摘要 :
Small spacecraft have emerged in recent years from a niche academic pursuit to a platform for governments and corporations to perform scientific and commercial ventures in space at much lower cost. Simultaneously, the field of Ent...
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Small spacecraft have emerged in recent years from a niche academic pursuit to a platform for governments and corporations to perform scientific and commercial ventures in space at much lower cost. Simultaneously, the field of Entry, Descent, and Landing (EDL) is rapidly maturing a number of technologies geared toward delivering ever-larger payloads to destinations across our solar system, with the culminating event being safe transport of human beings to the surface of Mars. One of these technologies for landing large payloads, known as the Adaptable, Deployable Entry and Placement Technology (ADEPT), uses a mechanical skeleton to deploy a revolutionary carbon fabric system that serves as both heat shield and primary structure during atmospheric entry. This paper explores the application of a Nano-ADEPT entry system for delivery of very small payloads (< 5 kg) to locations of interest in an effort to leverage low-cost platforms to rapidly mature the technology while simultaneously delivering high-value science. It is shown that secondary payload missions to Mars as well as entry from low Earth orbit are feasible. Secondary payload missions to Venus at small scale present a greater challenge and may only be feasible if the system can be designed with exceptionally low mass. The technology maturation strategy for Nano-ADEPT is described. Four test campaigns underway at the time of writing are discussed in detail, including deployment testing, wind tunnel testing, system-level arc jet testing, and a sounding rocket flight test. To conclude, a mission opportunity is described to demonstrate Nano-ADEPT from the International Space Station.
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1. FFCFD continues to expand V&V efforts with focus on low supersonic/transonic flow 1.1 Development of reduced DoF analysis with FFCFD enables fast population of Mach-alpha aero-database 1.2 Orion CM "cross-facility" comparison shows good agreement between simulation predicted pitch damping and experimental results 2. FFCFD support for DragonFly, EES, SpaceX Dragon Capsule 2.1 Application of end-to-end dynamic stability assessment using 1 -DoF simulations have been carried out for a range of Mach numbers and initial AoAs....
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1. FFCFD continues to expand V&V efforts with focus on low supersonic/transonic flow 1.1 Development of reduced DoF analysis with FFCFD enables fast population of Mach-alpha aero-database 1.2 Orion CM "cross-facility" comparison shows good agreement between simulation predicted pitch damping and experimental results 2. FFCFD support for DragonFly, EES, SpaceX Dragon Capsule 2.1 Application of end-to-end dynamic stability assessment using 1 -DoF simulations have been carried out for a range of Mach numbers and initial AoAs.
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Starting in 2014 and completing in 2019, the Heatshield for Extreme Entry Environment Technology (HEEET) project has been working to mature a 3-D Woven Thermal Protection System (TPS) to Technical Readiness Level (TRL) 6 to suppor...
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Starting in 2014 and completing in 2019, the Heatshield for Extreme Entry Environment Technology (HEEET) project has been working to mature a 3-D Woven Thermal Protection System (TPS) to Technical Readiness Level (TRL) 6 to support future NASA missions to destinations with extreme entry environments such as Venus, Saturn, Uranus, Neptune and high-speed sample return missions to Earth. A key aspect of the project has been the building and testing of a 1-meter base diameter Engineering Test Unit (ETU) representative of what could be used for a Saturn probe. This paper provides a high-level overview of the HEEET project including 1) manufacturing and testing of the ETU for structural model verification, 2) establish system capability and 3) verify manufacturing workmanship.
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A system overview of the sample chain planned for use on a Comet Surface Sample Return mission is provided. The key actions that must be performed in order to acquire, condition, and protect the surface samples are described. Sign...
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A system overview of the sample chain planned for use on a Comet Surface Sample Return mission is provided. The key actions that must be performed in order to acquire, condition, and protect the surface samples are described. Significant mission events are noted, especially with regard to their implications to successful sample return. Finally, recovery activities are discussed as these represent the initial steps taken in the terrestrial curatorial process.
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摘要 :
A system overview of the sample chain planned for use on a Comet Surface Sample Return mission is provided. The key actions that must be performed in order to acquire, condition, and protect the surface samples are described. Sign...
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A system overview of the sample chain planned for use on a Comet Surface Sample Return mission is provided. The key actions that must be performed in order to acquire, condition, and protect the surface samples are described. Significant mission events are noted, especially with regard to their implications to successful sample return. Finally, recovery activities are discussed as these represent the initial steps taken in the terrestrial curatorial process.
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摘要 :
A system overview of the sample chain planned for use on a Comet Surface Sample Return mission is provided. The key actions that must be performed in order to acquire, condition, and protect the surface samples are described. Sign...
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A system overview of the sample chain planned for use on a Comet Surface Sample Return mission is provided. The key actions that must be performed in order to acquire, condition, and protect the surface samples are described. Significant mission events are noted, especially with regard to their implications to successful sample return. Finally, recovery activities are discussed as these represent the initial steps taken in the terrestrial curatorial process.
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