Six-Axis Thruster Characterization Technique for Small Satellites

Elandt, Ryan; Aslan, Stewart; Peck, Mason A.

doi:10.2514/6.2017-0482

Cited by 3 publications

(2 citation statements)

References 14 publications

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“…Details of the experimental setup and post processing involved can be found in Ref. 8. The test setup enables measurements of all three forces and moments in the form of strain via known linear relationships.…”

Section: Propulsion System Performancementioning

confidence: 99%

An Innovative Control Allocation Scheme to Address Reaction Thruster Interactions on a 3U CubeSat

Pei

Choueiri

Elandt

et al. 2018

2018 AIAA Guidance, Navigation, and Control Conference

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A wealth of literature exists on control allocation algorithms for over-actuated air vehicles, launch vehicles, and spacecrafts. Most of these algorithms focus primarily on minimizing some objective function such as command tracking error and/or control effector usage. Linear allocators (pseudo inverses) are usually the conventional choice due to their simplicity and the ability to achieve a significant portion of the theoretical moment/impulse space. Generally, it is assumed that there exists minimal interaction effects between control effectors. In fact, very few studies address the problem of control effector interactions in the context of control allocation, especially for small spacecrafts with a reaction control system (RCS). This paper presents a CubeSat RCS design with a four thruster tetrahedral layout such that when two or more thrusters fire, the resultant impulse differs noticeably compared to the sum of the contributions from individual thruster firings. This undesirable effect is caused by the design of the propellant tank and regulator. To mitigate this issue, an innovative modified pseudo inverse (MPI) control allocation algorithm was developed that adjusts the pseudo inverse solution based on test data. The algorithm is iteration-free and superior to the standard pseudo inverse in minimizing the command tracking error.

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Section: Propulsion System Performancementioning

confidence: 99%

An Innovative Control Allocation Scheme to Address Reaction Thruster Interactions on a 3U CubeSat

Pei

Choueiri

Elandt

et al. 2018

2018 AIAA Guidance, Navigation, and Control Conference

Self Cite

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show abstract

“…Details of the experimental setup and post processing steps can be found in Ref. 11 The test setup enables the measurement of all three forces and moments. For a given run during the characterization test, the thruster combination (1 thruster, 2 thruster, 3 thruster firings, 14 total) and on-times (0.02 to 0.2 seconds) was selected at random.…”

Section: A Propulsionmentioning

confidence: 99%

Ground Demonstration on the Autonomous Docking of Two 3U CubeSats Using a Novel Permanent Magnet Docking Mechanism

Pei

Murchison²,

BenShabat³

et al. 2017

55th AIAA Aerospace Sciences Meeting

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Small spacecraft autonomous rendezvous and docking is an essential technology for future space structure assembly missions. A novel magnetic capture and latching mechanism is analyzed that allows for docking of two CubeSats without precise sensors and actuators. The proposed magnetic docking hardware not only provides the means to latch the CubeSats but it also significantly increases the likelihood of successful docking in the presence of relative attitude and position errors. The simplicity of the design allows it to be implemented on many CubeSat rendezvous missions. A CubeSat 3-DOF ground demonstration effort is on-going at NASA Langley Research Center that enables hardware-in-the loop testing of the autonomous approach and docking of a follower CubeSat to an identical leader CubeSat. The test setup consists of a 3 meter by 4 meter granite table and two nearly frictionless air bearing systems that support the two CubeSats . Four cold-gas on-off thrusters are used to translate the follower towards the leader, while a single reaction wheel is used to control the attitude of each CubeSat. An innovative modified pseudo inverse control allocation scheme was developed to address interactions between control effectors. The docking procedure requires relatively high actuator precision, a novel miminal impulse bit mitigation algorithm was developed to minimize the undesirable deadzone effects of the thrusters. Simulation of the ground demonstration shows that the Guidance, Navigation, and Control system along with the docking subsystem leads to successful docking under 3-sigma dispersions for all key system parameters. Extensive simulation and ground testing will provide sufficient confidence that the proposed docking mechanism along with the choosen suite of sensors and actuators will perform successful docking in the space environment.

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An Adaptable, Modular Cold-Gas Propulsion System for Small Satellite Applications

Aslan

Fares

DiStefano

et al. 2020

AIAA Scitech 2020 Forum

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Six-Axis Thruster Characterization Technique for Small Satellites

Cited by 3 publications

References 14 publications

An Innovative Control Allocation Scheme to Address Reaction Thruster Interactions on a 3U CubeSat

An Innovative Control Allocation Scheme to Address Reaction Thruster Interactions on a 3U CubeSat

Ground Demonstration on the Autonomous Docking of Two 3U CubeSats Using a Novel Permanent Magnet Docking Mechanism

An Adaptable, Modular Cold-Gas Propulsion System for Small Satellite Applications

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