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  • 1
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    Sand and dust issues for the MESUR mission (1991)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The presence of particles in the Martian atmosphere increases the rate of erosion of the heat shield during the entry phase of the MESUR mission. Preliminary analysis has shown that under certain conditions particles will penetrate the bow shock of the entry vehicle, impact and erode the heat shield, above the anticipated rate from the ablation process. Knowledge of the distribution, sizes, and composition of particles suspended in the atmosphere will permit the estimation of the heat shield recession both for a nominal Mars atmosphere and in dust storm conditions. On the surface of Mars, sand and dust can effect the operations and design of the science instruments (i.e., imaging) and lander subsystems (i.e., solar arrays). Distribution and deposition of sand and dust on the planet's surface will dictate the feasibility of using solar arrays as a power source for the lander. Furthermore, the potential abrasive nature of blowing particles must be understood in order to properly select suitable materials for lander structure and any components exposed to the environment. The selection of lander material may also be dictated by corrosive and chemically active properties of particles at a potential landing site. Some key interests concerning sand and dust on the surface and in the atmosphere are summarized in a number of questions that are included.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Sand and Dust on Mars; p 56-57
    Format: application/pdf
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  • 2
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    The flight and impact dispersion of the Comet Nucleus Penetrator - A six-degree-of-freedom simulation (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The flight dynamics of a Penetrator probe which, as part of a Comet Rendezvous and Asteroid Flyby mission will impact a known periodic comet, possibly Hempel 2, and penetrate beneath the surface to obtain measurements, is discussed. The mission is described, including the penetrator-separation dynamics, the dynamics during initial coast and rocket thrust phase, and the final coast to impact. The effects on the results that may be caused by the comet nucleus gravity field variations, uncertainty in the spacecraft state vector, the spacecraft pointing accuracy, initial separation errors, and rocket motor thrust errors are examined.
    Keywords: ASTRODYNAMICS
    Type: AIAA PAPER 86-2268
    Format: text
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  • 3
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    A theoretical prediction of the attitude dynamics due to aerodynamic effects on the reusable reentry satellite (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: As part of the preliminary mission analysis of the Reusable Reentry Satellite (RRS) (planned for launching in the early to mid-1990s), the on-orbit attitude dynamics of the RRS were analyzed to quantify various parameters that would affect the attitude dynamics of the vehicle. The analysis simulated the attitude dynamics of the RRS due to aerodynamic forces coupled with the motion of the satellite moving around the orbit, estimated the levels of induced angular rates due to external disturbance torques while in orbit, and established the limits of operational orbit altitudes. The results show that, for a typical 60-day mission, orbit altitudes above 350 km are necessary to prevent undesirable orbit decay, with about 200 km as the lower limit. It was also found that, in order to maintain a pointing attitude toward the sun within an acceptable angular deviation for periods exceeding 8 hrs, it is necessary to orbit at an altitude above 600 km.
    Keywords: ASTRODYNAMICS
    Type: AIAA PAPER 88-4272
    Format: text
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  • 4
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    Adaptable, Deployable Entry and Placement Technology (ADEPT) for Future Mars Missions (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The concept of a mechanically deploy- able hypersonic decelerator, developed initially for high mass (40 MT) human Mars missions, is currently funded by OCT for technology maturation. The ADEPT (Adaptive, Deployable Entry and Placement Technology) project has broad, game-changing applicability to in situ science missions to Venus, Mars, and the Outer Planets.
    Keywords: Spacecraft Design, Testing and Performance
    Type: ARC-E-DAA-TN9854 , International Planetary Probe Workshop (IPPW-10); Jun 17, 2013 - Jun 21, 2013; San Jose, CA; United States
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  • 5
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    Estimates of Heat Shielding Requirements for Saturn Probe Missions (1995)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: Entry trajectories, decelerations, heating and heat shielding requirements of probes entering the atmosphere of Saturn at relative entry velocities ranging from 26.5 - 33.0 km/sec were studied. Much of the Galileo Jupiter probe technology was applicable to these outer planet probes; therefore, the same configuration was used. A wide range entry flight path angles were used in the trajectory analysis in order to satisfy the complete range of arrival conditions and trajectory requirements. Various entry probe sizes and a range of entry masses from 32 - 258 kg were considered. The carbon phenolic heat shield material used on the Galileo and the successful Pioneer-Venus probes was selected. Turbulent boundary layer convection dominated the heating of the Saturn probes; radiative heating was negligible by comparison at the entry velocities considered. The peak heating rates were found to be about 4 kW per square centimeter, or approximately 17% of the Galileo probe's expected maximum value. The forebody heat shield mass fractions for the Saturn probes were found to vary from about 0.18 to 0.28. By comparison, the Pioneer-Venus probes' heat shield mass fractions ranged from 0.10 to 0.13 and the Galileo probe's forebody value is 0.43.
