The performance of the Viking lander has been evaluated by using a Monte Carlo simulation, and all results are presented in statistical form. The primary objectives of this analysis were as follows: (1) to determine the three sigma design values of maximum rigid body accelerations and the minimum clearance of the lander body during landing; (2) to determine the probability of an unstable landing; and (3) to determine the probability of the lander body striking a rock. Two configurations were analyzed with the only difference being in the ability of the primary landing gear struts to carry tension loads
Related space mission data for baseline evaluation of Viking Lander design and operatio
A six-degree-of-freedom analytical simulation of parachute deployment dynamics developed at the Lang...
In the study of entry, descent, and landing, Monte Carlo sampling methods are often employed to stud...
A limited analytical investigation was conducted to assess the effects of structural elasticity on t...
Wind tunnel tests to determine aerodynamic characteristics of Viking spacecraft entry and lander con...
Flight qualifications for parachutes were tested on full-scale simulated Viking spacecraft at entry ...
Validation of a landing-dynamics computer program has been accomplished by comparing analytical data...
Comparisons are made between the LAURA Navier-Stokes code and Viking Lander Capsule hypersonic aerod...
Simulation calculations of the Viking qualification flight tests are conducted by use of analytical ...
Technique for conducting landing impact tests at simulated planetary gravity for Mars lander spacecr...
This report presents the results of Viking Aerothermodynamics Test D4-34.0. Motion picture coverage ...
Monte Carlo method for determination of touchdown dynamics for soft lunar landin
Longitudinal aerodynamic characteristics of Viking lander spacecraft at hypersonic spee
This thesis investigates the residual kinetic energy of three energy dissipation mechanisms being ap...
Tests of the Viking 16.15-meter nominal-diameter disk-gap-band parachute were conducted at Mach numb...
Related space mission data for baseline evaluation of Viking Lander design and operatio
A six-degree-of-freedom analytical simulation of parachute deployment dynamics developed at the Lang...
In the study of entry, descent, and landing, Monte Carlo sampling methods are often employed to stud...
A limited analytical investigation was conducted to assess the effects of structural elasticity on t...
Wind tunnel tests to determine aerodynamic characteristics of Viking spacecraft entry and lander con...
Flight qualifications for parachutes were tested on full-scale simulated Viking spacecraft at entry ...
Validation of a landing-dynamics computer program has been accomplished by comparing analytical data...
Comparisons are made between the LAURA Navier-Stokes code and Viking Lander Capsule hypersonic aerod...
Simulation calculations of the Viking qualification flight tests are conducted by use of analytical ...
Technique for conducting landing impact tests at simulated planetary gravity for Mars lander spacecr...
This report presents the results of Viking Aerothermodynamics Test D4-34.0. Motion picture coverage ...
Monte Carlo method for determination of touchdown dynamics for soft lunar landin
Longitudinal aerodynamic characteristics of Viking lander spacecraft at hypersonic spee
This thesis investigates the residual kinetic energy of three energy dissipation mechanisms being ap...
Tests of the Viking 16.15-meter nominal-diameter disk-gap-band parachute were conducted at Mach numb...
Related space mission data for baseline evaluation of Viking Lander design and operatio
A six-degree-of-freedom analytical simulation of parachute deployment dynamics developed at the Lang...
In the study of entry, descent, and landing, Monte Carlo sampling methods are often employed to stud...