Pub Date : 2021-05-10DOI: 10.4050/f-0077-2021-16698
Jason K. Cornelius, D. Adams, L. Young, J. Langelaan, T. Opazo, S. Schmitz, Lev Rodovskiy, B. Villac
The Dragonfly lander will enter the Titan atmosphere following an approximate 7–10-year journey through space inside its aeroshell. After atmospheric entry, deployment of the main parachute, and heatshield release, the lander will begin its transition to powered flight (TPF). TPF is a maneuver sequence used for mid-air deployment of the Dragonfly rotorcraft lander. The sequence starts just after lander release with the rotors lightly loaded and finishes when a steadystate descent condition has been attained. Mid-air deployment of a multicopter unmanned aerial system is a multidisciplinary problem involving controller choice and tuning, trajectory planning and optimization, and computational fluid dynamics analyses. This paper is an introduction to the transition of rotor flow states in TPF from the windmill brake state, through the turbulent wake state and vortex ring state, and the successful emergence into a normal operating state. A particle swarm optimized controller’s nominal trajectory is plotted on a rotor aerodynamics state chart to show the trajectory’s path through the flow states along the TPF maneuver. Results of preliminary CFD simulations show the variance of individual rotor thrust and power in the early stages of TPF followed by a successful stabilization of rotor performance. Interactional aerodynamic studies also characterize the pre-release flowfield around the lander to be benign at the start of the maneuver. Additionally, results for the lander in steady axial descent show a previously observed coaxial rotor shielding phenomenon of the upper rotor from the effects of vortex ring state.
{"title":"Dragonfly - Aerodynamics during Transition to Powered Flight","authors":"Jason K. Cornelius, D. Adams, L. Young, J. Langelaan, T. Opazo, S. Schmitz, Lev Rodovskiy, B. Villac","doi":"10.4050/f-0077-2021-16698","DOIUrl":"https://doi.org/10.4050/f-0077-2021-16698","url":null,"abstract":"\u0000 The Dragonfly lander will enter the Titan atmosphere following an approximate 7–10-year journey through space inside its aeroshell. After atmospheric entry, deployment of the main parachute, and heatshield release, the lander will begin its transition to powered flight (TPF). TPF is a maneuver sequence used for mid-air deployment of the Dragonfly rotorcraft lander. The sequence starts just after lander release with the rotors lightly loaded and finishes when a steadystate descent condition has been attained. Mid-air deployment of a multicopter unmanned aerial system is a multidisciplinary problem involving controller choice and tuning, trajectory planning and optimization, and computational fluid dynamics analyses. This paper is an introduction to the transition of rotor flow states in TPF from the windmill brake state, through the turbulent wake state and vortex ring state, and the successful emergence into a normal operating state. A particle swarm optimized controller’s nominal trajectory is plotted on a rotor aerodynamics state chart to show the trajectory’s path through the flow states along the TPF maneuver. Results of preliminary CFD simulations show the variance of individual rotor thrust and power in the early stages of TPF followed by a successful stabilization of rotor performance. Interactional aerodynamic studies also characterize the pre-release flowfield around the lander to be benign at the start of the maneuver. Additionally, results for the lander in steady axial descent show a previously observed coaxial rotor shielding phenomenon of the upper rotor from the effects of vortex ring state.\u0000","PeriodicalId":273020,"journal":{"name":"Proceedings of the Vertical Flight Society 77th Annual Forum","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131919928","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}
Pub Date : 2021-05-10DOI: 10.4050/f-0077-2021-16722
R. Jain
Computational Fluid Dynamics (CFD) turbulence transition models are evaluated for rotors in unsteady axial and in forward flight conditions. The study is carried out using CREATETM -AV Helios with NASA codes, Overflow and FUN3D, as the near-body solvers. Three transition models are considered, Amplification Factor Transport (AFT), Langtry-Menter γ-Reθt (LM), and the LM with a crossflow transition model. The LM model is modified to allow for Galilean invariance. The validation study utilizes the data from two recent rotor tests where unsteady transition measurements were obtained on the upper (suction) surface of rotor blades using a novel application of the Differential Infrared Thermography (DIT) technique. The first configuration, the DLR RTG rotor, is a four-blade, 2.13-foot radius rotor in axial flow with pitching blades, operating at Reynolds numbers of 3.2 x 10-5 and 1.7 x 10-5> at three quarter radius, for the two test cases studied. The second configuration, the PSP rotor, is a model-scale, 5.58-foot radius, three-blade rotor in a high-advance-ratio, high-thrust forward flight condition, mounted on a ROBIN-Mod7 fuselage, and operating at a hover Reynolds number of 1.25 x 10-6 at three quarter radius. For this rotor, the validation study also included the DIT measurements on the lower (pressure) surface. Both configurations exhibit large unsteadiness in transition locations. CFD predictions are obtained using consistent grid resolution and numerical settings across the three models and the two rotor configurations. The computed results are analyzed in terms of the rotor transition maps, separation maps, and surface streamlines on the blade upper and lower surfaces. The agreement with the test data is good, in general, including the rapid, unsteady movement of the transition locations.
