3区工程技术

Aerospace Pub Date : 2025-04-25 DOI: 10.3390/aerospace12050372

Shih-Sin Wei, Jui-Cheng Hsu, Hsi-Yu Tso, Jong-Shinn Wu

{"title":"Investigation of Performance Stability of a Nytrox Hybrid Rocket Propulsion System","authors":"Shih-Sin Wei, Jui-Cheng Hsu, Hsi-Yu Tso, Jong-Shinn Wu","doi":"10.3390/aerospace12050372","DOIUrl":"https://doi.org/10.3390/aerospace12050372","url":null,"abstract":"Nitrous oxide is a highly suitable oxidizer for hybrid rockets due to its self-pressurizing properties, moderate cost, and high accessibility. However, its vapor pressure and density are highly dependent on ambient temperature, requiring careful consideration of temperature variations in real applications. To mitigate this issue, an oxidizer called Nytrox was produced by adding a small fraction of oxygen to bulk nitrous oxide. This modification enables the hybrid rocket propulsion system to maintain a nearly constant average thrust and total impulse across a wide range of ambient temperatures. A series of 7 s hot-fire tests of a small Nytrox/polypropylene hybrid rocket engine operating at ~60 barA of running tank pressure demonstrated a consistent average thrust of 45.3 ± 0.7 kgf and a total impulse of 307.6 ± 3.9 kgf·s within a N2O temperature range of 5.9–22.6 °C, compared to highly varying values of the N2O/polypropylene one within a N2O temperature range of 10.8–29.8 °C. Furthermore, the specific impulse of the Nytrox hybrid rocket engine increases mildly with decreasing temperature because of the increasing amount of added oxygen that benefits the combustion for generating the thrust.","PeriodicalId":48525,"journal":{"name":"Aerospace","volume":"12 5","pages":"372-372"},"PeriodicalIF":0.0,"publicationDate":"2025-04-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.mdpi.com/2226-4310/12/5/372/pdf?version=1745560081","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147909147","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

A Review of Recent Developments in Hybrid Rocket Propulsion and Its Applications 混合动力火箭推进技术及其应用进展综述

3区工程技术

Aerospace Pub Date : 2024-09-09 DOI: 10.3390/aerospace11090739

Shih-Sin Wei, Meng‐Che Li, Alfred Lai, Tzu-Hao Chou, Jong-Shinn Wu

{"title":"A Review of Recent Developments in Hybrid Rocket Propulsion and Its Applications","authors":"Shih-Sin Wei, Meng‐Che Li, Alfred Lai, Tzu-Hao Chou, Jong-Shinn Wu","doi":"10.3390/aerospace11090739","DOIUrl":"https://doi.org/10.3390/aerospace11090739","url":null,"abstract":"This paper extensively reviews hybrid rocket propulsion-related activities from combustion engine designs to launch tests. Starting with a brief review of rocket propulsion development history, a comparison among the three bi-propellant rocket propulsion approaches, and hybrid rocket engine design guidelines, a very thorough review related to hybrid rocket propulsion and its applications is presented in this paper. In addition to propellant choice, engine design also affects the hybrid rocket performance and, therefore, a variety of engine designs, considering, e.g., fuel geometry, swirl injection, ignition designs, and some innovative flow-channel designs are also explored. Furthermore, many fundamental studies on increasing hybrid rocket engine performances, such as regression rate enhancement, mixing enhancement, and combustion optimization, are also reviewed. Many problems that will be encountered for practical applications are also reviewed and discussed, including the O/F ratio shift, low-frequency instability, and scale-up methods. For hybrid rocket engine applications in the future, advanced capabilities and lightweight design of the hybrid rocket engine, such as throttling capability, thrust vectoring control concept, insulation materials, 3D-printing manufacturing technologies, and flight demonstrations, are also included. Finally, some active hybrid rocket research teams and their plans for flight activities are briefly introduced.","PeriodicalId":48525,"journal":{"name":"Aerospace","volume":"11 9","pages":"739-739"},"PeriodicalIF":0.0,"publicationDate":"2024-09-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.mdpi.com/2226-4310/11/9/739/pdf?version=1725951786","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147908118","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 29

Continuum Modeling and Boundary Control of a Satellite with a Large Space Truss Structure 带有大型空间桁架结构的卫星的连续建模和边界控制

