Session
Technical Session VII: New Mission or Bus Concepts I
Abstract
This paper describes the development of a simple low-cost Mars microlander that is matched to the capabilities of the recently-approved Mars Micromission program. This particular microlander design is intended to fill a capability gap between two existing landing systems: the large sophisticated soft landers like Mars Polar Lander and the miniaturized DS-2-class penetrators. This microlander would be able to deliver (in a controlled manner) a small but sophisticated science payload to multiple, exciting but risky landing sites (as an example for our point design, we have used the delivery of the 60% scale Sojourner-class minirover). The unique attribute of this design is the maximum exploitation of existing technology that is integrated in a unprecedented-simple lander system configuration. This inherent simplicity results in the system that is simultaneously low-cost and robust (and thus reliable). Two key technologies are employed in the microlander design: small solid rocket propulsion (commercially available) with adequate performance, and integrated FM-CW radar sensor (also commercially available) that is used as the only guidance sensor.The lander design is intended to be field tested soon in order to maximize the probability of mission success.
Design of Simple Low-Cost Mars Microlander
This paper describes the development of a simple low-cost Mars microlander that is matched to the capabilities of the recently-approved Mars Micromission program. This particular microlander design is intended to fill a capability gap between two existing landing systems: the large sophisticated soft landers like Mars Polar Lander and the miniaturized DS-2-class penetrators. This microlander would be able to deliver (in a controlled manner) a small but sophisticated science payload to multiple, exciting but risky landing sites (as an example for our point design, we have used the delivery of the 60% scale Sojourner-class minirover). The unique attribute of this design is the maximum exploitation of existing technology that is integrated in a unprecedented-simple lander system configuration. This inherent simplicity results in the system that is simultaneously low-cost and robust (and thus reliable). Two key technologies are employed in the microlander design: small solid rocket propulsion (commercially available) with adequate performance, and integrated FM-CW radar sensor (also commercially available) that is used as the only guidance sensor.The lander design is intended to be field tested soon in order to maximize the probability of mission success.
