A time suboptimal method for real-time spacecraft attitude agile maneuvering with angular velocity constraint

Wu, Yunhua; Hu, Yabo; Hua, Bing; Chen, Zhiming; Ge, Linlin

doi:10.1177/0954410017733017

Cited by 9 publications

(6 citation statements)

References 19 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Other approaches have been developed in an attempt to perform the maneuver design step on board the spacecraft. For example, Wu et al 16 proposed an interpolation scheme that uses a series of rules for performing suboptimal reorientation maneuvers in the open-loop. A closed-loop control was used to cancel any remaining pointing error.…”

Section: Introductionmentioning

confidence: 99%

Efficient on board storage and retrieval of fast maneuver profiles for space applications

Karpenko

Cristi

Levitas

2023

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

Attitude guidance is a concept for implementing performance enhancing rotational maneuvers that uses a conventional closed-loop attitude control system to track an optimized maneuver trajectory. Minimum-time attitude guidance is presently being used for executing fast occultation avoidance maneuvers on NASA’s Lunar Reconnaissance Orbiter (LRO). A challenge in operationalizing the idea is related to the limited size of the spacecraft’s command buffer, which was not designed with maneuver tracking in mind. In this paper, we propose an interpolating pre-filter built on B-splines that can be used on board to process downsampled maneuver commands (to save buffer space) and provide attitude control inputs at the servo-rate. The approach is validated using a high-fidelity simulation of the LRO developed at NASA’s Goddard Space Flight Center.

show abstract

Section: Introductionmentioning

confidence: 99%

Efficient on board storage and retrieval of fast maneuver profiles for space applications

Karpenko

Cristi

Levitas

2023

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

show abstract

“…Because ACSs are normally designed to respond to large step changes in the desired attitude, there is typically a limit to the number of commands that can be uplinked and subsequently issued to perform a coordinated multiaxis slew. One recent approach for side-stepping this problem was presented by Wu et al, 14 who proposed an interpolation scheme that uses a series of rules for performing suboptimal reorientation maneuvers in the open loop. A closed-loop control was used to cancel any remaining pointing error.…”

Section: Introductionmentioning

confidence: 99%

Waypoint following dynamics of a quaternion error feedback attitude control system

Karpenko

Halverson

Besser

2021

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

Closed-loop attitude steering is a concept for implementing an attitude trajectory by using a conventional quaternion error feedback controller to track the time-varying attitude reference, rather than to simply regulate to a desired orientation. This is done by sampling the reference input and executing the maneuver as a sequence of closely spaced regulating commands that are read out from the spacecraft’s command buffer. The idea has been employed in practice to perform zero-propellant maneuvers on the International Space Station and minimum-time maneuvers on NASA’s TRACE space telescope as well as NASA’s Lunar Reconnaissance Orbiter (LRO). A challenge for operational implementation of the idea is the limited capacity of a space vehicle’s command storage buffer, which is normally not designed with attitude tracking in mind. One approach to mitigate the problem is to downsample-and-hold the attitude commands so that the attitude control system (ACS) regulates to a series of waypoints. This article explores the waypoint following dynamics of a quaternion error feedback control law for such an approach. It is shown that downsample-and-hold induces a ripple between downsamples that causes the satellite angular rate to significantly overshoot the desired limit. Analysis in the z-domain is carried out in order to understand the phenomenon. An interpolating Chebyshev-type filter is proposed that allows the desired attitude trajectory to alternatively be encoded in terms of a small set of filter coefficients. Using the interpolating filter, the continuous-time reference trajectory can be reconstructed and issued at the ACS rate but with significantly reduced memory requirements. The ACS of the LRO is used as an example to illustrate the behavior of a practical ACS.

show abstract

“…Small satellites like ASNARO have been required to maneuver rapidly in missions such as fast three-dimensional imaging, multi-target acquisition, etc. [4,5]. Small observation satellites are required to increase the time required for data communication because it get a lot of observation data in a day.…”

Section: Introductionmentioning

confidence: 99%

Minimum-Time Attitude Maneuver and Robust Attitude Control of Small Satellite Mounted with Data Relay Communication Antenna

Mori

Takahashi

2019

Applied Sciences

View full text Add to dashboard Cite

This paper proposes a nonlinear control method for carrying out Minimum-time satellite attitude maneuver and antenna motion which have robustness against model uncertainty. In recent years, small Earth observation satellites have been utilized and expected to maneuver rapidly in missions such as multi-target acquisition. On the other hand, small satellites need to send the observation data to ground station. Recently, small Earth observation satellites acquire high-resolution data, resulting in an increase in the time required for data communication. Thus, small satellites need to use inter-orbit communication link through Data Relay test satellite sending data from Data Relay communication (DRC) antenna. In conventional operations, the antenna motion is implemented after satellite attitude maneuver. However, this method has a time delay between the completion of the attitude maneuver and the start of data communication. The purpose of this study is to extend the time of earth observation and data communication by carrying out satellite maneuver and antenna motion concurrently. Because small satellite mounted with DRC antenna has large mass ratio of the antenna, we cannot ignore time variability of the moment of inertia of the whole system and reaction torque generated by antenna motion. Hence, in order to take the influence of the antenna motion into consideration, we combine a satellite attitude control system and an antenna drive system into one control system by governing equations and constructing the optimal control problem. We convert the optimal control problem into a NLP by discretizing the control input (a series of pulses) to minimize the final time of the total maneuver that includes the antenna adjustment. In addition, it is considered that a model uncertainty and unknown disturbance occurs in real space. Thus, we have to design feedback controller to secure robustness in model error and unknown disturbance. Accordingly in order to propose a nonlinear control method for carrying out minimum-time satellite attitude maneuver and antenna motion which have robustness against model uncertainty and unknown disturbance, we calculate a reference attitude by application of optimal control input torque to ideal satellite model and design servo controller by using state-dependent Riccati equation (SDRE) control method in order to track time-variant reference attitude.

show abstract

A time suboptimal method for real-time spacecraft attitude agile maneuvering with angular velocity constraint

Cited by 9 publications

References 19 publications

Efficient on board storage and retrieval of fast maneuver profiles for space applications

Efficient on board storage and retrieval of fast maneuver profiles for space applications

Waypoint following dynamics of a quaternion error feedback attitude control system

Minimum-Time Attitude Maneuver and Robust Attitude Control of Small Satellite Mounted with Data Relay Communication Antenna

Contact Info

Product

Resources

About