Journal of Spacecraft and Rockets最新文献_第8页

Relative Motion in the Velocity Frame for Atmospheric Entry Trajectories 大气进入轨迹速度框架中的相对运动

IF 1.6 4区工程技术

Journal of Spacecraft and Rockets Pub Date : 2023-07-04 DOI: 10.2514/1.a35753

Samuel W. Albert, H. Schaub

{"title":"Relative Motion in the Velocity Frame for Atmospheric Entry Trajectories","authors":"Samuel W. Albert, H. Schaub","doi":"10.2514/1.a35753","DOIUrl":"https://doi.org/10.2514/1.a35753","url":null,"abstract":"Relative motion models provide a method of directly describing the position and velocity of a deputy spacecraft with respect to a chief spacecraft. Common approaches such as the Clohessy–Wiltshire equations describe relative motion in a rotating orbit frame aligned with the radial position vector of the chief, and intuitive solutions exist in this frame for circular or near-circular chief orbits. However, as eccentricity of the chief orbit increases, the along-track and velocity directions become less aligned and the orbit frame becomes less intuitive. This work revisits several key relative motion descriptions in the orbit frame and reformulates them to describe motion in the velocity frame, which provides an intuitive description of motion with respect to the flight path. Highly elliptic and hyperbolic chief motions are considered, which are common for atmospheric entry trajectory scenarios. These models are combined with the extended Allen–Eggers equations into a procedure for analytically estimating the offset in landing location for formation flying on an atmospheric entry trajectory. Three representative examples are given and compared with simulation, and range offset predictions are within 6% of total chief range in all cases.","PeriodicalId":50048,"journal":{"name":"Journal of Spacecraft and Rockets","volume":" ","pages":""},"PeriodicalIF":1.6,"publicationDate":"2023-07-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"47470982","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Thermal Model Correlation of SNIPE Satellite Using Genetic-Algorithm-Based Multi-Objective Optimization Method 基于遗传算法的SNIPE卫星热模型关联多目标优化方法

IF 1.6 4区工程技术

Journal of Spacecraft and Rockets Pub Date : 2023-07-01 DOI: 10.2514/1.a35517

Ji-Seok Kim, Seonho Lee, H. Kim, Hae-Dong Kim

引用次数: 0

Eddy-Current Actuator for Attraction and Repulsion of Non-Ferromagnetic, Conductive Spacecraft 用于非铁磁导电航天器吸引和排斥的涡流激励器

IF 1.6 4区工程技术

Journal of Spacecraft and Rockets Pub Date : 2023-07-01 DOI: 10.2514/1.a35466

Katherine T. Wilson, Guadalupe Bernal, M. Peck

{"title":"Eddy-Current Actuator for Attraction and Repulsion of Non-Ferromagnetic, Conductive Spacecraft","authors":"Katherine T. Wilson, Guadalupe Bernal, M. Peck","doi":"10.2514/1.a35466","DOIUrl":"https://doi.org/10.2514/1.a35466","url":null,"abstract":"This paper introduces a propellant-free approach to mobility of an inspection or servicing vehicle. The approach is suitable for motion near the surface of non-ferromagnetic, conductive objects in orbit. This work considers the specifics of eddy-current interactions between a translating permanent magnet and the aluminum surfaces of spacecraft. Such an actuator moves within the body of an inspection vehicle, requiring that its motion remains limited if the vehicle is to continuously interact with the client spacecraft. Experimental verification on a low-friction air track verifies a model for attraction–repulsion dynamics at millimeter-scale initial separations in one dimension. Results show good agreement between the simulated and tested conditions and motivate extension of the model to more general cases. To bound the design space and relative distances at which this actuator is effective, this work identifies the required size, mass, and trajectories for repulsion that restores the actuator to its initial configuration. Results support the utility of eddy-current actuation for microsatellites at separations of millimeters to centimeters from their conductive clients. For such clients the actuator may enable relative mobility and achieve other objectives key to proximity operations.","PeriodicalId":50048,"journal":{"name":"Journal of Spacecraft and Rockets","volume":" ","pages":""},"PeriodicalIF":1.6,"publicationDate":"2023-07-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"46420596","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Initial Orbit Determination from Only Heading Measurements 仅根据航向测量确定初始轨道

4区工程技术

Journal of Spacecraft and Rockets Pub Date : 2023-07-01 DOI: 10.2514/1.a35593

John A. Christian

引用次数: 0

Prescribed-Time Spacecraft Attitude Control Using Time-Varying State Feedback 时变状态反馈的定时航天器姿态控制

