Velocity Profile Measurements Under the Ramp of a Lockheed Martin C-130 Aicraft

Angle, Gerald M.; Pertl, Franz A.; Smith, James E.; Corso, Bruce J.

doi:10.4271/2004-01-3099

Cited by 7 publications

(3 citation statements)

References 2 publications

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“…The boundary conditions of the system assumed a complete restraint on the bearing stand four attachment holes and the loading applied is transferred through the two connection holes which are attachments for the rotational shaft bearing which is the attachment mechanism for the mechanical arms. This loading used on the bearing stands is the maximum drag (from report ~322 lbs) transferred through the mechanical arm moment arm with an additional dynamics loading factor of 1.5 to give a total of ~600lbs of pull-up force against the rear of the stand (27). were cut from a solid piece of 6061-T6 Aluminum, which completely eliminated a high stress concentration and vertical alignment issues because they were fabricated using the highly accurate cutting capabilities of a water-jet.…”

Section: Boundary Conditionsmentioning

confidence: 99%

“…(right) Upgraded OCULUS 1.affect on the mechanical arm/pod system is taken directly from aerodynamic load data obtained from an aerodynamic rake test performed by WVU on a C-130 aircraft. The results from the test give a worst case loading scenario that was designed during the development of the system(27).The mechanical arm system is fastened to a customized 6.5-inch thick reinforced standard military C-130 pallet, which is the foundation and anchor for the arm. The pallet is locked and secured onto the C-130 ramp, making the plane and mechanical arm act as one rigid body, leaving the arm with two degrees of freedom.…”

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Design Validation Methodology Development for an Aircraft Sensor Deployment System

Wowczuk¹

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Virginia University (WVU), outlined the general concept of a deployment system to be used on a C-130 aircraft. As a sequel, a new system, OCULUS 1.1, has been developed and designed. The new system transfers the concept system design to a safety of flight design, and also enhanced to a pre-production system to be used as the test bed to gain full military certification approval. The OCULUS 1.1 system has an implemented standard deployment system/procedure to go along with a design suited for military certification and implementation. This design process included analysis of the system's critical components and the generation of a critical component holistic model to be used as an analysis tool for future payload modification made to the system. Following the completion of the OCULUS 1.1 design, preparations and procedures for obtaining military airworthiness certification are described. The airworthiness process includes working with the agency overseeing all modifications to the normal operating procedures made to military C-130 aircraft and preparing the system for an experimental flight test. The critical steps in his process include developing a complete documentation package that details the analysis performed on the OCULUS 1.1 system and also the design of experiment flight test plan to analyze the system. Following the approval of the documentation and design of experiment an experimental flight test of the OCULUS 1.1 system was performed to verify the safety and airworthiness of the system. This test proved successfully that the OCULUS 1.1 system design was airworthy and approved for military use. The OCULUS 1.1 deployment system offers an open architecture design that is ideal for use as a sensor testing platform for developmental airborne sensors. The system's patented deployment methodology presents a simplistic approach to reaching the systems final operating position which offers the most robust field of view area of rear ramp deployment systems. iv Acknowledgements "It is good to have an end to journey toward; but it is the journey that matters, in the end,"-Ursula K. Le Guin The above quote is incredibly indicative of the process of obtaining a doctorate of philosophy in an engineering discipline. At the beginning of one's research the concentration must always be directed to accomplishing the goal of the research or one may stray and never find the path (or paths) that lead to completion. Throughout this process an immeasurable amount of knowledge, skills and self growth are gained and in the end these are the true accomplishments of one's work. There are several people that have been involved in this work both intimately and externally, and without their support a successful end to this process would never have been accomplished. I would like to begin by thanking those that were intimately involved in this research, namely those who guided me and those who worked along side of me. The majority of the guidance I received evolved from the diverse members of my research committee: Dr.

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Section: Boundary Conditionsmentioning

confidence: 99%

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confidence: 99%

Design Validation Methodology Development for an Aircraft Sensor Deployment System

Wowczuk¹

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“…West Virginia University (WVU) has been tasked with the needs assessment, design and fabrication of a sensor platform that is capable of operating remote sensors for use aboard the C-130 military aircraft [1][2][3][4][5][6][7][8][9][10][11][12][13]. WVU has completed design and construction of a transportable roll-on, roll-off sensor pallet(s) that will deploy via the rear cargo door of the aircraft while in flight.…”

Section: Introductionmentioning

confidence: 99%

Design of a quick-release mechanism for a C-130 aircraft sensor platform

Lucey¹

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The development of a standardized sensor pallet system for a C-130 aircraft was conceived by the Center for Industrial Research Applications at West Virginia University to assist in counterdrug reconnaissance activities within the United States. The system has been completed and is now being optimized for various uses in addition to counterdrug reconnaissance. It is sought to have the sensor carriers/housings easily interchangeable so that they may be switched in the field by operators rather than in the hangar by technicians. The design parameters were established by the National Guard mission requirements and by the limitations of the C-130 aircraft. These limitations include using Commercial off the Shelf (COTS) and Government off the Shelf (GOTS) components when developing the system that must be universal on all C-130 aircrafts variants B thru H. The following work describes the design process and engineering analysis of this "quick-release" mechanism design.

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