Weight-Efficiency of Conventional Shielding Systems in Protecting Unmanned Spacecraft from Orbital Debris

Cherniaev, Aleksandr; Telichev, Igor

doi:10.2514/1.a33596

Cited by 37 publications

(19 citation statements)

References 15 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Research continues to expand our capacity to efficiently protect external spacecraft parts from high-velocity debris impacts. 26 Immobile external spacecraft parts can be adequately protected from expected debris impacts with proper material selection and integration. Likewise, proper material selection for origami-based bellows design can allow for more function while adequately containing debris.…”

Section: B Materialsmentioning

confidence: 99%

Highly Compressible Origami Bellows for Microgravity Drilling-Debris Containment

Butler¹,

Magleby

Howell

et al. 2017

AIAA SPACE and Astronautics Forum and Exposition

View full text Add to dashboard Cite

The design and testing of an origami-based bellows for microgravity drilling is described. The potential benefits of an origami-based solution created an opportunity for application on NASA's Asteroid Redirect Mission (ARM) to protect sensitive parts from debris. Origami-based bellows were designed to fit spatial limitations and meet needed compression ratios. Designs have demonstrated high mass reductions, improved stroke length, greatly decreased stowed volume, improved flexibility, and reduced reaction forces in comparison with traditional metal bellows. A nylon-reinforced polyvinyl fluoride based bellows with an aramid fiber stitched seam is well suited for debris containment in space conditions. Various epoxies maintained an adequate bond with polyvinyl fluoride below expected environmental temperature for bellows mounting. Asymmetric compression of the bellows occurs at extreme low temperatures and is preventable by balancing stiffness within the structure.

show abstract

Section: B Materialsmentioning

confidence: 99%

Highly Compressible Origami Bellows for Microgravity Drilling-Debris Containment

Butler¹,

Magleby

Howell

et al. 2017

AIAA SPACE and Astronautics Forum and Exposition

View full text Add to dashboard Cite

show abstract

“…The main difficulties in solving this problem are due to the reasons: rigid weight limitations of the screens and high speeds upon impact. Scientists are working to create methods to protect the surface of spacecraft from damage [2][3][4][5][6], to simulate the conditions for such emergencies in orbit and to form a new promising class of layered materials. Layered composite materials (CM) have a wide range and a unique combination of properties such as high strength, corrosion resistance, wear resistance [7][8].…”

Section: Introductionmentioning

confidence: 99%

Experimental Study of the Stability of Layered Composite Plates

Bokhoeva¹,

Bochektueva²,

Rogov³

2019

Proceedings of the International Conference on Aviamechanical Engineering and Transport (AviaENT 2019)

View full text Add to dashboard Cite

This article presents the results of experimental studies of definition the mechanical characteristics of epoxy resin and hardener without adding nanopowder and with the inclusion of nanopowders. The stability and destruction process of laminated plates made of composite material with different numbers of layers without nano-additives and with nanopowders in the binder has been studied. The results of experimental studies of the stability and destruction process of laminated plates made of composite material are presented. Experimental and numerical methods are used to estimate the carrying capacity of laminated plates. A technique has been developed for the experimental study of the deformation and strength properties of composite materials using modern test equipment. It was established that the discrepancies between the values of the critical load of four-layer samples and the critical load of three-layer samples are 2-3%, therefore, to reduce the weight, products from composite materials can be made of three-layer plates. In the ANSYS system, twolayer, three-layer and four-layer plates were modeled. The results of numerical calculation by the finite element method are presented. Comparison of the obtained experimental results with numerical values is made, the possibility of using experimental data on the mechanical behavior of layered composite materials in the design and calculation of protective screen modules is estimated.

show abstract

“…Strength behavior of all materials considered in this study has been represented in terms of Johnson-Cook model [15], which is a typical choice for metals subjected to high strains, high strain rates, and high temperatures. Application of Johnson-Cook strength and failure models to hypervelocity impact problems has been studied in [1,16]. In [16] it was found that the models are applicable for accurate predictions of target hole diameters from hypervelocity …”

Section: Strength Modelmentioning

confidence: 99%

“…Unlike manned spacecraft that are conservatively designed to be protected against lowprobability impacts of centimeter-size and even larger orbital debris (crew safety reasons), unmanned satellites are typically being designed with lower margins of safety against more probable impacts of small, millimeter-sized particles [1]. It should be noted that because of the extremely high velocities of orbital debris (over 7 km/s), even 1 mm-sized objects can cause significant damage to spacecraft onboard systems.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Fragmentation of Millimeter-Size Hypervelocity Projectiles on Combined Mesh-Plate Bumpers

Cherniaev

Telichev

2017

Advances in Materials Science and Engineering

Self Cite

View full text Add to dashboard Cite

This numerical study evaluates the concept of a combined mesh-plate bumper as a shielding system protecting unmanned spacecraft from small (1 mm) orbital debris impacts. Two-component bumpers consisting of an external layer of woven mesh (aluminum or steel) directly applied to a surface of the aluminum plate are considered. Results of numerical modeling with a projectile velocity of 7 km/s indicate that, in comparison to the steel mesh-combined bumper, the combination of aluminum mesh and aluminum plate provides better fragmentation of small hypervelocity projectiles. At the same time, none of the combined mesh/plate bumpers provide a significant increase of ballistic properties as compared to an aluminum plate bumper. This indicates that the positive results reported in the literature for bumpers with metallic meshes and large projectiles are not scalable down to millimeter-sized particles. Based on this investigation's results, a possible modification of the combined mesh/plate bumper is proposed for the future study.

show abstract

Weight-Efficiency of Conventional Shielding Systems in Protecting Unmanned Spacecraft from Orbital Debris

Cited by 37 publications

References 15 publications

Highly Compressible Origami Bellows for Microgravity Drilling-Debris Containment

Highly Compressible Origami Bellows for Microgravity Drilling-Debris Containment

Experimental Study of the Stability of Layered Composite Plates

Fragmentation of Millimeter-Size Hypervelocity Projectiles on Combined Mesh-Plate Bumpers

Contact Info

Product

Resources

About