4区工程技术

Journal of Spacecraft and Rockets Pub Date : 2023-07-01 DOI: 10.2514/1.a35588

Vikram Kumar Saini, Dipak Kumar Giri, Renuganth Varatharajoo

引用次数: 0

Satellite Collision and Fragmentation Probabilities Using Radar-Based Size and Mass Estimates 基于雷达尺寸和质量估计的卫星碰撞和碎片概率

IF 1.6 4区工程技术

Journal of Spacecraft and Rockets Pub Date : 2023-07-01 DOI: 10.2514/1.a35697

D. Hall, Luis G. Baars

{"title":"Satellite Collision and Fragmentation Probabilities Using Radar-Based Size and Mass Estimates","authors":"D. Hall, Luis G. Baars","doi":"10.2514/1.a35697","DOIUrl":"https://doi.org/10.2514/1.a35697","url":null,"abstract":"Most conjunctions between Earth-orbiting satellites involve unknown objects, typically debris created by explosions or collisions. This study formulates methods to estimate probabilities of collision and fragmentation for such conjunctions, which depend on the estimated sizes and masses of the unknown objects. Analysis of radar cross-section (RCS) measurements provides estimated sizes, found to be accurate at the 90% confidence level to within a factor of 0.59 for potential underestimations and to within a factor of 3.1 for potential overestimations. For satellites that experience measurable atmospheric drag orbital perturbations, combining RCS data with orbit determination ballistic coefficients provides mass estimates accurate to within factors of 0.47 to 10.9 at the 90% confidence level. For satellites with perigee altitudes above 450 km, combining RCS data with solar radiation pressure coefficients provides mass estimates accurate to within factors of 0.44 to 5.6 at 90% confidence. The collision and fragmentation risk assessment formulation accounts for these size and mass estimation uncertainties. Specifically, conjunction collision probabilities formulated as statistically expected values account for the RCS-based size estimation uncertainties. Fragmentation probabilities, which measure the likelihood of producing more than a threshold number of collision fragments, account for both size and mass estimation uncertainties.","PeriodicalId":50048,"journal":{"name":"Journal of Spacecraft and Rockets","volume":" ","pages":""},"PeriodicalIF":1.6,"publicationDate":"2023-07-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"42866541","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Co-Delivery of a Martian Probe Network 火星探测器网络的共同交付

IF 1.6 4区工程技术

Journal of Spacecraft and Rockets Pub Date : 2023-06-29 DOI: 10.2514/1.a35560

Samuel W. Albert, H. Schaub

引用次数: 0

Passively Safe Spacecraft Motion Using Reachable Sets and Orbital Element Differences 基于可达集和轨道元差的被动安全航天器运动

IF 1.6 4区工程技术

Journal of Spacecraft and Rockets Pub Date : 2023-06-26 DOI: 10.2514/1.a35419

Daniel Aguilar-Marsillach, M. Holzinger

{"title":"Passively Safe Spacecraft Motion Using Reachable Sets and Orbital Element Differences","authors":"Daniel Aguilar-Marsillach, M. Holzinger","doi":"10.2514/1.a35419","DOIUrl":"https://doi.org/10.2514/1.a35419","url":null,"abstract":"The problem of passive safety between spacecraft is studied in this paper by means of backward reachable sets and orbital element differences. These reachable sets characterize the initial states that enter a swept region around a designated spacecraft within some time horizon, leading to collision or conjunction events. We provide an in-depth passive safety analysis using such representations and discuss how the motion of spacecraft can be constrained to satisfy such safety constraints. The work herein is particularly relevant for future formation-flying missions but can be extended to certain constellations, for example, Walker constellations. We demonstrate how to compute these sets for general dynamics models, which typically require numerical methods, but provide analytical and closed-form solutions for the Keplerian case as well as when first-order secular [Formula: see text] perturbations are considered with a mean orbital element difference description. Additionally, we show how the passive safety constraint based on such sets can be further simplified (or reduced) by considering projections or slices of the derived reachable sets. Finally, we propose an algorithm that finds passively safe configurations when considering multiple spacecraft. Simulations verify the passive safety constraints derived in this paper and their utility for a number of design cases in formation flying and a [Formula: see text]-perturbed low-Earth-orbit Walker constellation. In the latter case, long-term passive safety is shown even when subjected to unmodeled perturbations.","PeriodicalId":50048,"journal":{"name":"Journal of Spacecraft and Rockets","volume":" ","pages":""},"PeriodicalIF":1.6,"publicationDate":"2023-06-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"49189685","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Sensor Data Recovery of Faulty LOX/LH2 Rocket Engine Based on Multistage Graph Convolutional Network 基于多级图卷积网络的LOX/LH2火箭发动机故障传感器数据恢复

