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A12-098




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Basic Information:

Title:	Multi-functional Integrated Drive System Sensor(MIDSS) for Rotorcraft
Program:	SBIR
Technology Area:	Electronics
Open Date:	5/24/2012
Close Date:	6/27/2012

Description:

This effort will develop a MIDSS capable of measuring strain, vibration, torque and temperature at multiple locations. The ability to provide complete measurement capability for an entire gearbox or set of shafts is desired. The MIDSS measurements should be of sufficient accuracy and sampling rates for monitoring of normal drive-train function, detecting and quantifying over-speed or over-torque conditions, and use in calculation of advanced drive train health indicators. The MIDSS needs to be capable of interface to cockpit displays as well as being fed to on-board monitoring systems. The effort should address the sensor requirements such as accuracy and resolution, networking or multiplexing capacity, reliability and fault tolerance. Oil debris or quality sensors would be difficult to incorporate within the system and are not required as part of the effort. Other desired attributes to consider for Phase III are (1) impact per Mil-Std 810F, Method 516.5; (2) vibration requirements of Mil-Std 810F, Method 514.5; (3) acceleration per Mil-Std 810F, Method 513.5; (4) altitude per Mil-Std 810F, Method 500.4; (5) rain per Mil-Std 810F, Method 506.4; (6) fungus per Mil-Std 810F, Method 508.5; (7) humidity per Mil-Std 810F, Method 507.4; (8) salt spry/fog per Mil-Std 810F, Method 509.4; (9) sand/dust per Mil-Std 810F, Method 510.4; (10) fluid susceptibility per Mil-Std 810F, Method 504; and (11) electromagnetic interference (EMI) per Mil-Std 461E as modified by ADS-37A-PRF Table 1.

Objective:

The objective of this SBIR is to develop a Multi-functional Integrated Drive System Sensor (MIDSS) capable of measuring multiple parameters critical to the operation and health of a rotorcraft drive train.

Phase I:

Phase I of the effort will prove the feasibility of the proposed technology approach. Phase I will develop the technology sufficiently to prove the ability to integrate the required measurement capabilities and implement a MIDSS. The effort should address the monitoring requirements for a representative drive system component. The technical viability of the various sensors, as well as any associated digitization and multiplexing should be demonstrated at a bench test level. The source of data needed for the selected drive system component as well as any performance, usage or diagnostics models should be addressed. An aircraft level architecture and a roadmap for implementation should be defined under this phase. The architecture must address integration with existing aircraft Health and Usage Monitoring Systems (HUMS).

Phase II:

Phase II will develop the Phase I technology into a fully functional prototype. The MIDSS will be tested to assess the accuracy of the measurement capabilities as well as an aircraft level architecture. Individual sensor testing will be conducted along with the ability to combine multiple sensor locations covering the entire aircraft drive system.

Phase III:

The technology is applicable to both military and commercial rotary wing aircraft (qualified to military standards listed in description) to monitor components and performance in real time. This technology will be used on high value and flight safety critical drive system components. The MIDSS will alert the user to component(s) stressed beyond their intended boundaries. The reduction of the wire weight and number of sensors will prove to be very beneficial. As this technology matures it can be transitioned to non-aircraft applications such as gearboxes used in the wind energy industry.

References:

1. MIL-STD-810F, DOD Test Method Standard for Environmental Engineering Considerations and Laboratory Tests, 1 January 2000. 2. MIL-STD-461E, DOD Interface Standard Requirements for the Control of Electromagnetic Interference Characteristics of Subsystems and Equipment, 20 August 1999. 3. ADS-37A-PRF, Electromagnetic Environmental Effects (E3) Performance and Verification Requirements, 28 May 1996. 4. ADS-79A-HDBK, Aeronautical Design Standard Handbook for Condition Based Maintenance Systems for US Army Aircraft Systems, 17 December 2009

SBIR Keywords

Rotary Wing, Drive Systems, fiber optic, micro-electro-mechanical systems (MEMS), Health and Usage Monitoring Systems (HUMS)

TechMatch Keyword(s):

Aviation Technology

Aeronautics and Aerodynamics

Aircraft Components

Aircraft Equipment

Aircraft Damage Assessment

Displays

Integrated Diagnostics

Maintainability and Reliability Improvements

Performance Improvement

Computer Systems

Information Technology

Detection and Countermeasures

Acoustic Detection

Infrared and Ultraviolet Detection

Radio frequency Detection

Manufacturing Technology

Quality Control and Reliability

Sensors

Engineering

Mechanical

Test Equipment and Systems

DISCLAIMER:

The Solicitations listed on this site are copies from the various SBIR agency solicitations and are not necessarily the latest and most up-to-date. For this reason, you should use the agency link listed below which will take you directly to the appropriate agency server where you can read the official version of this solicitation and download the appropriate forms and rules. The Official Website can be found at: http://www.acq.osd.mil/sadbu/sbir/solicitations/index.htm