The SSRS and SIAD-R should be brought to TRL-6, while the SIAD-E should be brought to TRL-5. The project will develop a 33.5 m Do Supersonic Ringsail (SSRS) parachute, 6m attached torus, robotic class Supersonic Inflatable Aerodynamic Decelerator (SIAD-R), and an 8 m attached isotensoid, exploration class Supersonic Inflatable Aerodynamic Decelerator (SIAD-E). The Low Density Supersonic Decelerator (LDSD) project is tasked by NASA's Office of the Chief Technologist (OCT) to advance the state of the art in Mars entry and descent technology in order to allow for larger payloads to be delivered to Mars at higher altitudes with better accuracy. Blando, Guillermo Kennett, Andrew Von Der Heydt, Max Wolff, John Luke Yerdon, Mark High Altitude Supersonic Decelerator Test VehicleĬook, Brant T. The distribution of the patch dimensions tended to be log normal. The median thickness of high altitude turbulence patches was less than 400 meters (1300 feet) the median length was less than 16 kilometers (10 miles). Given values of gust acceleration were less frequent, on the basis of distance traveled, for supersonic flight of the YF-12A airplane at altitudes above 12.2 kilometers (40,000 feet) than for subsonic flight of a jet passenger airplane at altitudes below 12.2 kilometers (40,000 feet). The amount of turbulence varied with season, increasing by a factor of 3 or more from summer to winter. The portion of flight distance in turbulence ranged from 6 percent to 8 percent at altitudes between 12.2 kilometers and 16.8 kilometers (40,000 feet and 55,000 feet) to less than 1 percent at altitudes above 18.3 kilometers (60,000 feet). The air crew often rated given gust accelerations as being more intense during high altitude supersonic flight than during low altitude subsonic flight. Subjective turbulence intensity ratings were obtained from air crew members. The data were obtained during 90 flights at altitudes above 12.2 kilometers (40,000 feet). High altitude turbulence experienced at supersonic speeds is described in terms of gust accelerations measured on the YF-12A airplane. High altitude gust acceleration environment as experienced by a supersonic airplane This test method has the advantages of accuracy, fewer experimental limitations, and reusability. The test results indicated that the test bed produced a uniform-flow field with a static pressure and density equivalent to atmospheric conditions at an altitude of 13-15km and at a flow velocity of approximately M 2.4. Sled tests were used to verify the performance of the test bed. Based on an analysis of the requirements for high-altitude supersonic flight tests, a ground-based test bed was designed combining Laval nozzle, which is often found in wind tunnels, with a rocket sled system. Ground-based methods for accurately representing high-altitude, high-speed flight conditions have been an important research topic in the aerospace field. ![]() Verification of a ground-based method for simulating high-altitude, supersonic flight conditions Though primarily a shake out flight of the new test system, the flight was also able to achieve an early test of two of the LDSD technologies, a large 6 m diameter Supersonic Inflatable Aerodynamic Decelerator (SIAD) and a large, 30.5 m nominal diameter supersonic parachute. The first flight of this architecture occurred on June 28th of 2014. Once at those conditions, the vehicle is despun and the test period begins. ![]() The test vehicle is released from the balloon, spun up for gyroscopic stability, and accelerated to over four times the speed of sound and an altitude of 50 kilometers using a large solid rocket motor. A large, helium filled scientific balloon is used to hoist a 4.7 m blunt body test vehicle to an altitude of approximately 32 kilometers. ![]() To achieve this testing, the LDSD project developed a test architecture similar to that used by the Viking Project in the early 1970's for the qualification of their supersonic parachute. A key element of that development is the testing of full-scale articles in conditions relevant to their intended use, primarily the tenuous Mars atmosphere. NASA's Low-Density Supersonic Decelerator Project is developing and testing the next generation of supersonic aerodynamic decelerators for planetary entry. Summary of the First High-Altitude, Supersonic Flight Dynamics Test for the Low-Density Supersonic Decelerator Project
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