Performance enhancement of disturbance-free payload with a novel design of architecture and control

Kong, Yongfang

doi:10.1016/j.actaastro.2019.03.061

Cited by 16 publications

(8 citation statements)

References 28 publications

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“…where Θ sp = ½φ sp , θ sp , ψ sp T represents the attitude angle error angle of the service module relative to the three-axis of the payload module. Substituting Equation (15) into Equation ( 11), the relative attitude dynamics equation has the following expression:…”

Section: Collision Avoiding Control Of Service Modulementioning

confidence: 99%

“…However, it is insufficient to verify the multidynamics coupling problem of the noncontact close-proximity formation satellite architecture. The three-axis coupling dynamic model of the noncontact close-proximity formation satellite has been conducted by Newton-Euler approach, indicating that the current driving accuracy of the noncontact Lorentz actuator plays the most important role in the whole architecture control [15][16][17]. The optimization approaches based on multiphysical fields have been proposed to resolve the contradiction between the high power and low ripple, leading to a resolution with ppm within its air clearance [18].…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Compound Attitude Maneuver and Collision Avoiding Control for a Novel Noncontact Close-Proximity Formation Satellite Architecture

Liao

Xie²,

Zhou³

et al. 2022

International Journal of Aerospace Engineering

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In order to achieve the attitude maneuver performance of the noncontact close-proximity formation satellite architecture, this paper presents a compound control strategy with variable-parameter sliding mode control and disturbance observer-based feedforward compensation. Firstly, the variable-parameter sliding mode control is proposed to guarantee the attitude maneuver performance of the payload module. Secondly, the collision avoiding control with disturbance observer-based feedforward compensation is proposed to guarantee the synchronization of the two separated modules within the small air clearance constraint of the noncontact Lorentz actuator. Finally, a physical air-floating platform is established to verify the effectiveness of the proposed approach.

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Section: Collision Avoiding Control Of Service Modulementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Compound Attitude Maneuver and Collision Avoiding Control for a Novel Noncontact Close-Proximity Formation Satellite Architecture

Liao

Xie²,

Zhou³

et al. 2022

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

show abstract

“…τ cons (t) . (17) According to Assumption 1 and Equation ( 12), τ cons (t) is bound and differentiable. Therefore, we can assume that there exists a positive constant γ satisfies τ cons (t) ≤ γ, integrate both sides of Equation ( 17), we can obtain:…”

Section: Feasibility Analysismentioning

confidence: 99%

“…However, previous research has equipped cables between the two modules. The coupling effect of the non-contact interface created by the translational and torsional stiffness of the cable affects the attitude control performance of the PM [14][15][16][17], which contradicts the original purpose of the non-contact design. In addition, the analysis of the cable effects is included in the on-orbit validation of the non-contact platform by Lockheed Martin [18].…”

Section: Introductionmentioning

confidence: 98%

Event-Triggered Attitude-Tracking Control for a Cableless Non-Contact Close-Proximity Formation Satellite

Liao

et al. 2022

Aerospace

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The cablelessness of non-contact close-proximity formation satellites can fundamentally avoid the influence of non-contact interface coupling effects and can further enhance the attitude pointing accuracy and stability of the payload module (PM). However, it also brings the problem of limited on-board resources and system latency. In this paper, an event-triggered attitude tracking controller of the support module (SM) that avoids the Zeno phenomenon was proposed. The update time of the control signal was determined by the event-triggering mechanism based on intermediate variables, thus, reducing the communication burden and actuator asynchrony between the two modules. The feasibility and effectiveness of the proposed approach was demonstrated by numerical simulations.

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“…To accommodate launch and in-orbit mechanics conditions, there are two main types of modern satellite design solutions. One is the traditional satellite development idea of separating the payload and satellite bus development, and this design approach is pushing engineers to make their allocated system much redundant, which will increase the satellite system mass, size, and cost, and it is no longer suitable for today’s development trend (Guo et al, 2018; Kong and Huang, 2019; Tang et al, 2020). The other is a payload-centered, structurally integrated satellite design, which focuses on the optical payload and takes into account the interests of both the optical payload and the satellite bus, and it integrates the optical payload design and bus design to optimize the overall performance of the satellite by considering the satellite mass, volume, launch phase dynamics response, and in-orbit micro-vibration response.…”

Section: Introductionmentioning

confidence: 99%

Study of the multi-excitation decoupling optimization method for the integrated structure of a high-resolution optical satellite

Yang

Wang

2022

Journal of Vibration and Control

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In this paper, the sensitive frequency band for distortion and blurring phenomena of the in-orbit satellite is studied and the results are supplements for existing studies and can provide an important reference for the study of micro-vibration. To contain the large-amplitude and micro-vibration excitation response in this sensitive frequency band, a multi-excitation decoupling optimization method is proposed for the integrated structure of high-resolution optical satellites. First, the equivalent dynamics models of the satellite with and without an vibration isolator are established. By deriving the functional relationship between satellite bus stiffness, vibration isolator stiffness, and vibration isolation efficiency, the design objectives can be decoupled and assigned to the vibration isolator and satellite bus in a more cost-effective way, respectively, while maintaining a low computation volume of the multi-objective and multi-variable system optimization. Then, the satellite system is optimized with the objectives of minimizing the large-amplitude vibration response in the launch phase and the micro-vibration response in the orbital operation phase using the NSGA-II genetic algorithm. Finally, the design is verified by ground experiments that it can fully achieve required technical parameters under multiple vibration excitations. This method has certain reference value for the design of complex structural systems of high-resolution satellites.

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Performance enhancement of disturbance-free payload with a novel design of architecture and control

Cited by 16 publications

References 28 publications

Compound Attitude Maneuver and Collision Avoiding Control for a Novel Noncontact Close-Proximity Formation Satellite Architecture

Compound Attitude Maneuver and Collision Avoiding Control for a Novel Noncontact Close-Proximity Formation Satellite Architecture

Event-Triggered Attitude-Tracking Control for a Cableless Non-Contact Close-Proximity Formation Satellite

Study of the multi-excitation decoupling optimization method for the integrated structure of a high-resolution optical satellite

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