IF 1.6 4区工程技术

Journal of Spacecraft and Rockets Pub Date : 2023-06-26 DOI: 10.2514/1.a35620

Qiao Li, Xingchen Li, Wanxuan Zhang, Wen Yao

{"title":"Sensor Data Recovery of Faulty LOX/LH2 Rocket Engine Based on Multistage Graph Convolutional Network","authors":"Qiao Li, Xingchen Li, Wanxuan Zhang, Wen Yao","doi":"10.2514/1.a35620","DOIUrl":"https://doi.org/10.2514/1.a35620","url":null,"abstract":"Engine, the indispensable core of a rocket, has a significant impact on space exploration, especially the high-thrust liquid-propellant rocket engine. Most new-generation manned rockets for space stations or lunar exploration prefer the [Formula: see text] engine for its high performance and environmental friendliness. However, the [Formula: see text] engine is susceptible to failure under extreme conditions, which could cause catastrophic consequences without timely warning. Real-time state detection and fault location can prevent some catastrophic outcomes, but they require reliable sensor data. Nevertheless, some sensor data could be lost due to signal interruptions or equipment shutdown caused by system faults. Therefore, recovering the lost data based on the remaining measurements is a critical challenge that involves dealing with the distribution gap between normal and faulty data. To tackle the data drift and achieve real-time and high-precision sensor data recovery of the faulty engine, a multistage model based on graph convolutional networks is proposed in this paper. Trained by a multiloss function, the model primarily recognizes the status of the engine and passes the status to the next stage. Then the second stage recovers the lost data by two graph convolutional networks specific to the normal or faulty state. Evaluated on the practical experimental data from Xi’an Aerospace Propulsion Institute, our method successfully identifies the state of the system with accuracy above 99.99% and recovers the incomplete sensor data with a mean absolute error under 0.0065. Moreover, some ablation studies demonstrate that the blocks of two-stage and graph convolution could achieve a 26% improvement over the vanilla neural network.","PeriodicalId":50048,"journal":{"name":"Journal of Spacecraft and Rockets","volume":" ","pages":""},"PeriodicalIF":1.6,"publicationDate":"2023-06-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45350988","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Impact Angle Guidance Using Computationally Enhanced State-Dependent Differential Riccati-Equation Scheme 使用计算增强的状态相关微分Riccati方程格式的冲击角制导

IF 1.6 4区工程技术

Journal of Spacecraft and Rockets Pub Date : 2023-06-24 DOI: 10.2514/1.a35624

Li-Gang Lin, Ruei-Syuan Wu, Chih-Ting Yeh, Ming Xin

{"title":"Impact Angle Guidance Using Computationally Enhanced State-Dependent Differential Riccati-Equation Scheme","authors":"Li-Gang Lin, Ruei-Syuan Wu, Chih-Ting Yeh, Ming Xin","doi":"10.2514/1.a35624","DOIUrl":"https://doi.org/10.2514/1.a35624","url":null,"abstract":"This study considers the latest three-dimensional impact angle guidance based on the state-dependent differential Riccati-equation (SDDRE) scheme, and it presents novel theories that efficiently guarantee the SDDRE’s applicability and largely reduce the computational burden. The unified applicability analysis completely categorizes the state space in terms of a simple equivalent condition, where all the inapplicable cases (leading to implementation breakdowns) are newly discovered and efficiently resolved. The condition almost removes the tedious online checking routine, which accounts for the dominant effort as endorsed by complexity analysis and practical validations. Moving forward to a general scope, we analyze the computational complexity of such an SDDRE controller: first subject to the MATLAB® framework and then the state-of-the-art enhancements, where the latter come from the best performance among extensive trials. Finally, numerical and hardware experiments (notably, microcontroller and field-programmable gate array) strengthen the confidence in the analytical findings, and they enrich the value in robustness and generality that benefit more guidance or control systems.","PeriodicalId":50048,"journal":{"name":"Journal of Spacecraft and Rockets","volume":" ","pages":""},"PeriodicalIF":1.6,"publicationDate":"2023-06-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"44463908","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0