness in the airdrop environment and quantify usability. Repeat testing of the prototypes will be conducted to assess the operational life of the system and validate durability in an airdrop environment. Partnerships between companies with electro textile knowledge and those with experience manufacturing and developing military parachutes is encouraged. In addition to the delivery of full-scale prototype systems, a report shall be delivered documenting the research and development supporting the effort along with a detailed description and specification of the materials, designs performance and manufacturing processes. A full drawing package including all 3D CAD models, schematics, wiring diagrams, etc. should be provided with the final report.

PHASE III DUAL USE APPLICATIONS: The initial use of this technology will be to collect information about forces exerted on parachute lines during military airdrop. This information could be applicable to both military and civilian applications that utilize load-bearing textiles to determine when a particular cord, line or rope has reached the end of its usable life. Smart cords could enable longer service lives by extending the time in service of lightly used cords, lines or ropes beyond the standard “service life models’ used presently.

REFERENCES:

1. Favini, E; Niemi, E; Niezrecki, C; Willis, D; Chen, J; Desabrais, K; Charette, C; Manohar, S. (2011) Sensing Performance of Electrically Conductive Fabrics and Suspension Lines. May 23, 2011; doi: 10.2514/6.2011-2512 (uploaded in SITIS on 11/30/16).

2. Military Specification, MIL-C-5040H, CORD, FIBROUS, NYLON https://www.milspecmonkey.com/materials/MIL-C-5040H(550cord).pdf

3. JPADS Ultra Light Weight-http://nsrdec.natick.army.mil/media/fact/airdrop/JPADS%20ULW.pdf

KEYWORDS: force sensor, strain measurement, parachute, instrumentation, airdrop, smart textiles, cord, suspension lines, nylon, polyester, spectra, braid

TECHNOLOGY AREA(S): Air Platform

OBJECTIVE: Develop an instrumentation system to measure and record the on-board continuous strain field in a parachute canopy during inflation and once it is fully inflated

DESCRIPTION: Traditionally, parachutes are developed through full-scale flight testing which is a time consuming and expensive process. Advanced computer models are being developed by the US Army Natick Soldier Center to simulate airdrop systems in order to provide a resource for early evaluation and initial development of airdrop systems. These computer models require validation against test data to ensure accurate prediction results from the simulation. The validation of the parachute canopy structural dynamics in the simulation would be greatly aided by detailed knowledge of the temporally evolving strain field in the canopy as the parachute inflates and once the canopy is fully inflated and falling/gliding under steady descent.

In addition, guided airdrop systems rely on control systems which use the dynamic characteristics of the canopy and airborne guidance units to navigate to a predetermined ground location. Sensors provide feedback which serve as critical inputs to the control system, and as such have a direct impact on system efficiency and accuracy. If the control systems could also include information about the temporally evolving strain field in the canopy, then the ability to navigate airdrop systems would be significantly enhanced.

The intent of this solicitation is for the development of an instrument or sensor system which measures the fabric strain over large portions of the canopy surface, up to and including the entire surface of the parachute canopy, either as a continuous two-dimensional field measurement or at a sufficient number of discrete points such that the single point measurements could be extrapolated to obtain an accurate representation of the continuous field. By having the capability to measure the strain over the entire surface, a complete strain field can be obtained for a thorough comparison with the numerical simulation ensuring a more complete validation of the simulation. If the strain measurement system were used in a parachute development program, then regions of high strain in the canopy could be identified allowing the parachute designer to take measures to reduce the strain in those regions thereby reducing the chance of structural failure. After a number of drops the cumulative effect of the strain data would also provide life-cycle and sustainment data to assist in the determination of future system procurement decisions.

PHASE I: During Phase I, a feasibility demonstration of the strain measurement system should be provided in a laboratory on various samples of parachute fabric. The demonstration should show at a minimum the: 1) measurements of strain in the range of 2%-25% and 2) frequency response capability of the system. Concepts should be provided for the development of a prototype system useable on small and mid-scale ballistic and ram-air parachute systems. Wind tunnel testing to determine the fidelity of the system to document material responses induced by relevant air flows may be appropriate. Deliverables desired include a Final Technical Report documenting the research and development supporting the effort along with a detailed description of testing apparatus and processes. In addition, an analysis, as appropriate, of the cost-to-accuracy ratio should be addressed to gauge the current state of the technology for this application and the potential transition of the technology to the airdrop application.

PHASE II: During Phase II, a prototype system should be developed for demonstration of the system on mid-scale parachutes initially and then developed for deployment on full-scale parachute systems. The ultimate goal is to measure the strain on a full-scale parachute system deployed from an aircraft. The successful demonstration would include repeatable data collection supported by validation against wind tunnel testing or other experimental data sources. It is desired that a live demonstration from an aircraft be performed. Deliverables desired include a Final Technical Report documenting the research and development supporting the effort including specification of design performance. Also desired is one complete prototype system for use on full-scale systems.

