Session
Technical Session 11: Propulsion
Location
Utah State University, Logan, UT
Abstract
The Integrated Propulsion System (IPS) is a bolt-on green monopropellant propulsion system specifically designed for ESPA-class Small Satellites. The purpose of this paper is to document Proto-flight testing of three Integrated Propulsion Systems.
The objective of Proto-flight testing is to certify systems for flight while preserving their ability to be subsequently flown and fulfill their mission requirements. This approach is widely used in the Small Sat community where program lead times are short and budgets tight.
Proto-flight testing of the Integrated Propulsion Systems combined both acceptance testing that screen for workmanship and qualification testing that verifies the design. As with conventional propulsion systems, Integrated Propulsion Systems are not hot fire tested at the system level. The LMP-103S 1N thrusters were already space qualified with 82 units successfully flown on 21 different spacecraft. For this application each of the twelve thrusters used were acceptance tested, including hot fire testing, at the thruster level. In parallel, the IPS systems were Protoflight tested with mass simulators in place of thrusters. After the thrusters were mounted, final electrical and functional checks were performed.
The subject paper is a follow-up to SSC20-IX-02 presented at the 2020 Small Sat Conference where Engineering Model testing, thruster hot fire acceptance testing and system Burst Testing results were presented. Now that Proto-flight testing is complete and the units have been delivered, the proposed paper will summarize the balance of test data and compare results with failure criteria. Specific data to be presented includes inspection for dimensional / mass compliance, proof pressure testing, electrical functional testing, surrogate liquid functional testing (including vibration to proto-flight levels) and proto-flight thermal vacuum testing.
The Integrated Propulsion System is a smart system with an integral microprocessor and flight software. Proto-flight testing includes a full suite of tests and calibration checks performed to verify compliant controller operation. Controller testing included output voltage, valve driver power step-down and data acquisition accuracy. Software was tested by virtue of operating the system during Proto-flight testing.
The capabilities of the Integrated Propulsion System are a key asset to the Small Satellite community. This paper will be a valuable tool for potential users to evaluate it against their mission requirements.
Proto-Flight Testing of a Green Monopropellant Integrated Propulsion System
Utah State University, Logan, UT
The Integrated Propulsion System (IPS) is a bolt-on green monopropellant propulsion system specifically designed for ESPA-class Small Satellites. The purpose of this paper is to document Proto-flight testing of three Integrated Propulsion Systems.
The objective of Proto-flight testing is to certify systems for flight while preserving their ability to be subsequently flown and fulfill their mission requirements. This approach is widely used in the Small Sat community where program lead times are short and budgets tight.
Proto-flight testing of the Integrated Propulsion Systems combined both acceptance testing that screen for workmanship and qualification testing that verifies the design. As with conventional propulsion systems, Integrated Propulsion Systems are not hot fire tested at the system level. The LMP-103S 1N thrusters were already space qualified with 82 units successfully flown on 21 different spacecraft. For this application each of the twelve thrusters used were acceptance tested, including hot fire testing, at the thruster level. In parallel, the IPS systems were Protoflight tested with mass simulators in place of thrusters. After the thrusters were mounted, final electrical and functional checks were performed.
The subject paper is a follow-up to SSC20-IX-02 presented at the 2020 Small Sat Conference where Engineering Model testing, thruster hot fire acceptance testing and system Burst Testing results were presented. Now that Proto-flight testing is complete and the units have been delivered, the proposed paper will summarize the balance of test data and compare results with failure criteria. Specific data to be presented includes inspection for dimensional / mass compliance, proof pressure testing, electrical functional testing, surrogate liquid functional testing (including vibration to proto-flight levels) and proto-flight thermal vacuum testing.
The Integrated Propulsion System is a smart system with an integral microprocessor and flight software. Proto-flight testing includes a full suite of tests and calibration checks performed to verify compliant controller operation. Controller testing included output voltage, valve driver power step-down and data acquisition accuracy. Software was tested by virtue of operating the system during Proto-flight testing.
The capabilities of the Integrated Propulsion System are a key asset to the Small Satellite community. This paper will be a valuable tool for potential users to evaluate it against their mission requirements.
