Download or read book Thermal and Stress Analysis of an Attached Inflatable Decelerator AID Deployed in the Mars and Earth Atmospheres written by and published by . This book was released on 1971 with total page 112 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Note written by and published by . This book was released on 1974 with total page 792 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1971 with total page 294 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Heating at Mach 8 of Attached Inflatable Decelerator Configurations written by Theodore R. Jr Creel and published by . This book was released on 1971 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Deployment and Performance Characteristics of 1 5 meter Supersonic Attached Inflatable Decelerators written by Herman L. Bohon and published by . This book was released on 1974 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Deployment and Performance Characteristics of 5 foot diameter 1 5 M Attached Inflatable Decelerators from Mach Number 2 2 to 4 4 written by Herman L. Bohon and published by . This book was released on 1970 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: Deployment and performance characteristics of 5-Foot diameter (1.5m) Attached Inflatable Decelerators (AID) from Mach Numbers 2.2-4.4. Deployment characteristics and steady-state performance data were obtained over the Mach number range from 2.2 to 4.4 and at angles of attack from 0 degrees to 10 degrees. All attached inflatable decelerator (AID) models deployed successfully and exhibited flutter-free performance after deployment. Shock loads commonly associated with inflation of parachutes during deployment were not experienced. Force and moment data and ram-air pressure data were obtained throughout the Mach number range and at angles of attack from 0 degrees to l0 degrees. The high drag coefficient of 1.14 was in good agreement with the value predicted by the theory used in the design and indicated other AID shapes may be designed on a rational basis with a high degree of confidence.--NTIS Web site.
Download or read book Scalability of a Tension Cone Supersonic Inflatable Aerodynamic Decelerator written by Alejandro Pensado and published by . This book was released on 2017 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Human-class missions to Mars will require larger and safer payloads than current technology can achieve. The inflatable aerodynamic decelerator concept has the potential to meet these needs which will enable human-class missions to Mars for a desired 2030s window. This concept, started in the 1960s for the Viking missions, involves a deployable inflatable aeroshell designed for missions with entry, descend and land stages. Research fluctuated in the following decade from minor development in the 1980s to an increased interest in recent years including international entities. The continuing research resulted in two major designs: Supersonic and hypersonic decelerators. The objective of this thesis is to systematically study the scalability of the supersonic inflatable aerodynamic decelerator tension cone and computationally simulate the minimum inflation pressure required for Earth and Mars deployment conditions. The scalability study is based on the 0.6-meter diameter tension cone model studied in the supersonic wind tunnel tests conducted at NASA Glenn Research Center. The scaling parameters chosen to investigate the deployment performance of 14, 17, 20, and 23-meter tension cones are Reynolds number, Froude number, ballistic coefficient, and mass efficiency at a fixed Mach number. Scaling the Reynolds number showed the tension cones operate under laminar flow conditions. Matching the Froude number determined that a larger tension cone is more effective in decelerating the entry vehicle and less effective in a Mars atmosphere compared to an Earth atmosphere. Both the ballistic coefficient and mass efficiency showed that a larger tension cone is less efficient at decelerating because the mass increase of the tension cone overwhelms the effect of increasing the diameter of the tension cone. The velocity to match each scaling parameter was calculated for the 0.6-meter model. These results were compiled into eight potential case studies to investigate the tension cone at these deployment conditions.The objective of the simulations was to determine time history of forces at the scaled conditions, inflation pressure required for deployment, and minimum inflation pressure required to prevent buckling. The computational work focused on the Earth and Mars cases for the 0.6-meter tension cone with the scaled conditions to match the 14-meter tension cone. Matching the Mach number was used as the validation, where the simulation and experimental axial forces agreed with minimal error. In order to determine the inflation pressure required for deployment, the internal pressure of the torus was reduced until the tension shell began to wrinkle. Wrinkles indicate structural failure and eventual torus buckling. The Mach, Reynolds, and Froude number simulations yielded similar results. Fully deployed, the tension cone had small oscillations, wrinkling appeared and became more prominent as the structure began to fail until the torus buckled. The mass efficiency simulation experienced higher axial force, resulting in more violent tension cone oscillations. The torus experienced a bending moment until the structure buckled. This indicates the axial force load limit on the tension cone. The data were compiled shows a linear relationship between minimum torus inflation pressure and axial loading. This allows tension cone mass optimization for future designs.
Download or read book Government Reports Announcements written by and published by . This book was released on 1971 with total page 1346 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Research and Technology Program Digest written by United States. National Aeronautics and Space Administration and published by . This book was released on with total page 792 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Government Reports Announcements Index written by and published by . This book was released on 1971 with total page 928 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Static Structural Tests of a 1 5 meter diameter Fabric Attached Inflatable Decelerator written by Conrad M. Willis and published by . This book was released on 1972 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Research and Technology Program Digest Flash Index written by and published by . This book was released on 1967 with total page 794 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Structural Merit Function for Aerodynamic Decelerators written by Melvin S. Anderson and published by . This book was released on 1969 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Structural merit function for aerodynamic decelerators.
Download or read book Investigation of an Attached Inflatable Decelerator with Mechanically Deployed Inlets at Mach Numbers from 2 25 to 4 75 written by and published by . This book was released on 1969 with total page 33 pages. Available in PDF, EPUB and Kindle. Book excerpt: A test was conducted in the 16-ft supersonic wind tunnel to obtain deployment, inflation, and steady-state characteristics of an attached inflatable decelerator with mechanically deployed inlets. Deployments were made at Mach numbers 3.0 and 4.4 at free-stream dynamic pressures of 120 and 73 psf, respectively. The mechanically deployed inlet system resulted in successful deployments of the three test models with inflation times of from 0.4 to 0.7 sec.
Download or read book Deployment and Performance Characteristics of Attached Inflatable Decelerators with Mechanically Deployed Inlets at Mach Numbers from 2 6 to 4 5 written by David E. A. Reichenau and published by . This book was released on 1972 with total page 31 pages. Available in PDF, EPUB and Kindle. Book excerpt: A test was conducted in the wind tunnel to determine deployment, inflation, and steady-state characteristics of attached inflatable decelerators. Deployments were made at a Mach number of 3.0 at a free-stream dynamic pressure of 120 psf. The mechanically deployed inlet system resulted in successful deployments of the five test models with rapid inflation times of approximately 0.2 sec. The attached decelerators were stable throughout the Mach number range from 2.6 to 4.5 and at angles of attack through 10 deg. (Author).
Download or read book Performance Evaluation of Attached Inflatable Decelerators with Mechanically Deployed Inlets at Mach Numbers from 2 6 to 4 4 written by D. C. Baker and published by . This book was released on 1970 with total page 23 pages. Available in PDF, EPUB and Kindle. Book excerpt: A test was conducted in the 16-ft Propulsion Wind Tunnel (16S) to determine the effect of reducing the inlet capture area on the deployment and performance characteristics of attached inflatable decelerators. Because of malfunctions of the inlet deployment mechanism, limited deployment data were obtained on only one of the decelerator models. Decreasing the inlet capture area increased the inflation time to 2.2 sec but resulted in poor decelerator inflation and low drag coefficient compared with previous AID models tested. (Author).
Download or read book Journal of Hydronautics written by and published by . This book was released on 1971 with total page 236 pages. Available in PDF, EPUB and Kindle. Book excerpt:
