Laser space propulsion overview

Phipps,; Claude,; Luke,; James, Michael

doi:10.1117/12.738682

Cited by 7 publications

(8 citation statements)

References 16 publications

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“…For a formation near a libration point, spacecraft maneuvering exhibits the unusual limitation that ideal control solutions require thrust acceleration magnitudes smaller than existing technology can provide. [17][18][19][20][21][22] In addition, it is conceivable that spacecraft orientation may be restricted by mission requirements, which can inhibit maneuverability depending on the number and placement of thrusters on the spacecraft body. When these two conditions are combined, the control problem is extremely constrained, motivating the development of unique solution methods to handle these constraints.…”

Section: Transcription Formulations For the Actuator Constrained mentioning

confidence: 99%

“…15,16 The sensitivity of the dynamical regime near the libration points is apparent in the precise control requirements for non-natural formations derived in the above investigations. Some studies [17][18][19][20][21][22] focus on reducing the lower performance bounds on thruster technology. However, unconstrained control laws in this regime often require thrust levels below the limits of the technology presently available.…”

Section: Introductionmentioning

confidence: 99%

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Actuator Constrained Optimal Control of Formations Near the Libration Points

Stanton

Marchand

2008

AIAA/AAS Astrodynamics Specialist Conference and Exhibit

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Spacecraft applications like space-based interferometry have motivated investigations into the feasibility of spacecraft formations near the libration points of the Sun-Earth/Moon system. The sensitivity of the dynamical regime imposes extremely precise control requirements for non-natural formations. Unconstrained control laws tend to require acceleration magnitudes smaller than existing thruster technology can provide. In the present study, a methodology is presented that identifies actuator constrained solutions in the nonlinear model. The optimal solutions that ensue are attainable with existing technology and demonstrate the feasibility of spacecraft formationkeeping in the presence of actuator constraints in the Circular Restricted Three-Body Problem.

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Section: Transcription Formulations For the Actuator Constrained mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Actuator Constrained Optimal Control of Formations Near the Libration Points

Stanton

Marchand

2008

AIAA/AAS Astrodynamics Specialist Conference and Exhibit

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“…[18][19][20][21][22] The combination of these conditions constrain actuators to either thrust at their lower limits or not at all. This results in control solutions characterized by a switching schedule that can be optimized.…”

Section: • Chapter 3: Transcription Formulations For the Finite Set Cmentioning

confidence: 99%

“…While some studies [18][19][20][21][22] focus on reducing the lower performance bounds on thruster technology, unconstrained control laws in this regime often require thrust levels below the limits of the technology presently available. The associated control accelerations, though small, cannot be neglected if precision formation keeping is desired.…”

Section: Motivationmentioning

confidence: 99%

“…This example is specifically motivated by spacecraft limited to commercial off-the-shelf actuator technologies that are inexpensive and readily available. The available literature [18][19][20]22 indicates a range of new thruster technologies for small spacecraft that are currently under development. Although these may offer wide ranges of thrust magnitudes and performance efficiencies, it is interesting to explore how the capability of traditional technologies can be stretched to maximize performance.…”

Section: Small Spacecraft Attitude Controlmentioning

confidence: 99%

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Finite Set Control Transcription for Optimal Control Applications

Stanton

2010

Journal of Spacecraft and Rockets

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Impacts of laser pulse width and target thickness on laser micro-propulsion performance

Wang¹,

Du²,

Du³

et al. 2022

Plasma Sci. Technol.

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In order to optimize laser ablation performance of a micro-thruster with 1U dimensions, which employs a micro semiconductor laser, the impacts of pulse width and glycidyl azide polymer (GAP) thickness on thrust performance was researched. The results showed that with a GAP thickness of 200 μm, the single-pulse impulse (I) increased gradually with the increase in the laser pulse width from 50 to 800 μs, while the specific impulse (Isp), impulse coupling coefficient (Cm), and ablation efficiency (η) all reached optimal values with a 200 μs pulse width. It’s worth noting that the optimal pulse width is exactly the ignition delay time. Both Cm and η peaked with the pulse width of 200 μs, reaching 242.22 μN/W and 35.4%, respectively. With the increase in the GAP thickness, the I and the Cm increased gradually. The GAP of different thickness corresponded to different optimal laser pulse width. Under a certain laser pulse width, the optimal GAP thickness should be the most vertical thickness of the ablation pit, and the various propulsion performance parameters at this time were also optimal. With the current laser parameters, the optimal GAP thickness was approximately 150 μm, the Isp was approximately 322.22 s, and the η was approximately 34.94%.

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Laser space propulsion overview

Cited by 7 publications

References 16 publications

Actuator Constrained Optimal Control of Formations Near the Libration Points

Actuator Constrained Optimal Control of Formations Near the Libration Points

Finite Set Control Transcription for Optimal Control Applications

Impacts of laser pulse width and target thickness on laser micro-propulsion performance

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