IF 2.6 3区工程技术

Aerospace Pub Date : 2024-01-05 DOI: 10.3390/aerospace11010054

Shilei Cao, Man Yang, Jian Liu

{"title":"Continuum Modeling and Boundary Control of a Satellite with a Large Space Truss Structure","authors":"Shilei Cao, Man Yang, Jian Liu","doi":"10.3390/aerospace11010054","DOIUrl":"https://doi.org/10.3390/aerospace11010054","url":null,"abstract":"Due to its advantages of easy deployment and high stiffness-to-mass ratio, the utilization of truss structures for constructing large satellites presents an appealing solution for modern space missions, including Earth observation and astronomy. However, the dimensions of the traditional finite element model for a satellite with a large space truss structure become exceedingly large as the structure’s size increases. The control system design process based on the finite element model is complex and time-consuming. This paper employs the continuum modeling method to represent the truss structure as a continuous entity. The bending vibrations of the truss structure are encapsulated by a simplified partial differential equation (PDE), as opposed to the more intricate traditional finite element model. Simultaneously, the satellite’s attitude motion is characterized by an ordinary differential equation (ODE). Building upon this coupled PDE-ODE model, a boundary control law that only requires sensors/actuators at the boundary is formulated to effectively mitigate structural vibrations and regulate the satellite’s attitude. The exponential stability of this closed-loop system is scrutinized using Lyapunov’s direct method. The simulation results affirm that the continuum modeling method is indeed well-suited for satellites endowed with substantial truss structures, and the proposed boundary law proves to be highly effective in both attitude tracking and vibration suppression.","PeriodicalId":48525,"journal":{"name":"Aerospace","volume":"13 1","pages":""},"PeriodicalIF":2.6,"publicationDate":"2024-01-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139381011","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"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

Decision Science-Driven Assessment of Ti Alloys for Aircraft Landing Gear Beams 飞机起落架横梁用钛合金的决策科学评估

IF 2.6 3区工程技术

Aerospace Pub Date : 2024-01-04 DOI: 10.3390/aerospace11010051

R. Canumalla, T.V. Jayaraman

{"title":"Decision Science-Driven Assessment of Ti Alloys for Aircraft Landing Gear Beams","authors":"R. Canumalla, T.V. Jayaraman","doi":"10.3390/aerospace11010051","DOIUrl":"https://doi.org/10.3390/aerospace11010051","url":null,"abstract":"Titanium alloys, with their low density, exceptional mechanical properties, and outstanding corrosion resistance, play a vital role in various aerospace applications. Our decision science-driven assessment focused on metastable β, near-β, α + β, and near-α Ti alloys for landing gear applications, integrating multiple-attribute decision-making (MADM) methods, principal component analysis (PCA), and hierarchical clustering (HC) is based on current literature. The ranks of the alloys evaluated by diverse MADM methods were consistent. The methodology identifies five top-ranked Ti alloys assists and verifies the guidelines for alloy design. The top-ranked alloy, Ti1300-BM-nano-α (alloy chemistry: Ti-5Al-4V-4Mo-3Zr-4Cr, solution treatment: 800 °C for 1 h followed by air cooling—solution treated below β transus, and aging: 500 °C for 4 h followed by air cooling), stands out with a percentage elongation (%EL) ~3.3 times greater than the benchmark or goal (density, d = ~4.6 g/cm3; yield strength YS = ~1250 MPa; %El = ~5), while maintaining similar density and yield strength. The analyses underline that metastable β Ti alloys comprising globular primary α + trans β matrix coupled with α precipitates in trans β are the base optimal microstructure to fine-tune using thermomechanical processing for aircraft landing gear applications.","PeriodicalId":48525,"journal":{"name":"Aerospace","volume":"57 4","pages":""},"PeriodicalIF":2.6,"publicationDate":"2024-01-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139386082","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"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

A Study for a Radio Telescope in Indonesia: Parabolic Design, Simulation of a Horn Antenna, and Radio Frequency Survey in Frequency of 0.045–18 GHz 印度尼西亚射电望远镜研究：抛物面设计、喇叭天线模拟和 0.045-18 千兆赫频率的射电频率测量

IF 2.6 3区工程技术

Aerospace Pub Date : 2024-01-04 DOI: 10.3390/aerospace11010052

P. Sitompul, P. Razi, T. Manik, M. Batubara, M. Lathif, Farahhati Mumtahana, R. Suryana, Ibnu Nurul Huda, Taufiq Hidayat, Yana Taryana, F. Sobirin

