Investigation of Reaction Control System Design on Spacecraft Handling Qualities for Docking

Bailey, Randall E.; Jackson, Edward M.; Goodrich, Kenneth H.; Ragsdale, W. A.; Neuhaus, Jason R.; Barnes, Jim

doi:10.2514/1.44688

Cited by 15 publications

(10 citation statements)

References 4 publications

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“…Statistical tests must be used to analyze datasets containing large variances. As such, they are commonly used in the evaluation of the performance of piloted [27][28][29][30][31] or teleoperated [32][33][34] systems. Since the guidance and control algorithm tested in this paper generated substantial variances in its maneuver performance, the use of statistical analysis methods was required.…”

Section: Discussionmentioning

confidence: 99%

“…The experimental results are analyzed by using a two-way analysis of variance (ANOVA) [25] and post hoc Tukey multiple comparison tests [26]. These methods are commonly used in the evaluation of piloted [27][28][29][30][31] or teleoperated [32][33][34] systems to identify significant differences within data sets with substantial variance. Statistical analysis methods are not common in the evaluation of the performance of autonomous robotic system, since these are considered to be deterministic in nature and produce small variances in their performance.…”

Section: Introductionmentioning

confidence: 99%

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Experimental Characterization of Inverse Dynamics Guidance in Docking with a Rotating Target

Wilde

Ciarcià

Grompone

et al. 2016

Journal of Guidance, Control, and Dynamics

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The performance of an inverse dynamics guidance and control strategy is experimentally evaluated for the planar maneuver of a "chaser" spacecraft docking with a rotating "target." The experiments were conducted on an airbearing proximity maneuver testbed. The chaser spacecraft simulator consists of a three-degree-of-freedom autonomous vehicle floating via air pads on a granite table and actuated by thrusters. The target consists of a docking interface mounted on a rotational stage with the rotation axis perpendicular to the plane of motion. Given a preassigned trajectory, the guidance and control strategy computes the required maneuver control forces and torque via an inverse dynamics operation. The recorded data of 150 experimental test runs were analyzed using two-way analysis of variance and post hoc Tukey tests. The metrics were maneuver success, vehicle mass change, maneuver duration, thruster duty cycle, and maneuver work. The results showed that the guidance and control algorithm provided robust performance over a range of target rotation rates from 1 to 4 deg ∕s. = maximum available torque, N · m T z = chaser torque about z axis of laboratory coordinate system, N · m t = maneuver time, s t D = total duration of docking maneuver, s t DA = duration of final docking approach, s t FF = duration of free-flight phase, s t f = final maneuver time, s W = maneuver work, J x C ; y C T = planar position vector of chaser center of mass in laboratory coordinate system, m x T ; y T T = planar position vector of the target center of rotation in laboratory coordinate system, m x; y; z = Cartesian coordinate system fixed in laboratory x 0 ; y 0 ; z 0 = Cartesian coordinate system fixed to chaser spacecraft simulator x 0 0 ; y 0 0 ; z 0 0 = Cartesian coordinate system fixed to target object γ = auxiliary maneuver targeting angle, rad Δm = chaser mass change, kg Δr = positioning tolerance for completion of docking maneuver, m Δt DA = extended maneuver time beyond nominal maneuver time, s Δt G = time step of the guidance algorithm, s ζ = auxiliary maneuver targeting angle, rad θ C = chaser orientation angle in relation to laboratory coordinate system, rad θ T = target orientation angle in relation to laboratory coordinate system, rad χ ij = thruster activity for thruster j at time step ∈ 0; 1, s ω T = target object angular rate, rad∕s

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Section: Discussionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Experimental Characterization of Inverse Dynamics Guidance in Docking with a Rotating Target

Wilde

Ciarcià

Grompone

et al. 2016

Journal of Guidance, Control, and Dynamics

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“…One predominate handling qualities factor in proximity operations and docking is the rotational coupling of the vehicle due to translational inputs [17,18]. This effect is illustrated in Figure 2 using a simplistic example where the relationship between reaction control system (RCS) jet longitudinal location varies with respect to the vehicle center-of-mass (CM).…”

