Journal of Spacecraft and Rockets最新文献_第4页

Thermospheric Density Estimation Method Using a First-Order Gauss–Markov Process 使用一阶高斯-马尔科夫过程的热层密度估计方法

Journal of Spacecraft and Rockets Pub Date : 2024-04-03 DOI: 10.2514/1.a35884

Jinyuan Li, Hong-Xin Shen, Pu Huang, Yin Chu, H. Baoyin

{"title":"Thermospheric Density Estimation Method Using a First-Order Gauss–Markov Process","authors":"Jinyuan Li, Hong-Xin Shen, Pu Huang, Yin Chu, H. Baoyin","doi":"10.2514/1.a35884","DOIUrl":"https://doi.org/10.2514/1.a35884","url":null,"abstract":"Low-Earth-orbit (LEO) spacecraft are significantly influenced by atmospheric drag. Accurately estimating thermospheric density is pivotal for the precise calculation of drag acceleration. However, thermospheric density along a specific orbit, computed using existing thermospheric models, has certain inaccuracies. In this work, a first-order Gauss–Markov process is used to model the deviation of atmospheric drag acceleration. With the Markov parameter of the initial state iteratively computed through sequential estimation and the smoothing method, the thermospheric density is derived from high-precision GPS measurements. In simulation scenarios, the root-mean-square error and relative error of the estimated thermospheric density reduce by about 45 and 50% relative to the prior density, respectively. Using the estimated density for orbit propagation, satellite trajectories’ one-day position and velocity error are, respectively, within 100 m and 0.1 m/s, and an average improvement in orbit precision is over 80%. The proposed method has been applied to the real Tsinghua Science Satellite (Q-SAT) GPS measurements for effectiveness verification. It shows strong adaptability under extreme space weather and during the occurrence of geomagnetic storms. Due to the estimated Markov parameter of the initial state obeying the Langevin dynamics properties, the proposed method also offers short-term thermospheric density forecasting potential.","PeriodicalId":508266,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"194 3","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-04-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140746585","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Numerical Simulation and Influence of Non-Gaussian Vibrations on Flexible Robotic Systems 非高斯振动的数值模拟及其对柔性机器人系统的影响

Journal of Spacecraft and Rockets Pub Date : 2024-03-31 DOI: 10.2514/1.a35648

John Bell, Laura Redmond, Kalind C. Carpenter, Jean-Pierre de la Croix

{"title":"Numerical Simulation and Influence of Non-Gaussian Vibrations on Flexible Robotic Systems","authors":"John Bell, Laura Redmond, Kalind C. Carpenter, Jean-Pierre de la Croix","doi":"10.2514/1.a35648","DOIUrl":"https://doi.org/10.2514/1.a35648","url":null,"abstract":"Random vibration excitation is a standard method for obtaining the dynamic properties of aerospace structures and simulating loading conditions. Shaker-based random excitation and traditional finite element analysis techniques use random vibrations, assuming a Gaussian distribution of excitation impulse magnitudes. While Gaussian signals may sufficiently describe some vibrational environments, many real-world excitations have non-Gaussian distributions. These signals may contain vibrational impulses larger than those observed in a Gaussian signal and could cause damage if not considered. This paper examines the influence of non-Gaussian signals on flexible vs. rigid robotic architectures using NASA JPL’s Pop-Up Flat Folding Explorer Robot (PUFFER) and Cooperative Autonomous Distributed Robotic Explorer (CADRE). The results indicate that flexible systems can be significantly impacted by a non-Gaussian excitation profile and that neither a typical enveloping of a Gaussian excitation nor a superposition of the responses to a worst-case impulse load with the response to a Gaussian signal was sufficient to bound the response due to non-Gaussian excitation. The driving mechanism for increased sensitivity of flexible robotic systems appears to be inertial, and designers may consider shifting the relative flexibility of the system or its constraints to force particular deformation modes or designing hinge mechanisms with increased damping to minimize the influence of non-Gaussian signals on the response of a flexible robotic structure.","PeriodicalId":508266,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"76 6","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-03-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140360080","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

