Satellite Formation Flying Design and Evolution

Sabol, Chris; Burns, Rich; McLaughlin, Craig

doi:10.2514/2.3681

Cited by 304 publications

(143 citation statements)

References 11 publications

Supporting

Mentioning

138

Contrasting

Unclassified

Order By: Relevance

“…(25) makes the relative motion bounded for every axis, and it also matches the solutions of the HCW equations satisfying the constraint Eq. (26) [27]. Since Eqs.…”

Section: Controlled Motionmentioning

confidence: 99%

See 1 more Smart Citation

Explicit solution to the full nonlinear problem for satellite formation-keeping

Cho

Udwadia

2010

Acta Astronautica

View full text Add to dashboard Cite

a b s t r a c tThis paper presents simple and exact formation-keeping guidance schemes that use a new method that is rooted in some recent advances in analytical dynamics. As a result of this new approach, explicit control inputs to exactly maintain a given formation configuration are easily determined using continuous thrust propulsion systems. The complete nonlinear problem is addressed, and no linearizations and/or approximations are made. The approach provides a marked improvement over existing results in that the control forces, which cause geometric formation-keeping constraints to be exactly satisfied for arbitrary reference orbits, are found in closed form. For Keplerian reference orbits, a much simpler and explicit expression for the control needed to exactly satisfy formation-keeping constraints than hereto available is obtained. The paper also includes explicit control results when the follower is inserted into orbit with incorrect initial conditions, as usually happens in practice. The Hill reference frame, which is often more intuitive for formation-keeping, is used in the analysis. While this paper takes an example of a projected circular formation, the methodology that is developed can be applied to any desired configuration or orbital requirements. Extensive computational simulations are performed to demonstrate the ease of implementation, and the numerical accuracy provided by the approach developed herein.

show abstract

“…(25) makes the relative motion bounded for every axis, and it also matches the solutions of the HCW equations satisfying the constraint Eq. (26) [27]. Since Eqs.…”

Section: Controlled Motionmentioning

confidence: 99%

“…This geometry has significant practical utility. Besides being rigorously investigated in many papers [8,10,27], it was planned [14] to be used for the TechSat-21 mission which was, unfortunately, cancelled later on. We assume unbounded continuous burn throughout the maneuvers and place no restrictions on the leader's reference orbit.…”

Section: Article In Pressmentioning

confidence: 99%

Explicit solution to the full nonlinear problem for satellite formation-keeping

Cho

Udwadia

2010

Acta Astronautica

View full text Add to dashboard Cite

show abstract

“…nano-satellite and pico-satellites, to achieve complex space missions (Barnhart, et al, 2007). Depending on the application, the formation flying can be specified into distinct kinds (Sabol, et al 2001;Burns, et al, 2000) . These types include:…”

Section: Structurementioning

confidence: 99%

1-Bit processing based model predictive control for fractionated satellite missions

Bai

2014

Acta Astronautica

View full text Add to dashboard Cite

In this thesis, a 1-bit processing based Model Predictive Control (OBMPC) structure is proposed for a fractionated satellite attitude control mission. Despite the appealing advantages of the MPC algorithm towards constrained MIMO control applications, implementing the MPC algorithm onboard a small satellite is certainly challenging due to the limited onboard resources. The proposed design is based on the 1-bit processing concept, which takes advantage of the affine relation between the 1-bit state feedback and multi-bit parameters to implement a multiplier free MPC controller.As multipliers are the major power consumer in online optimization, the OBMPC structure is proven to be more efficient in comparison to the conventional MPC implementation in term of power and circuit complexity. The system is in digital control nature, affected by quantization noise introduced by Δ∑ modulators. The stability issues and practical design criteria are also discussed in this work.Some other aspects are considered in this work to complete the control system. Firstly, the implementation of the OBMPC system relies on the 1-bit state feedbacks. Hence, 1-bit sensing components are needed to implement the OBMPC system. While the ∆∑ modulator based Microelectromechanical systems (MEMS) gyroscope is considered in this work, it is possible to implement this concept into other sensing components.Secondly, as the proposed attitude mission is based on the wireless inter-satellite link (ISL), a state estimator is required. However, conventional state estimators will once again introduce multi-bit signals, and compromise the simple, direct implementation of the OBMPC controller. Therefore, the 1-bit state estimator is also designed in this work to satisfy the requirements of the proposed fractionated attitude control mission.The simulation for the OBMPC is based on a 2U CubeSat model in a fractionated satellite structure, in which the payload and actuators are separated from the controller and controlled via the ISL. Matlab simulations and FPGA implementation based performance analysis shows that the OBMPC is feasible for fractionated satellite missions and is advantageous over the conventional MPC controllers. V VI

show abstract

“…Qingsong et al ͑2004͒ solved this formation-keeping problem by using a low-thrust fuzzy control method. However, Yan and others ͑Yan et al 2000;Sparks 2000;Sabol et al 2001;Armellin et al 2004;Qingsong et al 2004͒ made use of the linearized equations of relative motion, and hence the methods thus derived are suitable only for very close formations.…”

Section: Introductionmentioning

confidence: 99%

New Approach to Satellite Formation-Keeping: Exact Solution to the Full Nonlinear Problem

Cho

2009

J. Aerosp. Eng.

View full text Add to dashboard Cite

This paper presents a new, simple, and exact solution to the formation keeping of satellites when the relative distance between the satellites is so large that the linearized relative equations of motion no longer hold. We employ a recently proposed approach, the Udwadia-Kalaba approach, which makes it possible to explicitly obtain the desired control function without making any approximations related to the nonlinearities in the underlying dynamics. We use an inertial frame of reference to describe the motion of a satellite and since no approximations are made, the results obtained apply to situations even when the distance between the satellites is arbitrarily large. The paper deals with a projected circular formation, but the methodology in this paper can be applied to any desired configuration or orbital requirements. Numerical simulations confirm the brevity and the accuracy of the analytical solution to the dynamical control problem developed herein.

show abstract

Satellite Formation Flying Design and Evolution

Cited by 304 publications

References 11 publications

Explicit solution to the full nonlinear problem for satellite formation-keeping

Explicit solution to the full nonlinear problem for satellite formation-keeping

1-Bit processing based model predictive control for fractionated satellite missions

New Approach to Satellite Formation-Keeping: Exact Solution to the Full Nonlinear Problem

Contact Info

Product

Resources

About