Smart Thermal Protection Systems

Keller, Karl; Pfeiffer, E.; Gaudenzi, Paolo; Lampani, Luca; Ullmann, Thomas; Ritter, Heiko

doi:10.4271/2005-01-2901

Cited by 7 publications

(11 citation statements)

References 9 publications

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“…More and more designers are paying attention to related issues in design and analysis of the morphing skin and its deployable frame (Keller et al 2006;Lampani, Keller, and Pfeiffer 2005;Simpson et al 1998;Thill, Etches, and Bond 2008). The deformation of the morphing skin must be accurate enough to meet the requirements of the aerodynamic profile.…”

Section: Introductionmentioning

confidence: 98%

“…Email: yansz@tsinghua.edu.cn As a result, many scholars have started to conduct research on smart thermal protection systems for the key components of spacecraft (Lampani, Keller, and Pfeiffer 2005). Morphing technology in aircraft and aerospace vehicles has received increased interest in recent decades because it is likely to enhance performance and efficiency over a wide range of flight conditions (Keller et al 2006;Thill, Etches, and Bond 2008). The ability to continuously transform vehicle geometry provides a single air vehicle with a multiple-mission capacity, as the vehicle can maintain and operate within the optimum or near-optimum flight envelope (Inoyama, Sanders, and Joo 2008).…”

Section: Introductionmentioning

confidence: 99%

“…Keller et al (2006) provided five ideas for a smart thermal protection system associated with the morphing structures of the aircraft. Comparison of the five programs revealed that the compliant mechanism ranked the best, and also enabled leading edge curvature changes during atmospheric flight (Keller et al 2006).…”

Section: Introductionmentioning

confidence: 99%

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Design of deployable bistable structures for morphing skin and its structural optimization

Yan

2013

Engineering Optimization

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The morphing skin is the surface of a deployable frame which can change its shape to present optimal performance in all stages of a task for an aerospace vehicle. This article proposes a deployable frame with low kinematic error and high stability. Mechanical design and optimization of the deployable mechanism are developed, and specifically the analysis model of the deployable mechanism is established by the use of extendable units. The genetic algorithm is employed to find the optimal geometric parameters of the foldable structure. Furthermore, the design method of a bistable compliant mechanism is investigated to achieve the bistability. An example of a morphing leading edge (MLE) is analysed using the proposed method. The results show that the position errors converge to the optimal solution which supplies the minimum value. Numerical analysis indicates that the mechanism can provide two bistable positions for the actual use of the MLE.

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Section: Introductionmentioning

confidence: 98%

Section: Introductionmentioning

confidence: 99%

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Design of deployable bistable structures for morphing skin and its structural optimization

Yan

2013

Engineering Optimization

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“…During these years, a hot issue of morphing technology is morphing wing for which numerous studies have been carried out. Lampani et al [15,16] proposed a concept of smart thermal protection system for morphing leading edge. Inoyama et al [18,19] present a topology optimization methodology for determining multiple configuration for morphing wing structure.…”

Section: Introductionmentioning

confidence: 99%

“…Morphing technology on aircraft and spacecraft has found increased interest over the past 30 years because it is likely to enhance performance and efficiency over a wider range of flight conditions [15,16]. NASA had started the Aircraft Morphing Program to develop and mature smart component technologies for advanced airframe systems that can be embedded in aircraft structures and provide cost effective system benefits [17].…”

Section: Introductionmentioning

confidence: 99%

Conceptual Design of Deployment Structure of Morphing Nose Cone

Yan

2013

Advances in Mechanical Engineering

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For a reusable space vehicle or a missile, the shape of the nose cone has a significant effect on the drag of the vehicle. In this paper, the concept of morphing nose cone is proposed to reduce the drag when the reentry vehicle flies back into the atmosphere. The conceptual design of the structure of morphing nose cone is conducted. Mechanical design and optimization approach are developed by employing genetic algorithm to find the optimal geometric parameters of the morphing structure. An example is analyzed by using the proposed method. The results show that optimal solution supplies the minimum position error. The concept of morphing nose cone will provide a novel way for the drag reduction of reentry vehicle. The proposed method could be practically used for the design and optimization of the deployable structure of morphing nose cone.

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