    Keywords: Spacecraft Design, Testing and Performance
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  • 6
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    New Stagnation Arc Jet Model Design for Testing ADEPT 3-D Carbon Cloth (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The ADEPT concept has been considered as an entry, descent and landing system to enable Human Mars class missions. Ground rules for the Mars studies required aerocapture, orbit, and then entry. The design utilizes a 3-D woven carbon cloth fabric as both heatshield and primary structure and design guidelines required 6 layers remaining after all entry events. The peak heating predicted for the ADEPT carbon cloth was 35 Wcm2 and resulting temperatures were predicted to be 1400K. Predictions for carbon mass loss were performed using equilibrium thermochemistry, which is only accurate for T2000K. Carbon oxidation is kinetically controlled at T2000K, and mass loss drops off considerably from equilibrium values. Design of the cloth thickness and mass would be significantly reduced if kinetics were considered. This effort was to design a stagnation test article design that could be used in the AHF with varying levels of oxygen where the results could be used to develop an engineering model to describe the recession rate of the carbon as a function of the partial pressure of monotomic oxygen.
    Keywords: Nonmetallic Materials; Spacecraft Design, Testing and Performance
    Type: ARC-E-DAA-TN46959 , Ames Research and Technology Symposium; Sep 28, 2017; Moffett Field, CA; United States
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  • 7
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    Mechanically-Deployed Hypersonic Decelerator and Conformal Ablator Technologies for Mars Missions (2012)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The concept of a mechanically deployable hypersonic decelerator, developed initially for high mass (approximately 40 MT) human Mars missions, is currently funded by OCT for technology maturation. The ADEPT (Adaptive, Deployable Entry and Placement Technology) project has broad, game-changing applicability to in situ science missions to Venus, Mars, and the Outer Planets. Combined with maturation of conformal ablator technology (another current OCT investment), the two technologies provide unique low-mass mission enabling capabilities otherwise not achievable by current rigid aeroshell or by inflatables. If this abstract is accepted, we will present results that illustrate the mission enabling capabilities of the mechanically deployable architecture for: (1) robotic Mars (Discovery or New Frontiers class) in the near term (2) alternate approaches to landing MSL-class payloads, without the need for supersonic parachute or lifting entry, in the mid-term and (3) Heavy mass and human missions to Mars in the long term.
    Keywords: Space Transportation and Safety
    Type: ARC-E-DAA-TN-5212 , Mars Exploration Workshop; Jun 12, 2012 - Jun 14, 2012; Houston, TX; United States
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  • 8
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    Adaptable, Deployable Entry and Placement Technology (ADEPT) Overview of FY15 Accomplishments (2015)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: ADEPT is an atmospheric entry architecture for missions to most planetary bodies with atmospheres: Current Technology development project funded under STMD Game Changing Development Program (FY12 start); stowed inside the launch vehicle shroud and deployed in space prior to entry; low ballistic coefficient (less than 50 kilograms per square meter) provides a benign deceleration and thermal environment to the payload; High-temperature ribs support three dimensional woven carbon fabric to generate drag and withstand high heating.
    Keywords: Fluid Mechanics and Thermodynamics; Astrodynamics; Lunar and Planetary Science and Exploration
    Type: ARC-E-DAA-TN27622 , Meeting of the Venus Exploration Analysis Group (VEXAG); Oct 27, 2015 - Oct 29, 2015; Washington, D.C.; United States
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  • 9
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    A Neptune Orbiter Concept Using Drag Modulated Aerocaptue (DMA) and the Adaptable, Deployable Entry and Placement Technology (ADEPT) (2019)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Conceptual Neptune orbiter was designed for the purpose of assessing mission feasibilityBuilt off of the 2017 Pre-Decadal Study, but adapted for drag modulation aerocapture.Science payload includes: Narrow Angle camera, Doppler Imager, Magnetometer, Atmospheric Probe (w/ ASI, Nephelometer, Mass Spectrometer). Baseline concept of operations releases probe prior to orbit insertion, but investigations are ongoing to assess the feasibility of bringing the probe to orbit before release.
    Keywords: Engineering (General)
    Type: ARC-E-DAA-TN67573 , Outer Planets Assessment Group Meeting; Apr 23, 2019; Washington, DC; United States
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  • 10
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    Space artificial gravity facilities - An approach to their construction (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: In the course of adaptation to a space microgravity environment, humans experience cardiovascular deconditioning, loss of muscle mass, and loss of bone minerals. One possible solution to these space adaptation problems is to simulate earth's gravity using the centripetal acceleration created by a rotating system. The design and construction of rotating space structures pose many challenges. Before committing to the use of artificial gravity in future space missions, a man-rated Variable Gravity Research Facility (VGRF) should be developed in earth orbit as a gravitational research tool and testbed. This paper addresses the requirements and presents preliminary concepts for such a facility.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Space 88 Conference on Engineering, Construction, and Operations in Space; Aug 29, 1988 - Aug 31, 1988; Albuquerque, NM; United States
    Format: text
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