PHASE III DUAL USE APPLICATIONS: A successfully developed system would be used as a tool to acquire data for the validation of numerical computer models of parachute systems. A properly validated computer model will be used to expedite and decrease the costs associated development and improvement of parachute systems. The development of a strain measurement system is a critical tool needed to aid in the validation of these numerical parachute models. A strain measurement system capable of measuring the strain in a large flexible fabric could be applied to numerous structures and objects such as tents or clothing. The device would also make it possible to test and measure strain in other textile objects such as webbing used to secure loads on trucks or in aircraft, airbag systems, kites, or sails. Non-aerodynamics applications may include water/liquid flexible membrane/material measurements. The successful transition from SBIR research to an operationally capable system would require the refinement of the prototype systems developed during Phase II to a user-friendly, turn-key commercial instrumentation system.

REFERENCES:

1. Thomas W. Jones, James M. Downey, Charles B. Lunsford, Kenneth J. Desabrais, and Gregory Noetscher, “Experimental Methods Using Photogrammetric Techniques for Parachute Canopy Shape Measurements,” paper AIAA 2007-2550, AIAA Balloon Systems Conference, Williamsburg, VA, 21-24 May, 2007. (Uploaded in SITIS on 11/30/16.)

2. P. M. Wagner, "Experimental measurement of parachute canopy stress during inflation", Wright -Patterson Air Force Base Technical Report No. AFFDL-TR-78-53, May 1978, Ohio 45433 http://oai.dtic.mil/oai/oai?verb=getRecord&metadataPrefix=html&identifier=ADA058474

3. Tony J. Ragucci, Alan Cisar, Michael L. Huebschman, and Harold R. Garner, “Film Strain Measurement through Hyperspectral Polarimetry,” paper AIAA 2007-2619, AIAA Balloon Systems Conference, Williamsburg, VA, 21- 24 May, 2007. (Uploaded in SITIS on 11/30/16.)

4. Mattman, C., Clemens, F., and Tröster, “Sensor for Measuring Strain in Textile,” Sensors, 2008, ISSN 1424-8220, www.mdpi.com/1424-8220/8/6/3719/pdf

KEYWORDS: strain, measurement, fabric, parachute, instrumentation, airdrop, fiber, stress, canopy

TECHNOLOGY AREA(S): Human Systems

OBJECTIVE: Develop and demonstrate a controllable 3D food printer incorporating an effective paste-delivery system with positive displacement technology (such as by pneumatic, peristaltic or progressive cavity pumps). This system must be food-grade and enable smooth printing of multicomponent consumable items, without clogging/fouling of the print head. System interface must be sufficiently user-friendly such that an untrained Soldier could operate the printer.

DESCRIPTION: There would be a great benefit to nourishing soldiers who are in isolated small units (i.e., Forward Operating Base (FOB)) or who require specialized diets (i.e., in field hospitals) by offering sustenance that is on-demand and tailored to individual requirements and needs. An innovative solution is 3D printing, which can provide tailorable ration components that fulfill individual preferences and nutritional needs. Printable ration components, in forward operating base camps for example, can be produced by pre-provisioned ingredients that are stockpiled and ready to use. Such technology also reduces unit waste and can improve the Soldier’s psychological and physical well-being and readiness, thus optimizing nutritional support for enhanced energy and cognition.

Using novel printing technologies, tailored food may be targeted to fulfill specific Soldier nutritional needs and menu preferences. Such ration items furthermore would not require storage, improving logistical demands as well as providing freshly-made high quality foods for the individual/unit; improvements in quality and fulfillment of preferences would increase consumption and consumer satisfaction. 3-D printing of on-demand ration components will in turn reduce packaging, transportation, and storage costs.

PHASE I: The goal of Phase I is to provide a feasibility demonstration of the 3D food printer and software to demonstrate the technical practicability (and user ease) of producing a formed, consumable food product. A demonstration 3D printed food prototype (i.e., such as an energy bar) is required as part of this Phase. The deliverables are thus: 1) a demonstration of the adapted food 3D printer with positive-flow delivery of at least two different product streams by separate print-heads; 2) the user-friendly interface; and 3) at least one demonstrated consumable multicomponent food product and formulation/process variables. Deliverables of this phase will include the Phase 1 report detailing the system, estimated production costs, and the written formulation(s) and process parameters for the test prototype.

PHASE II: Expand the system to allow thermal treating of the printed products. (1) Provide for in/post-processing cooking of formed products. (2) Provide for thermal treatment of the extruded stream during processing (i.e., by a targeted laser), thus facilitating “setting” of the product (facilitating build-up of successive layers). (3) Using technology currently available determine maximum throughput and optimize speed of the printer. Provide at least two multicomponent consumable prototypes produced from Phase II work, to include post-extrusion processing/setting, for technical and sensory evaluation. It is envisioned this printer could be used in a Force Provider (FP) modular kitchen that is restrictive in overall space. The FP modular kitchen consists of the same building blocks which allows for configuring appliances in different variations. Printer should be ruggedized for durability, with minimized weight and footprint, capable of printing multicomponent food in short duration, and electrically compatible with mobile military field kitchen power supplies. This system should be sufficiently mature for technical and operational testing, limited field-testing, demonstration, and display. Deliverables of this phase: 1) printer with all modifications; 2) software source code; 3) least two multicomponent consumable prototypes; 4) the Phase 2 report detailing the augmented system, written operating manuals, and the written formulations and process parameters for the test prototypes.

