Qualification flight tests of the Viking decelerator system

Author:

MOOG R.1,BENDURA R.2,TIMMONS J.2,LAU R.3

Affiliation:

1. Martin Marietta Corp., Denver, Colo.

2. NASA, Langley Research Center, Hampton, Va.

3. Goodyear Aerospace Corp., Akron, Ohio

Publisher

American Institute of Aeronautics and Astronautics

Reference32 articles.

1. 3-6and 10.

2. Even with no modification to our load prediction model, the BLDT results imply that we will certainly be able to predict the Mars opening load for a given sat of conditions to within +2000 Ib. At the Mars maximum predicted load level of 13,300 Ib, the uncertainty in load prediction will be closer to +lo 001b and we will more likely overpredict than underpredict.

3. Plots of the above force coefficients 3-6are highly oscillatory, reflecting the natural elastic frequency of the two-body spring mass system and noise on both the accelerometer and tensiometer data. When steady-statedescent conditions are achieved, the data become practically useless because noise obscures variation in the parameter of interest. These shortcomings led to a search for a better method of extracting parachute drag performance.

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1. Mars InSight Parachute System Performance;AIAA Aviation 2019 Forum;2019-06-14

2. Aerodynamic Models for the Low Density Supersonic Declerator (LDSD) Test Vehicles;34th AIAA Applied Aerodynamics Conference;2016-06-10

3. Development and Testing of a New Family of Low-Density Supersonic Decelerators;AIAA Aerodynamic Decelerator Systems (ADS) Conference;2013-03-23

4. Low Density Supersonic Decelerator Parachute Decelerator System;AIAA Aerodynamic Decelerator Systems (ADS) Conference;2013-03-23

5. Mars Scout Phoenix Parachute System Performance;20th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar;2009-05-04

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