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  • 1
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    Progress in Payload Separation Risk Mitigation for a Deployable Venus Heat Shield (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A deployable decelerator known as the Adaptive Deployable Entry and Placement Technology (ADEPT) offers substantial science and mass savings for the Venus In Situ Explorer (VISE) mission. The lander and science payload must be separated from ADEPT during atmospheric entry. This paper presents a trade study of the separation system concept of operations and provides a conceptual design of the baseline: aft-separation with a subsonic parachute. Viability of the separation system depends on the vehicle's dynamic stability characteristics during deceleration from supersonic to subsonic speeds. A trajectory sensitivity study presented shows that pitch damping and Venusian winds drive stability prior to parachute deployment, while entry spin rate is not a driver of stability below Mach 5. Additionally, progress in free-flight CFD techniques capable of computing aerodynamic damping parameters is presented. Exploratory simulations of ADEPT at a constant speed of Mach number of 0.8 suggest the vehicle may have an oscillation limit cycle near 5 angle-of-attack. The proposed separation system conceptual design is thought to be viable.
    Keywords: Spacecraft Design, Testing and Performance
    Type: ARC-E-DAA-TN8136 , 22nd AIAA Aerodynamic Decelerator Systems Technology Conference; Mar 25, 2013 - Mar 28, 2013; Daytona Beach, FL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Inflatable Re-entry Vehicle Experiment (IRVE-4) Overview (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The suite of Inflatable Re-Entry Vehicle Experiments (IRVE) is designed to further our knowledge and understanding of Hypersonic Inflatable Aerodynamic Decelerators (HIADs). Before infusion into a future mission, three challenges need to be addressed: surviving the heat pulse during re-entry, demonstrating system performance at relevant scales, and demonstrating controllability in the atmosphere. IRVE-4 will contribute to a better understanding of controllability by characterizing how a HIAD responds to a set of controlled inputs. The ability to control a HIAD is vital for missions that are g-limited, require precision targeting and guidance for aerocapture or entry, descent, and landing. The IRVE-4 flight test will focus on taking a first look into controlling a HIAD. This paper will give an overview of the IRVE-4 mission including the control response portion of the flight test sequence, and will provide a review of the mission s development.
    Keywords: Spacecraft Design, Testing and Performance
    Type: NF1676L-11478 , 21st AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar; May 23, 2011 - May 26, 2011; Dublin; Ireland
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Launch Vehicle Ascent Trajectory Simulation Using the Program to Optimize Simulated Trajectories II (POST2) (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Program to Optimize Simulated Trajectories II (POST2) has been continuously developed for over 40 years and has been used in many flight and research projects. Recently, there has been an effort to improve the POST2 architecture by promoting modularity, flexibility, and ability to support multiple simultaneous projects. The purpose of this paper is to provide insight into the development of trajectory simulation in POST2 by describing methods and examples of various improved models for a launch vehicle liftoff and ascent.
    Keywords: Astrodynamics
    Type: NF1676L-25552 , AAS/AIAA Space Flight Mechanics Meeting; Feb 05, 2017 - Feb 09, 2017; San Antonio, TX; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Reverse Launch Abort System Parachute Architecture Trade Study (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This study investigated a potential Launch Abort System (LAS) Concept of Operations and abort parachute architecture. The purpose of the study was to look at the concept of jettisoning the LAS tower forward (Reverse LAS or RLAS) into the free-stream flow rather than after reorienting to a heatshield forward orientation. A hypothesized benefit was that due to the compressed timeline the dynamic pressure at main line stretch would be substantially less. This would enable the entry parachutes to be designed and sized based on entry loading conditions rather than the current stressing case of a Pad Abort. Ultimately, concerns about the highly dynamic reorientation of the CM via parachutes, and the additional requirement of a triple bridle attachment for the RLAS parachute system, overshadowed the potential benefits and ended this effort.
    Keywords: Launch Vehicles and Launch Operations
    Type: AIAA Paper 2011-1225 , NF1676L-11872 , 49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition; Jan 04, 2011 - Jan 07, 2011; Orlando, FL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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