On Constrained Lyapunov Stabilization of Spacecraft Orbits Using Gauss Variational Equations 论利用高斯变分方程实现航天器轨道的受限李亚普诺夫稳定

Journal of Spacecraft and Rockets Pub Date : 2024-03-30 DOI: 10.2514/1.a35932

E. Garone, Ilya V. Kolmanovsky

引用次数: 0

General Dynamics for Single- and Dual-Axis Rotating Rigid Spacecraft Components 通用动力公司的单轴和双轴旋转刚性航天器部件

Journal of Spacecraft and Rockets Pub Date : 2024-03-30 DOI: 10.2514/1.a35865

João Vaz Carneiro, Cody Allard, Hanspeter Schaub

{"title":"General Dynamics for Single- and Dual-Axis Rotating Rigid Spacecraft Components","authors":"João Vaz Carneiro, Cody Allard, Hanspeter Schaub","doi":"10.2514/1.a35865","DOIUrl":"https://doi.org/10.2514/1.a35865","url":null,"abstract":"Deriving and propagating a spacecraft’s equations of motion is fundamental to describing its behavior accurately. These equations of motion depend on the spacecraft’s configuration, which includes any physical subsystem such as attitude control devices, solar panels, gimbals, etc. Prior work introduced the backsubstitution method to yield a modular and scalable formulation to develop complex spacecraft dynamics specific to rotating components attached to a rigid hub as effectors. This paper relaxes assumptions made in deriving effector components in prior work, such as mass properties and frame definitions. This produces a general architecture that uses common equations of motion for physically equal parts. The result is an analytical solution of a set of general rotating effector equations of motion that greatly expand the configuration space of spacecraft that can be simulated with the backsubstitution method. In contrast to prior work where the rotations are highly constrained, rigid-body components can rotate about one or two general axes, and the component mass distribution can be general, no longer requiring the component’s principal axis to align with the center of mass or hinge axis. A numerical software solution demonstrates and verifies how these effectors can mimic a range of dynamic spacecraft components.","PeriodicalId":508266,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"17 5","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-03-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140364424","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Convex Low-Thrust Trajectory Optimization with No-Thrust Constraints and Moving Target 带无推力约束和移动目标的凸低推力轨迹优化

Journal of Spacecraft and Rockets Pub Date : 2024-03-30 DOI: 10.2514/1.a35877

Christian Hofmann, Francesco Topputo

引用次数: 0

Neural Network-Based Formation Flying Using Aerodynamic Forces via Variable Shape Function 通过可变形状函数利用空气动力进行基于神经网络的编队飞行

Journal of Spacecraft and Rockets Pub Date : 2024-03-19 DOI: 10.2514/1.a35750

Shogo Kitamura, S. Matunaga

{"title":"Neural Network-Based Formation Flying Using Aerodynamic Forces via Variable Shape Function","authors":"Shogo Kitamura, S. Matunaga","doi":"10.2514/1.a35750","DOIUrl":"https://doi.org/10.2514/1.a35750","url":null,"abstract":"Conventional formation flying Earth-orbiting satellites control their orbits to perform their missions using thrusters, but the amount of propellant loaded into a satellite is limited. Therefore, the use of aerodynamic forces for orbit control has been attracting attention, particularly in low Earth orbit. The orbit control can be achieved by appropriately changing the state of satellite, such as attitude and shape, to meet the aerodynamic requirements. In modeling the relationship between satellite state and aerodynamic forces, conventional methods ignore the shielding caused by the nonconvexity of the satellite’s appearance. Ignoring the shielding creates a gap between the modeled and the real aerodynamic forces, resulting in poor control performance. To solve this problem, we propose an aerodynamic force modeling method that incorporates a neural network to estimate the shielding. We train the neural network using data from an aerodynamics simulator. The optimal state that not only generates the required aerodynamic forces but also improves controllability under various mechanical constraints is obtained by solving an optimization problem that incorporates the proposed aerodynamic model. We conduct numerical simulations for establishing and maintaining general circular orbit formations. The results show convergence and continuous stable control of the deputy satellite to the ideal orbit.","PeriodicalId":508266,"journal":{"name":"Journal of Spacecraft and Rockets","volume":" 15","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-03-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140389228","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Noise Generated in a Scramjet Combustor Scramjet 燃烧器产生的噪音

