The Advanced Video Guidance Sensor: Orbital Express and the Next Generation

Howard, Richard T.; Heaton, Andrew; Pinson, Robin M.; Carrington, Connie L.; Lee, James E.; Bryan, Thomas C.; Robertson, Bryan; Spencer, Susan; Johnson, J. D.

doi:10.1063/1.2845036

Cited by 12 publications

(3 citation statements)

References 3 publications

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“…For example, that the output data rate of advanced video guide sensor (AVGS) is 5 Hz implies there is a delay of 0.2 s, where AVGS is one of the primary sensors for Automated Rendezvous and Docking (cf. [18]). It usually requires 1-10 s to perform star identification algorithms which are used in star trackers to determine the attitude of a spacecraft (see [19] and the survey [20]).…”

Section: Introductionmentioning

confidence: 93%

Estimating the stability domain of spacecraft attitude with delayed feedback

Zhu¹,

Hu²,

Yin³

2012

IET Control Theory Appl.

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This study deals with the estimation of the stability domain of the spacecraft attitude control system with delayed feedback. For autonomous functional-differential equations, by using the invariance principle, a general estimation theorem is established to explicitly estimate the stability domain. Furthermore, based on the estimation theorem and an applicable Lyapunov functional, an estimation criterion of the stability domain for the spacecraft attitude control system with delayed proportional-derivative (PD) controller is obtained. It is worth noting that the estimation criterion can be described as a generalised eigenvalue problem and thus can be solved by linear matrix inequality (LMI) optimisation techniques. Finally, numerical examples show the effectiveness of the estimation criterion.

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Section: Introductionmentioning

confidence: 93%

Estimating the stability domain of spacecraft attitude with delayed feedback

Zhu¹,

Hu²,

Yin³

2012

IET Control Theory Appl.

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“…Multiple alternative means to acquire these data are available, and lidar was adopted by Altair GN&C only as a placeholder. [13][14][40][41] Once the vehicles are within 100-150 m, lidar will also provide estimates of the relative attitude of Altair and Orion (also called "pose"). The uses of Altair RPOD and docking sensors as a function of vehicle range is depicted in Fig.…”

Section: A Preliminary Altair Gnandc System Designmentioning

confidence: 99%

Preliminary Design of the Guidance, Navigation, and Control System of The Altair Lunar Lander

Lee

Ely

Sostaric

et al. 2010

AIAA Guidance, Navigation, and Control Conference

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Guidance, Navigation, and Control (GN&C) is the measurement and control of spacecraft position, velocity, and attitude in support of mission objectives. This paper provides an overview of a preliminary design of the GN&C system of the Lunar Lander Altair. Key functions performed by the GN&C system in various mission phases will first be described. A set of placeholder GN&C sensors that is needed to support these functions is next described. To meet Crew safety requirements, there must be high degrees of redundancy in the selected sensor configuration. Two sets of thrusters, one on the Ascent Module (AM) and the other on the Descent Module (DM), will be used by the GN&C system. The DM thrusters will be used, among other purposes, to perform course correction burns during the Trans-lunar Coast. The AM thrusters will be used, among other purposes, to perform precise angular and translational controls of the ascent module in order to dock the ascent module with Orion. Navigation is the process of measurement and control of the spacecraft's "state" (both the position and velocity vectors of the spacecraft). Tracking data from the Earth-Based Ground System (tracking antennas) as well as data from onboard optical sensors will be used to estimate the vehicle state. A driving navigation requirement is to land Altair on the Moon with a landing accuracy that is better than 1 km (radial 95%). Preliminary performance of the Altair GN&C design, relative to this and other navigation requirements, will be given. Guidance is the onboard process that uses the estimated state vector, crew inputs, and pre-computed reference trajectories to guide both the rotational and the translational motions of the spacecraft during powered flight phases. Design objectives of reference trajectories for various mission phases vary. For example, the reference trajectory for the descent "approach" phase (the last 3-4 minutes before touchdown) will sacrifice fuel utilization efficiency in order to provide landing site visibility for both the crew and the terrain hazard detection sensor system. One output of Guidance is the steering angle commands sent to the 2 degree-of-freedom (dof) gimbal actuation system of the descent engine. The engine gimbal actuation system is controlled by a Thrust Vector Control algorithm that is designed taking into account the large quantities of sloshing liquids in tanks mounted on Altair. In this early design phase of Altair, the GN&C system is described only briefly in this paper and the emphasis is on the GN&C architecture (that is still evolving). Multiple companion papers will provide details that are related to navigation, optical navigation, guidance, fuel sloshing, rendezvous and docking, machine-pilot interactions, and others. The similarities and differences of GN&C designs for Lunar and Mars landers are briefly compared.

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“…The experimental results represent the advanced performance of the present method, i.e., the measurement frequency of the PXS is 2 Hz, with centimeter-scale accuracy in the relative position and one-tenth-of-a-degree-scale accuracy in the relative attitude [9]. Similar to the PXS, the advanced video guidance sensor (AVGS) [10,11] designed by the Marshall Space Flight Center and the visual based system (VBS) [12,13,14] designed by the Technical University of Denmark both require artificial beacons, which are either passive markers (reflectors) or active markers (LEDs). Sansone et al and Pirat et al similarly determined the pose of CubSats by using a camera and LED marks [15,16].…”

Section: Introductionmentioning

confidence: 99%

Monocular Vision-Based Pose Determination in Close Proximity for Low Impact Docking

Liu

Zhu

et al. 2019

Sensors

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Pose determination in close proximity is critical for space missions in which monocular vision is one of the most promising solutions. Although numerous approaches such as using artificial beacons or specific shapes on spacecrafts have proved to be effective, the high individuation and the large time delay limit their use in low impact docking. This paper proposes a unified framework to determinate the relative pose between two docking mechanisms by treating their guide petals as measurement objects. Fusing the pose information of one docking mechanism to simplify image processing and creating an intermediate coordinate system to solve the perspective-n-point problem greatly improve the real-time performance and the robustness of the method. Experimental results show that the position measurement error is within 3.7 mm, while the rotation error around docking direction is less than 0.16°, corresponding to a measurement time reduction of 85%.

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The Advanced Video Guidance Sensor: Orbital Express and the Next Generation

Cited by 12 publications

References 3 publications

Estimating the stability domain of spacecraft attitude with delayed feedback

Estimating the stability domain of spacecraft attitude with delayed feedback

Preliminary Design of the Guidance, Navigation, and Control System of The Altair Lunar Lander

Monocular Vision-Based Pose Determination in Close Proximity for Low Impact Docking

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