NTRS - NASA Technical Reports Server

Back to Results
Design, Instrumentation, and Data Analysis for the SLS Core Stage Green Run Test SeriesThe Space Launch System (SLS) Core Stage (CS) Thrust Vector Control (TVC) system is comprised of eight mechanical feedback Shuttle heritage Type III TVC actuators and four RS-25 engines, each attached to a Shuttle heritage gimbal block/bearing. The actuators are powered by a Shuttle-derived hydraulic Core Auxiliary Power Unit (CAPU), and integrated with an all-new Core Stage thrust structure. The actuators are interfaced to the SLS Vehicle Management (VM) software via an all-new TVC Actuator Control (TAC) avionics subsystem. Despite the significant test and flight experience of the Shuttle hardware, the SLS Green Run ambient and hot fire test activities revealed a number of new findings associated with the dynamic response of the TVC integrated system. Test responses suggested that the TVC system did not meet its performance specifications and its step and frequency responses exhibited unexpected departures from prior lab tests and modeled behavior. This paper is the fifth installment in a seven-paper series surveying the design, engineering, test validation, and flight performance of the Core Stage Thrust Vector Control system. In this paper, the design of the TVC analyses conducted during the Core Stage Green Run test series are discussed in detail. Throughout the course of the test activities, the SLS flight control team worked diligently with the Core Stage contractor to revise test command profiles and ensure sufficient instrumentation was available to collect data. Post-test analysis combined the Green Run modal, ambient, and hot fire test data, MSFC 2- axis Core Stage TVC Inertial Load Simulator (ILS) data, Hardware-In-the-Loop (HWIL) Systems Integration Lab (SIL) results, and actuator Acceptance Testing Procedure (ATP) responses. These data were used to characterize the response, validate critical math models of the TVC subsystem, and isolate the probable cause of the unexpected responses. Through comprehensive analysis of the available test data sources, the integrated team identified the dominant contributors to the observed response and developed test-correlated rationale for vehicle flight control system performance, ultimately leading to a confident posture for the Artemis I mission.
Document ID
Acquisition Source
Marshall Space Flight Center
Document Type
Conference Paper
John H. Wall
(McLaurin Aerospace)
Chris Russell
(Boeing (United States) Chicago, Illinois, United States)
Richard K. Moore
(McLaurin Aerospace)
Jeb S. Orr
(McLaurin Aerospace)
Abran Alaniz
(McLaurin Aerospace)
Stephen G. Ryan
(Manufacturing Technical Solutions Huntsville, AL)
Date Acquired
January 13, 2023
Subject Category
Astronautics (General)
Aircraft Design, Testing and Performance
Report/Patent Number
AAS 23-156
Meeting Information
Meeting: 45th American Astronautical Society Guidance, Navigation, and Control Conference
Location: Breckenridge, CO
Country: US
Start Date: February 2, 2023
End Date: February 8, 2023
Sponsors: American Astronomical Society
Funding Number(s)
Distribution Limits
Public Use Permitted.
Technical Review
Single Expert
No Preview Available