Aerospace Systems最新文献_第6页

Non-unique regimes of oscillatory transonic flow in bent channels 弯曲通道中振荡跨音速流动的非独特机制

Aerospace Systems Pub Date : 2023-08-07 DOI: 10.1007/s42401-023-00243-4

Alexander Kuzmin

引用次数: 0

Model predictive control switching strategy for safe small satellite cluster formation flight 小卫星编队安全飞行模型预测控制切换策略

Aerospace Systems Pub Date : 2023-07-26 DOI: 10.1007/s42401-023-00237-2

Tyson Smith, John Akagi, Greg Droge

{"title":"Model predictive control switching strategy for safe small satellite cluster formation flight","authors":"Tyson Smith, John Akagi, Greg Droge","doi":"10.1007/s42401-023-00237-2","DOIUrl":"10.1007/s42401-023-00237-2","url":null,"abstract":"<div><p>This paper presents the development and analysis of a spacecraft formation flying architecture. The desired state of each spacecraft is maintained using a model predictive control-based control framework that is based on the Hill–Clohessy–Wiltshire equations and a polytope boundary constraint as a switching surface. This framework can be used to maintain the desired cluster formation while also guaranteeing internal cluster flight. The polytope boundaries are designed, such that no two agents have overlapping regions, allowing the vehicles to execute avoidance strategies without continually maintaining the trajectories of other agents. The model predictive control framework combined with the convex polytope boundary enables a scalable method that can support clusters of satellites to coordinate to safely achieve mission objectives while minimizing fuel usage. As part of the implementation of this control scheme, the authors created two spacecraft formation flying control approaches. The first approach uses fewer, large maneuvers to control a spacecraft to the center of a keep-in-volume. The second approach allows the spacecraft to perform many small maneuvers to stay just inside the boundary of the keep-in-volume. This paper compares the fuel cost savings of these two approaches. The results presented in this paper demonstrate that the first approach produces the lower total fuel usage, but if a lower amount of fuel per maneuver is required, then the second approach should be used. This work also compares the computation requirements and fuel usage for <span>(hbox {L}_1)</span>, <span>(hbox {L}_2)</span>, and <span>(hbox {L}_infty )</span> norms formulations of the framework, the <span>(hbox {L}_1)</span> and <span>(hbox {L}_2)</span> norms require the least amount of fuel usage, while the <span>(hbox {L}_2)</span> requires the least amount of computation time.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-07-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"88835252","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 modeling of hybrid rocket engine 混合动力火箭发动机的数值模拟

Aerospace Systems Pub Date : 2023-07-25 DOI: 10.1007/s42401-023-00241-6

Sachin Srivastava, Amit Kumar Thakur, Lovi Raj Gupta, Anita Gehlot

{"title":"Numerical modeling of hybrid rocket engine","authors":"Sachin Srivastava, Amit Kumar Thakur, Lovi Raj Gupta, Anita Gehlot","doi":"10.1007/s42401-023-00241-6","DOIUrl":"10.1007/s42401-023-00241-6","url":null,"abstract":"<div><p>Recent development in space mission demands safer and more cost-effective space missions. Hybrid rocket engine technological advancements have prolonged a critical stage in their development and it is the better option for such space missions, as it has a lot of advantages over the solid rocket motor and liquid rocket engine. It is simple in design, has high thrust density, low weight, and is safer than a liquid rocket engine. It has restarted capability, safe, low explosion risk, and high specific impulse than a solid rocket motor. This paper shows the numerical analysis of a hybrid rocket engine. The paper highlights the initial boundary conditions in the analysis of a 300-N hybrid rocket engine. The process started with a chemical kinematic examination of engine-compatible fuels and oxidizers. This investigation provided the fundamental parameters required for the design and subsequent dimensioning of a hybrid rocket engine. It also produced a three-dimensional design model, performed numerical analysis using ANSYS software, and validated the findings using existing literature. Using the <i>k</i>–<span>(varepsilon)</span> turbulence model and transient solver on 8 mm port diameter for analyzing. The computational fluid dynamics model offered the qualities of a real hybrid rocket engine and it will be helpful to researchers and the scientific community in the future.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-07-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"72371737","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

Adaptive control for excitation and parameter identification of a three-axis spacecraft simulator with full-state constraints 全状态约束下三轴航天器模拟器激励与参数辨识的自适应控制