Journal of Spacecraft and Rockets Pub Date : 2024-03-08 DOI: 10.2514/1.a35779

Ramprakash Ananthapadmanaban, Timothy J. McIntyre, Vincent Wheatley, David J. Mee

{"title":"Noise Generated in a Scramjet Combustor","authors":"Ramprakash Ananthapadmanaban, Timothy J. McIntyre, Vincent Wheatley, David J. Mee","doi":"10.2514/1.a35779","DOIUrl":"https://doi.org/10.2514/1.a35779","url":null,"abstract":"This paper presents the noise levels generated inside a two-dimensional scramjet combustor at Mach 7.3 freestream using the focused laser differential interferometric (FLDI) technique. FLDI measurements were taken at the front, middle, and rear of the combustor’s center plane under unfueled, combustion-suppressed, and combustion-on conditions. Spectral analysis of the FLDI signal shows density fluctuations inside the scramjet combustor are almost two times higher than the freestream and confirms the capability of this technique for measuring the disturbances in a complex hypersonic flowfield. Though combustion-induced pressure rise is low, a trend in the increase in the normalized density fluctuations/noise levels due to supersonic combustion is observed across the measurement locations for the combustion-on condition. However, the overall increment in the noise level is modest between the three conditions and across the three probing locations. This infers that, for the current scramjet geometry, fueling rates, fuel–air mixing, and supersonic combustion are not the dominant noise sources in the scramjet combustor. Instead, the base hypersonic flowfield inside the scramjet combustor is the main contributor to the noise field. Noting that there is relatively large uncertainty in the measured noise levels and that the combustion-induced pressure rise is modest in the present study, further investigation is needed to check the applicability of these results to the scramjet engines with flow paths having more complex flowfields, fueling schemes, and fueling rates.","PeriodicalId":508266,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"49 13","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-03-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140077148","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Multi-User System for Earth Sensing Spacecraft Attitude Calibration and Analysis 地球传感航天器姿态校准和分析多用户系统

Journal of Spacecraft and Rockets Pub Date : 2024-02-29 DOI: 10.2514/1.a35655

M. Whorton, J. Crassidis

{"title":"Multi-User System for Earth Sensing Spacecraft Attitude Calibration and Analysis","authors":"M. Whorton, J. Crassidis","doi":"10.2514/1.a35655","DOIUrl":"https://doi.org/10.2514/1.a35655","url":null,"abstract":"The Teledyne Multiple User System for Earth Sensing (“MUSES”) was developed for commercial Earth imaging and instrument technology development on the International Space Station (ISS). MUSES simultaneously hosts up to four Earth ensing instruments and provides inertial pointing and tracking to orient instruments toward planned targets on the ground. Up to four instruments are robotically installed on MUSES and periodically interchanged as warranted. MUSES was delivered to the ISS in June 2017, with initial testing successfully completed and subsequently documented in an initial requirements verification report. Assessing the performance of the MUSES attitude estimation system is challenging due to the lack of an independent attitude estimate of the platform attitude. A novel approach is introduced herein where the ISS attitude estimate, derived from ISS Global Positioning System sensors, is employed as an independent measure of MUSES platform attitude. Spectral decomposition methods are used to account for the contributions of ISS deformations to the variance in disparities between the ISS and MUSES attitudes and thus enable a less conservative estimate of the variance in MUSES attitude error. Implementing the spectral decomposition results in a best estimate upper bound on MUSES attitude errors of 34.5 and 27.7 arcsec, respectively, in the along-track and cross-track axes. Both the simulated and real results obtained from the spacecraft are presented.","PeriodicalId":508266,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"9 2","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-02-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140411051","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Advances in Space Launch System Booster Separation Computational Fluid Dynamics 太空发射系统助推器分离计算流体动力学的进展

