Analysis of spacecraft entry into Mars atmosphere
Abstract
The effects on a spacecraft body while entering the Martian atmosphere and the resulting design constraints are analyzed. The analyses are conducted using the Viking entry phase restriction conditions and a Mars atmosphere model. Results from analysis conducted by the Program to Optimize Simulated Trajectories (POST) are described. Results obtained from the analysis are as follows: (1) flight times depend greatly on lift-to-drag ratio and less on ballistic coefficients; (2) terminal landing speeds depend greatly on ballistic coefficients and less on lift-to-drag ratios; (3) the dependence of the flight path angles on ballistic coefficients is slightly larger than their dependence on lift-to-drag ratios; (4) as the ballistic coefficients become smaller and the lift-to-drag ratios become larger, the deceleration at high altitude becomes larger; (5) small ballistic coefficients and low lift-to-drag ratios are required to meet the constraints of Mach number at parachute deployment and deployment altitude; and (6) heating rates at stagnation points are dependent on ballistic coefficients. It is presumed that the aerodynamic characteristics will be 0.2 for the lift-to-drag ratio and 75 kg/sq m for the ballistic coefficient for the case of a Mars landing using capsules similar to those used in the Viking program.
- Publication:
-
Future Space Activities Workshop
- Pub Date:
- July 1991
- Bibcode:
- 1991fsa..workU....N
- Keywords:
-
- Aerodynamic Characteristics;
- Flight Mechanics;
- Hypersonic Reentry;
- Mars (Planet);
- Mars Atmosphere;
- Mars Landing;
- Mars Probes;
- Space Exploration;
- Spacecraft Reentry;
- Aerodynamic Heating;
- Atmospheric Density;
- Atmospheric Models;
- Atmospheric Temperature;
- Dynamic Pressure;
- Flight Paths;
- Flight Time;
- Mariner Space Probes;
- Viking Orbiter Spacecraft;
- Spacecraft Design, Testing and Performance