PHASE III DUAL USE APPLICATIONS: Refine 3D printing technology process and provide validation of results. Prove feasibility of technology for technology transition and commercialization through advanced testing and optimization of the process. Products and processes demonstrated under Phase I and Phase II will be used to improve comparable commercial items and may be used in more complex food systems.

The development of this technology will benefit all users by reducing logistics, costs, and weight while improve the quality of rations. Further, this technology may be applicable beyond military applications to NASA, Antarctic and disaster relief sites.

REFERENCES:

1. De Roos, B. 2013. Personalized nutrition: ready for practice? Proceedings of the Nutrition Society. 72(01), 48-52. http://unfoldfab.blogspot.com/2014/12/Unfold-Viscotec-Professional-Paste-3D-Printing.html

2. Jie Sun, Zhuo Peng, Weibiao Zhou, Jerry Y.H.Fuh, Geok Soon Hong, Annette Chiu; Procedia Manufacturing, Volume XXX, 2015, pages 1-12; A Review on 3D Printing for Customized Food Fabrication;

3. Modular Appliances to Dramatically Improve Field Feeding, US Army Homepage,

KEYWORDS: 3D Printing, Food printer

TECHNOLOGY AREA(S): Weapons

The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), which controls the export and import of defense-related material and services. Offerors must disclose any proposed use of foreign nationals, their country of origin, and what tasks each would accomplish in the statement of work in accordance with section 5.4.c.(8) of the Announcement.

OBJECTIVE: Develop Innovative technologies and/or methodologies that optimize the range and precision of current US mortar systems focusing on propulsion energy and aerodynamics.

DESCRIPTION: A mortar system by its very nature needs to be light weight, low cost, and maneuverable. This restricts the ability to fire at longer ranges with greater accuracy since firing range and accuracy are a function of the size and weight of the system (the bigger the system, the farther it shoots). Advanced technologies and methodologies have emerged that show promise in optimizing the launch and flight conditions of the mortar system to provide a more efficient sequence of launch and flight events (i.e. ignition of propellant, expansion of propellant gasses, travel of the mortar round up and out of the tube, ballistic flight, and terminal impact). Specifically, optimizing energies imparted on the munition within the launch tube can increase the propulsion forces to increase range. Similarly, aerodynamic and flight characteristics can be investigated and modified to increase range and precision. Major modifications to the weapon system could achieve the desired results, but that is not the intent of this topic. The objective is to investigate high payoff improvements to the current design, which will include: 1) detailed modeling of the launch and flight conditions noted above, 2) assessment of areas that can be optimized based on the models, and 3) identification and application of specific technologies or methodologies that will optimize performance. The analysis will include the expected payoff of the improvement in terms of percent range gained and decrease in dispersion expected. Since no major modifications to the weapon system are desired, it is expected that only minor changes will be required to the overall design of the mortar weapon and ammunition to accommodate these solutions, and that the weight of the system will not increase (and objectively will decrease). The final Phase II demonstration of the technology will be on the 120mm mortar to demonstrate at least a 20 percent increase in maximum range as well as a 20 percent decrease in dispersion (measured using Circular Error Probable (CEP) method). The operational environment for mortar systems is very demanding and includes the rough handling of the soldiers and extreme environmental conditions (as described in the latest version of MIL-STD-810), and high shock and pressure conditions during firing. Cost is also a key consideration, as the new technologies shall not significantly increase system cost. Detailed information regarding operational environment will be provided after award of the Phase I contract.

PHASE I: Perform detailed scientific analyses and modeling on the launch and flight conditions, and the feasibility of one or more approaches considering the operational environment, including detailed analyses of propulsion and energy transfer, and analysis of resulting product costs. Conduct laboratory studies/experiments as needed to demonstrate feasibility of the proposed solutions with respect to the range and dispersion metrics listed above. The result of Phase I will be a report citing 1) detailed modeling of the launch and flight conditions noted above, 2) assessment of areas that can be optimized based on the models, and 3) identification and prioritization of specific technologies or methodologies that can be applied to optimize performance.

PHASE II: Based on the results and recommendations of Phase I, produce actual models/prototypes that incorporate the selected high value solutions, and test in a simulated operational environment. Modify solutions as necessary based on test/demonstration results and retest. The final deliverable of Phase II will be prototypes with demonstrated improvements incorporated, as well as a report of the demonstration results with supporting data indicating and quantifying 1) the extended range capability as a percent increase of current maximum range, and 2) the decrease in dispersion from current CEP. The report will also include a scientific explanation of the underlying physical properties/characteristics that validate the demonstrated performance as predicted in Phase I.