{"title":"A Study for a Radio Telescope in Indonesia: Parabolic Design, Simulation of a Horn Antenna, and Radio Frequency Survey in Frequency of 0.045–18 GHz","authors":"P. Sitompul, P. Razi, T. Manik, M. Batubara, M. Lathif, Farahhati Mumtahana, R. Suryana, Ibnu Nurul Huda, Taufiq Hidayat, Yana Taryana, F. Sobirin","doi":"10.3390/aerospace11010052","DOIUrl":"https://doi.org/10.3390/aerospace11010052","url":null,"abstract":"After years of preparation, the Indonesia National Observatory, located in Mount Timau, Kupang Regency, is currently in the completion stage of research in astronomy and astrophysics and related subjects. An optic telescope with a 3.8 m diameter is expected to receive its first light in mid-2024. A feasibility study for Indonesia’s radio telescopes and networks is in progress. A single-dish parabolic radio antenna with a diameter of 20 m is proposed to work in a frequency range of 1–50 GHz. An array dipole antenna with an area of 100 m × 100 m will also be installed at a 70–350 MHz frequency. A feasibility study about system design is in progress, and a radio frequency interference (RFI) survey has been underway since 2014. In this paper, we described the design of radio telescopes such as parabolic reflectors, horn antenna, and the radio frequency interference (RFI) in the surrounding area of the National Observatory, covering the frequency band from 45 MHz to 18 GHz. The frequencies in 45–85 MHz and 120–360 MHz intervals are still relatively quiet and suitable for developing radio telescopes. The selected higher frequency of 1.4 GHz for a neutral hydrogen (HI) spectral line, 6.6 GHz for a methanol (CH3OH) spectral line, and 8.6 GHz for a helium (3 He+) spectral line is still relatively quiet and suitable for the development of radio telescopes.","PeriodicalId":48525,"journal":{"name":"Aerospace","volume":"16 6","pages":""},"PeriodicalIF":2.6,"publicationDate":"2024-01-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139385717","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"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

Topology Optimization of a Single-Point Diamond-Turning Fixture for a Deployable Primary Mirror Telescope 用于可部署主镜望远镜的单点金刚石车削夹具的拓扑优化

IF 2.6 3区工程技术

Aerospace Pub Date : 2024-01-04 DOI: 10.3390/aerospace11010050

Cyril Bourgenot, Valdis Krumins, David G. Bramall, Abdul M. Haque

{"title":"Topology Optimization of a Single-Point Diamond-Turning Fixture for a Deployable Primary Mirror Telescope","authors":"Cyril Bourgenot, Valdis Krumins, David G. Bramall, Abdul M. Haque","doi":"10.3390/aerospace11010050","DOIUrl":"https://doi.org/10.3390/aerospace11010050","url":null,"abstract":"CubeSats, known for their compact size and cost effectiveness, have gained significant popularity. However, their limited size imposes restrictions on the optical aperture and, consequently, the Ground Resolution Distance in Earth Observation missions. To overcome this limitation, the concept of deployable optical payloads with segmented primary mirrors which can unfold like petals has emerged, enabling larger synthetic apertures and enhanced spatial resolution. This study explores the potential benefits of leveraging Additive Manufacturing (AM) and Topology Optimization (TO) in the realm of ultra-precision machining, specifically single-point diamond machining. The goal is to reduce fixture weight while improving stiffness to minimize deformations caused by rotational and cutting forces which compromise optical performance. Through Finite Element Analysis, this research compares conventionally machined fixtures with those produced using AM and TO techniques. The results reveal that concept designs created via TO can achieve a remarkable 68% reduction in weight. This reduction makes the assembly, including the machining fixture and 12 U deployable segments, manageable by a single operator without the need for specialized lifting equipment. Moreover, these innovative designs lead to substantial reductions of up to 86% and 51% in deformation induced by rotational and cutting forces, respectively.","PeriodicalId":48525,"journal":{"name":"Aerospace","volume":"57 42","pages":""},"PeriodicalIF":2.6,"publicationDate":"2024-01-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139384660","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"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

Coupled Aerodynamics–Structure Analysis and Wind Tunnel Experiments on Passive Hinge Oscillation of Wing-Tip-Chained Airplanes 翼尖链式飞机被动铰链振荡的空气动力学-结构耦合分析和风洞试验

