Application of Advanced Grid-Stiffened Structures Technology to the Minotaur Payload Fairing

Wegner, Peter; Higgins, John E.; VanWest, Barry

doi:10.2514/6.2002-1336

Cited by 13 publications

(13 citation statements)

References 4 publications

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“…The U.S. Air Force Research Laboratory, U.S. Air Force Office of Scientific Research, Orbital Sciences Corporation, and Boeing have jointly developed an advanced, grid-stiffened, composite fairing designed for the Minotaur launch vehicle [12]. This fairing was made using a graphite-epoxy composite and measures about 5 m in length.…”

Section: Introductionmentioning

confidence: 99%

Noise Transmission Studies of an Advanced Grid-Stiffened Composite Fairing

Lane

Kennedy²,

Richard

2007

Journal of Spacecraft and Rockets

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Interior fairing noise is an important consideration for payload launch survivability and has been studied extensively since the beginning of the space program. This work presents acoustic transmission studies conducted by the Air Force Research Laboratory, Space Vehicles Directorate, on a composite, grid-stiffened, Minotaur payload fairing. These tests were performed in an acoustics laboratory and examined the effects of acoustic flanking paths, the thermal protection system, and melamine-type acoustic blanket treatments on fairing noise. The data showed that acoustic flanking paths significantly increase noise transmission, especially at low frequency. The bare fairing with thermal protection system provided approximately 14 dB of noise reduction over the 5000 Hz bandwidth relative to external levels. Acoustic blanket performance was measured as a function of bandwidth, surface area coverage, and mass. It was observed that small amounts of treatment (2 kg) significantly increased noise reduction (3.6 dB), even at low frequency.

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Section: Introductionmentioning

confidence: 99%

Noise Transmission Studies of an Advanced Grid-Stiffened Composite Fairing

Lane

Kennedy²,

Richard

2007

Journal of Spacecraft and Rockets

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“…Elastic constants and ultimate strengths for the IM7/ 8552 unidirectional composite material used to fabricate the rib panels are listed in Tables 1 and 2, respectively [3]. The properties in these tables were determined from tests performed on coupons manufactured from an 8-ply unidirectional panel that was fiber-placed, vacuum bagged, and autoclave cured in the same manner as the actual AGS panels used in the tee pulloff and tee bend tests.…”

Section: Materials Stiffness and Strengthmentioning

confidence: 99%

“…AGS structures have been fabricated with a significant weight reduction, and a 20-30% cost reduction, when compared to honeycomb-core structures [1,2]. In one particular application of AGS design, an AGS structure used on a sounding rocket payload fairing, showed a decrease in weight of 60% over the existing aluminum fairing, and a 40% weight reduction over a conventional skin-stiffener composite fairing [3]. AGS structures traditionally have a very thin skin, as the ribs carry the majority of the load.…”

Section: Introductionmentioning

confidence: 99%

Progressive failure predictions for rib-stiffened panels based on multicontinuum technology

Key¹,

Garnich

Hansen

2004

Composite Structures

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“…Different design and production criteria were considered while realizing this method. Best PLF composite material was chosen by scoring PLFs that produced from different composite materials according to the criteria [2]. Another method that used was hybrid heuristic method.…”

Section: Introductionmentioning

confidence: 99%

Structural Optimization of Payload Fairing Used for Space Launch Vehicles

Atar¹,

Acar²

2015

Balkan Journal of Electrical and Computer Engineering

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Space Launch Vehicle (SLV) is a system to transport and place the Payloads (PL) such as satellites, experimental tools, and observation robots into desired orbit. PL are transported in Payload Fairing (PLF) that is a part of SLV and protects PL from environmental effects exposed during SLV's flight. PL capacity is the major criteria in design of SLVs. One option to increase PL capacity of SLV is to minimize PLF weight while protecting the volume allocated for PL. In this study, an Optimization System (OS) is developed to minimize PLF weight while maintaining the PLF structural design strong enough to protect PL from effects such as aerodynamic and inertial loads that emerged from flight conditions. Tabu Search is integrated to the OS to perform optimization. Structural analysis program is integrated to the OS to evaluate the structural strength. It is found that an optimized and structurally appropriate PLF configuration can be selected with Tabu Search integrated OS.

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Application of Advanced Grid-Stiffened Structures Technology to the Minotaur Payload Fairing

Cited by 13 publications

References 4 publications

Noise Transmission Studies of an Advanced Grid-Stiffened Composite Fairing

Noise Transmission Studies of an Advanced Grid-Stiffened Composite Fairing

Progressive failure predictions for rib-stiffened panels based on multicontinuum technology

Structural Optimization of Payload Fairing Used for Space Launch Vehicles

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