Landing Gear Structural Health Prognostic/Diagnostic System

Award Information
Agency: Department of Defense
Branch: Navy
Contract: N68335-14-C-0084
Agency Tracking Number: N121-043-0366
Amount: $1,599,777.00
Phase: Phase II
Program: SBIR
Awards Year: 2014
Solicitation Year: 2012
Solicitation Topic Code: N121-043
Solicitation Number: 2012.1
Small Business Information
(ES3) Engineering & Software System Solution, Inc.
550 West C Street, Suite 1630, San Diego, CA, 92101
DUNS: 127283500
HUBZone Owned: N
Woman Owned: Y
Socially and Economically Disadvantaged: N
Principal Investigator
 Rob Huot
 SHM Lead Engineer
 (801) 928-2719
Business Contact
 Doug Wiser
Title: COO
Phone: (801) 928-2769
Research Institution
Landing gear systems are one of the more problematic subsystems on Naval aircraft. Landing gear failure can be caused by hard landings due to actual severe high sink rate with high enough GW to exceed the design strength, but are extremely rare. More common are fatigue and environmentally caused failures. Aircraft managers address this issue by making estimations of operational loads, and doing detailed fatigue analysis as appropriate to ensure safe landing gear operation. These estimations are conservative by nature, and frequently necessitate assumptions about landing, ground or braking conditions that may be different in actual operational service. The ability to measure, record, and possibly process the operational loads data for each aircrafts landing gear would give Aircraft Program Offices the ability to make more intelligent management decisions about operational limits, inspection intervals, and removal & depot overhaul cycle values. Additionally, landing gear failures can be caused by mis-servicing of the landing gear, resulting in much higher loads (even for a "normal" landing events or cause excessive fatigue damage than originally assumed). This phenomena is present and problematic for multiple aircraft platforms. The proposed SHM system would address this issue at two levels - detecting and prevent mis-servicing gears hence eliminating higher peak load failures, and also minimize/avoid unnecessary inspections due to perceived "hard landings". ES3 proposes to address all these issues through the use of an on-aircraft miniaturized data acquisition system, with sufficient data storage and processing capabilities to utilize multiple sensor inputs. During the Phase I SBIR effort, ES3 evaluated several of these systems, and numerous applicable sensors for their suitability in a SHM system. During the Phase I activities, prototype hardware was laboratory tested for various SHM functionality. The N121-043 Phase II effort intends to capitalize on the significant opportunity to resolve problems with the current SHM systems/datavia the integration of new technologies for sensors, communication devices, and miniaturized Data Acquisition Systems (DAQ). In Phase I, ES3 demonstrated the technical feasibility of developing this type of multi-function SHM system that could address four main categories 1) fatigue life management, 2) safety, 3) maintenance reduction, and 4) mission impactin order to aid in the technology evaluation process The primary focus of the Phase II solution will be development/demonstration/validation on the P-8 (PMA-290) acquisition program. However, the proposed solution will be directly transferable to other acquisition programs included in the N121-043 SBIR topic, currently including V-22 (PMA-275), C-130 (PMA-207), and H-53K (PMA-261).

* information listed above is at the time of submission.

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