Section: Handling Qualities Influencesmentioning

confidence: 99%

“…The initial condition on a +V-bar docking approach to the International Space Station (ISS) was offset by 2.5 ft from the docking axis [17,18]. This offset required the evaluation pilot to laterally and vertically reacquire the docking axis.…”

Section: Piloting Taskmentioning

confidence: 99%

Handling qualities implications for crewed spacecraft operations

Bailey

Jackson

Arthur

2012

2012 IEEE Aerospace Conference

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Abstract-Handling qualities embody those qualities or characteristics of an aircraft that govern the ease and precision with which a pilot is able to perform the tasks required in support of an aircraft role. These same qualities are as critical, if not more so, in the operation of spacecraft.A research, development, test, and evaluation process was put into effect to identify, understand, and interpret the engineering and human factors principles which govern the pilot-vehicle dynamic system as they pertain to space exploration missions and tasks. Toward this objective, piloted simulations were conducted at the NASA Langley Research Center and Ames Research Center for earth-orbit proximity operations and docking and lunar landing.These works provide broad guidelines for the design of spacecraft to exhibit excellent handling characteristics. In particular, this work demonstrates how handling qualities include much more than just stability and control characteristics of a spacecraft or aircraft. Handling qualities are affected by all aspects of the "pilot-vehicle dynamic system," including the motion, visual and aural cues of the vehicle response as the pilot performs the required operation or task. A holistic approach to spacecraft design, including the use of manual control, automatic control, and pilot intervention/supervision is described. The handling qualities implications of design decisions are demonstrated using these pilot-in-the-loop evaluations of docking operations and lunar landings.

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“…3 In 2007, NASA began another effort to study spacecraft handling qualities in preparation for a new generation of piloted spacecraft intended to replace the Space Shuttle and travel beyond Earth orbit. [4][5][6][7][8][9][10][11] Although vehicle control during entry is usually done with an automated system, Apollo and current-day requirements (e.g. NASA's Human Rating Requirements, NPR 8705.2b) stipulate that pilots have the ability to manually control the vehicle's flight path and attitude in off-nominal situations.…”

Section: Introductionmentioning

confidence: 99%

Orion Capsule Handling Qualities for Atmospheric Entry

Tigges

Bihari²,

Stephens

et al. 2011

AIAA Guidance, Navigation, and Control Conference

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Two piloted simulations were conducted at NASA's Johnson Space Center using the Cooper-Harper scale to study the handling qualities of the Orion Command Module capsule during atmospheric entry flight. The simulations were conducted using high fidelity 6-DOF simulators for Lunar Return Skip Entry and International Space Station Return Direct Entry flight using bank angle steering commands generated by either the Primary (PredGuid) or Backup (PLM) guidance algorithms. For both evaluations, manual control of bank angle began after descending through Entry Interface into the atmosphere until drogue chutes deployment. Pilots were able to use defined bank management and reversal criteria to accurately track the bank angle commands, and stay within flight performance metrics of landing accuracy, g-loads, and propellant consumption, suggesting that the pilotability of Orion under manual control is both achievable and provides adequate trajectory performance with acceptable levels of pilot effort. Another significant result of these analyses is the applicability of flying a complex entry task under high speed entry flight conditions relevant to the next generation Multi Purpose Crew Vehicle return from Mars and Near Earth Objects.1 Aerospace Engineer, Advanced Mission Design Branch, Mail Stop EG5; michael.a.tigges@nasa.gov

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Investigation of Reaction Control System Design on Spacecraft Handling Qualities for Docking

Cited by 15 publications

References 4 publications

Experimental Characterization of Inverse Dynamics Guidance in Docking with a Rotating Target

Experimental Characterization of Inverse Dynamics Guidance in Docking with a Rotating Target

Handling qualities implications for crewed spacecraft operations

Orion Capsule Handling Qualities for Atmospheric Entry

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