Journal of Spacecraft and Rockets Pub Date : 2024-02-23 DOI: 10.2514/1.a35807

Jamie G. Meeroff, Derek J. Dalle, Stuart E. Rogers, Aaron C. Burkhead, D. Schauerhamer, Joshua F. Diaz

{"title":"Advances in Space Launch System Booster Separation Computational Fluid Dynamics","authors":"Jamie G. Meeroff, Derek J. Dalle, Stuart E. Rogers, Aaron C. Burkhead, D. Schauerhamer, Joshua F. Diaz","doi":"10.2514/1.a35807","DOIUrl":"https://doi.org/10.2514/1.a35807","url":null,"abstract":"The Space Launch System (SLS) employs two Space Shuttle–derived solid rocket boosters, which separate from the SLS core while still experiencing appreciable aerodynamic loads. Creating an aerodynamic database for this phase of flight can be challenging due to the large number of independent variables needed to fully constrain the problem and the complex flow induced by exhaust plumes of the booster separation motors and core main engines impinging on other parts of the vehicle. This paper details recent efforts in generating aerodynamic data used to create databases for the SLS during the booster separation event using viscous computational fluid dynamics (CFD) simulations obtained using NASA’s FUN3D solver. Particular challenges faced when modeling a complex problem, such as booster separation, are presented. Reductions in interpolation error estimates were observed through the introduction of a physics-based covariance approach to building the CFD run matrix, eliminating infeasible booster location permutations that could potentially skew final response surfaces. Interpolation error control is shown using test cases outside of the main database. Code-to-code comparisons between the FUN3D and OVERFLOW solvers are also presented to further verify the results.","PeriodicalId":508266,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"34 7","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-02-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140435273","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Control Co-Design Optimization of Spacecraft Trajectory and System for Interplanetary Missions 星际飞行任务航天器轨迹和系统的控制协同设计优化

Journal of Spacecraft and Rockets Pub Date : 2024-02-21 DOI: 10.2514/1.a35680

Gage W. Harris, Ping He, O. Abdelkhalik

{"title":"Control Co-Design Optimization of Spacecraft Trajectory and System for Interplanetary Missions","authors":"Gage W. Harris, Ping He, O. Abdelkhalik","doi":"10.2514/1.a35680","DOIUrl":"https://doi.org/10.2514/1.a35680","url":null,"abstract":"This paper develops a control co-design (CCD) framework to simultaneously optimize the spacecraft’s trajectory and onboard system (rocket engine) and quantify its benefit. An open-loop optimal control problem (two-finite burn Mars missions) is used as the benchmark, and the engine design considers the combustion equilibrium and nozzle geometry. The objective function is the fuel burn. The design variables are the trajectory control parameters (such as burn times, burn directions, and time of flight), initial fuel mass, and engine design parameters (such as throat area, mixture ratio, and chamber pressure). The constraints include the final velocities and positions of spacecraft. Single-point optimizations are conducted for three departure dates in May, July, and September 2020. A multipoint optimization is also performed to balance the engine performance for these dates with 49 design variables and 20 constraints. It is found that the CCD optimizations exhibit 22–28% more fuel burn reduction than the trajectory-only optimization with fixed engine parameters and 16–20% more fuel burn reduction than the decoupled trajectory-engine optimization. The proposed CCD optimization framework can be extended to more spacecraft trajectory control parameters and onboard systems and has the potential to design more efficient spacecraft missions.","PeriodicalId":508266,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"7 4","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-02-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140442586","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0