IF 2.6 3区工程技术

Aerospace Pub Date : 2024-01-04 DOI: 10.3390/aerospace11010053

Yoichi Suenaga, Kojiro Suzuki

{"title":"Coupled Aerodynamics–Structure Analysis and Wind Tunnel Experiments on Passive Hinge Oscillation of Wing-Tip-Chained Airplanes","authors":"Yoichi Suenaga, Kojiro Suzuki","doi":"10.3390/aerospace11010053","DOIUrl":"https://doi.org/10.3390/aerospace11010053","url":null,"abstract":"This study examines the wing hinge oscillations in an aircraft concept that employs multiple wings, or small aircraft, chained at the wing tips through freely rotatable hinges with minimal structural damping and no mechanical position-locking system. This creates a single pseudo long-span aircraft that resembles a flying chain oriented perpendicular to the flight direction. Numerical calculations were conducted using the vortex lattice method and modified equations for a multi-link rigid body pendulum. The calculations demonstrated good agreement with small-scale wind tunnel experiments, where the motion of the chained wings was tracked through color tracking, and the forces were measured using six-axis force sensors. The total CL/CD increased for the chained wings, even in the presence of hinge joint oscillations. Furthermore, numerical simulations assuming an unmanned airplane size corroborated the theoretical attainment of passive stability with high chained numbers (≥9 wings), without any structural damping and relying solely on aerodynamic forces. Guidelines for appropriate hinge axis angle δ and angle-of-attack regions for different chained wing numbers to maximize passive oscillation stability were obtained. The results showed that wing-tip-chained airplanes could successfully provide substantially large wing spans while retaining flexibility, light weight and CL/CD, without requiring active hinge rotation control.","PeriodicalId":48525,"journal":{"name":"Aerospace","volume":"48 21","pages":""},"PeriodicalIF":2.6,"publicationDate":"2024-01-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139385130","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"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

Robust Trajectory Prediction Using Random Forest Methodology Application to UAS-S4 Ehécatl 使用随机森林方法进行鲁棒轨迹预测在 UAS-S4 Ehécatl 中的应用

IF 2.6 3区工程技术

Aerospace Pub Date : 2024-01-02 DOI: 10.3390/aerospace11010049

Seyed Mohammad Hashemi, R. Botez, Georges Ghazi

引用次数: 0

Delay-D: Research on the Lifespan and Performance of Storage Devices in Unmanned Aerial Vehicles 延迟-D：无人驾驶飞行器中存储设备的寿命和性能研究

IF 2.6 3区工程技术

Aerospace Pub Date : 2023-12-31 DOI: 10.3390/aerospace11010047

Donghyun Kang

引用次数: 0

Multi-Objective Bayesian Optimization Design of Elliptical Double Serpentine Nozzle 椭圆形双蛇形喷嘴的多目标贝叶斯优化设计

IF 2.6 3区工程技术

Aerospace Pub Date : 2023-12-31 DOI: 10.3390/aerospace11010048

Saile Zhang, Qingzhen Yang, Rui Wang, Xufei Wang

{"title":"Multi-Objective Bayesian Optimization Design of Elliptical Double Serpentine Nozzle","authors":"Saile Zhang, Qingzhen Yang, Rui Wang, Xufei Wang","doi":"10.3390/aerospace11010048","DOIUrl":"https://doi.org/10.3390/aerospace11010048","url":null,"abstract":"The use of traditional optimization methods in engineering design problems, specifically in aerodynamic and infrared stealth optimization for engine nozzles, requires a large number of objective function evaluations, therefore introducing a considerable challenge in terms of time constraints. In this paper, this limitation is addressed by using a sample-efficient multi-objective Bayesian optimization that takes Kriging as a surrogate model and Expected Hypervolume Improvement as the infill criterion. Using this approach, the probabilistic model is continuously established and updated, and the approximate Pareto front is obtained at a relatively small computational budget. The objective of this work is to evaluate the applicability of employing a multi-objective Bayesian optimization framework for the aerodynamic-infrared shape optimization of an elliptical double serpentine nozzle at 6 km flight condition, where the objective functions are evaluated by means of high-fidelity computational fluid dynamics and reversed Monte Carlo ray tracing simulations. We achieve good results in both infrared radiation signature reduction and aerodynamic performance improvement with a reasonable number of evaluations, indicating that the proposed method is effective and efficient for tackling the computationally intensive optimization challenges in the aircraft design.","PeriodicalId":48525,"journal":{"name":"Aerospace","volume":"103 32","pages":""},"PeriodicalIF":2.6,"publicationDate":"2023-12-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139133547","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"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

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