Session
Technical Poster Session 4
Location
Utah State University, Logan, UT
Abstract
With recent and upcoming initiatives to revisit the moon and to begin planning for sending humans to Mars, the role of small spacecraft to facilitate and compliment these types of missions continues to grow. However, unlike low-Earth orbit (LEO), where small satellites have historically found their highest utilization, venturing further away from Earth and the more benign space environment it provides can prove to be a challenge for spacecraft designers. Factors can become difficult to design for, such as expected temperature ranges, power generation and radiation effects. At the same time, the objectives that small spacecraft are attempting to accomplish are becoming more and more complex as the capabilities of these spacecraft continues to grow. One example of this increasing complexity can be found in Rendezvous and Proximity Operations (RPO) missions, where spacecraft attempt to perform tasks involving on-orbit servicing, docking, active debris removal, formation flying, inspection, or any other function that involves one or more satellites (natural or otherwise) matching their orbital plane, altitude and phasing while also performing maneuvers to approach at a close distance1.
As the number of small satellite missions operating beyond LEO grow, so too will the need for spacecraft that are capable of performing complex RPO. One key technology that is needed to facilitate these types of missions is a means of propulsion that is capable, reliable, and safe to use and handle. Benchmark Space Systems is poised to provide the mobility solutions that will enable these deep space missions to traverse the vast distances as well as help carry out the precise maneuvers necessary for these types of endeavors. One such example is the RPO Kit that Benchmark Space has recently developed for a commercial customer, whose mission objectives will take their spacecraft to Cislunar orbit.
Development of a Modular Propulsion System for Use in a Deep Space Hybrid Architecture
Utah State University, Logan, UT
With recent and upcoming initiatives to revisit the moon and to begin planning for sending humans to Mars, the role of small spacecraft to facilitate and compliment these types of missions continues to grow. However, unlike low-Earth orbit (LEO), where small satellites have historically found their highest utilization, venturing further away from Earth and the more benign space environment it provides can prove to be a challenge for spacecraft designers. Factors can become difficult to design for, such as expected temperature ranges, power generation and radiation effects. At the same time, the objectives that small spacecraft are attempting to accomplish are becoming more and more complex as the capabilities of these spacecraft continues to grow. One example of this increasing complexity can be found in Rendezvous and Proximity Operations (RPO) missions, where spacecraft attempt to perform tasks involving on-orbit servicing, docking, active debris removal, formation flying, inspection, or any other function that involves one or more satellites (natural or otherwise) matching their orbital plane, altitude and phasing while also performing maneuvers to approach at a close distance1.
As the number of small satellite missions operating beyond LEO grow, so too will the need for spacecraft that are capable of performing complex RPO. One key technology that is needed to facilitate these types of missions is a means of propulsion that is capable, reliable, and safe to use and handle. Benchmark Space Systems is poised to provide the mobility solutions that will enable these deep space missions to traverse the vast distances as well as help carry out the precise maneuvers necessary for these types of endeavors. One such example is the RPO Kit that Benchmark Space has recently developed for a commercial customer, whose mission objectives will take their spacecraft to Cislunar orbit.