Aerospace Systems Pub Date : 2023-07-20 DOI: 10.1007/s42401-023-00218-5

Zhongyuan Zhu, Dexin Zhang, Xiaowei Shao

{"title":"Adaptive control for excitation and parameter identification of a three-axis spacecraft simulator with full-state constraints","authors":"Zhongyuan Zhu, Dexin Zhang, Xiaowei Shao","doi":"10.1007/s42401-023-00218-5","DOIUrl":"10.1007/s42401-023-00218-5","url":null,"abstract":"<div><p>The three degrees of freedom spacecraft attitude simulator is of vital importance in verifying spacecraft control strategies and many other space techniques. It requires accurate knowledge of simulator inertia parameters which can be identified by a variety of estimation methods under appropriate excitation situation. However, constraints on the rotation range, angular velocity, and torque may lead to a bad parameter estimation performance and cause security problem in excitation process. A new adaptive reorientation controller is proposed in this paper to solve these problems. By deriving the expression of parameter estimation error and analyzing the ill-conditioned problem resulted from the attitude constraint, a preconditioned adaptive parameter estimation law is designed and then combined with a new proposed reorientation controller, such that the errors of parameter identification and reorientation excitation simultaneously converge to zero. And the constraints can also be met. Compared to conventional parameter identification schemes, the proposed controller can simultaneously achieve the closed-loop reorientation excitation for security requirement and the more efficient parameter identification outcome. The effectiveness of the adaptive controller is finally demonstrated by numerical simulations.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-07-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"81438540","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

Estimation of satellite attitude dynamics and external torques via mixed Kalman/H-infinity filter under inertia uncertainties 惯性不确定性下卫星姿态动力学和外力矩的混合卡尔曼/ h∞滤波估计

Aerospace Systems Pub Date : 2023-07-20 DOI: 10.1007/s42401-023-00235-4

Halima Boussadia, Mohammed Arezki Si Mohammed, Abdelkrim Meche, Nabil Boughanmi, Abdelkader Slimane, Abdellatif Bellar

{"title":"Estimation of satellite attitude dynamics and external torques via mixed Kalman/H-infinity filter under inertia uncertainties","authors":"Halima Boussadia, Mohammed Arezki Si Mohammed, Abdelkrim Meche, Nabil Boughanmi, Abdelkader Slimane, Abdellatif Bellar","doi":"10.1007/s42401-023-00235-4","DOIUrl":"10.1007/s42401-023-00235-4","url":null,"abstract":"<div><p>In this work, a mixed Kalman/H-infinity filter is designed for the attitude estimation of a low Earth orbit microsatellite and the external disturbance torques acting on it. The state vector will be formed by satellite's attitude along with angular rates and the external disturbances. An improved external disturbance modeled as a random walk acting (slowly varying) around three axis attitude was proposed. This external disturbance is mainly generated by the aerodynamic torque, the residual magnetic moment and the gravity gradient torque. The satellite has only magnetometer on board as the attitude sensor. The proposed algorithm is tested using simulated data for a microsatellite, and the results of this study are tested in different scenarios. The first two scenarios are the cases with and without uncertainty in the satellite’s inertia. The last scenario is extensive Monte Carlo simulations with uniformly distributed initial conditions of the Euler angle and angular rate. The major purpose of this work is to demonstrate that we can estimate external disturbances and attitude dynamic parameters of a satellite using a simple filter that combines the best features of Kalman and <span>({mathrm{H}}_{infty })</span> filters. The simulation results show that the attitude RMS error is less than <span>(pm 1)</span> deg (acceptable accuracy). Also, Monte Carlo simulation gives good results of the proposed filter. This latter estimates the attitude with accuracy less than 0.8 deg, the rate order is 1 milli-deg/s and the external disturbances around 1.5 μNm.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-07-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42401-023-00235-4.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"86536125","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Methods for determining the weight of a supersonic passenger administrative aircraft fuselage structure based on regression analysis 基于回归分析确定超音速行政客机机身结构重量的方法

Aerospace Systems Pub Date : 2023-07-17 DOI: 10.1007/s42401-023-00240-7

Gulnar Resulkulyeva, Sergey Serebryansky

引用次数: 0

Intention recognition of UAV swarm with data-driven methods 基于数据驱动的无人机群意图识别

Aerospace Systems Pub Date : 2023-07-05 DOI: 10.1007/s42401-023-00238-1

Zhichao Wang, Jiayun Chen, Jiaju Wang, Qiang Shen

引用次数: 0

Airfoil smoothing using unconditional optimization 利用无条件优化平滑机翼

Aerospace Systems Pub Date : 2023-07-05 DOI: 10.1007/s42401-023-00232-7

Alexander Yerokhin, Yuri Deniskin