对旋翼在非定常轴向和前向飞行条件下的湍流转捩模型进行了计算流体力学(CFD)评估。该研究使用CREATETM -AV Helios和NASA代码Overflow和FUN3D作为近体解算器进行。考虑了放大因子输运(AFT)、Langtry-Menter γ-Reθt (LM)和具有横流输运模型的LM三种输运模型。LM模型被修改为允许伽利略不变性。验证研究利用了最近两次转子试验的数据，其中使用差分红外热成像(DIT)技术的新应用，在转子叶片的上(吸力)表面获得了非定常过渡测量。第一种配置是DLR RTG转子，在轴向流动中是一个四叶，半径2.13英尺的转子，带俯伏叶片，在四分之三半径处的雷诺数为3.2 x 10-5和1.7 x 10-5>。第二种配置，PSP旋翼，是一个模型规模的、半径5.58英尺的三叶旋翼，在高推进比、高推力的前飞条件下，安装在ROBIN-Mod7机身上，在四分之三半径处的悬停雷诺数为1.25 x 10-6。对于该转子，验证研究还包括在较低(压力)表面的DIT测量。两种构型在过渡位置都表现出很大的不稳定性。CFD预测是通过三种模型和两种转子配置的一致网格分辨率和数值设置获得的。从转子过渡图、分离图和叶片上下表面流线三个方面对计算结果进行了分析。总的来说，与试验数据吻合较好，包括过渡位置的快速、不稳定运动。
{"title":"CFD Turbulence Transition Models Validation for Rotors in Unsteady Axial and Forward-flight Conditions using CREATETM-AV Helios","authors":"R. Jain","doi":"10.4050/f-0077-2021-16722","DOIUrl":"https://doi.org/10.4050/f-0077-2021-16722","url":null,"abstract":"\u0000 Computational Fluid Dynamics (CFD) turbulence transition models are evaluated for rotors in unsteady axial and in forward flight conditions. The study is carried out using CREATETM -AV Helios with NASA codes, Overflow and FUN3D, as the near-body solvers. Three transition models are considered, Amplification Factor Transport (AFT), Langtry-Menter γ-Reθt (LM), and the LM with a crossflow transition model. The LM model is modified to allow for Galilean invariance. The validation study utilizes the data from two recent rotor tests where unsteady transition measurements were obtained on the upper (suction) surface of rotor blades using a novel application of the Differential Infrared Thermography (DIT) technique. The first configuration, the DLR RTG rotor, is a four-blade, 2.13-foot radius rotor in axial flow with pitching blades, operating at Reynolds numbers of 3.2 x 10-5 and 1.7 x 10-5> at three quarter radius, for the two test cases studied. The second configuration, the PSP rotor, is a model-scale, 5.58-foot radius, three-blade rotor in a high-advance-ratio, high-thrust forward flight condition, mounted on a ROBIN-Mod7 fuselage, and operating at a hover Reynolds number of 1.25 x 10-6 at three quarter radius. For this rotor, the validation study also included the DIT measurements on the lower (pressure) surface. Both configurations exhibit large unsteadiness in transition locations. CFD predictions are obtained using consistent grid resolution and numerical settings across the three models and the two rotor configurations. The computed results are analyzed in terms of the rotor transition maps, separation maps, and surface streamlines on the blade upper and lower surfaces. The agreement with the test data is good, in general, including the rapid, unsteady movement of the transition locations.\u0000","PeriodicalId":273020,"journal":{"name":"Proceedings of the Vertical Flight Society 77th Annual Forum","volume":"18 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132674329","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}
Pub Date : 2021-05-10DOI: 10.4050/f-0077-2021-16825
H. Xin, A. Black, T. Herrmann, Patricia Jaeger, M. Luszcz, T. Smith, A. Thorsen, Chi Zhang
Flight dynamics models for engineering simulation are vital to rotorcraft design and testing. This paper focuses on a multi-year effort to develop and improve the S-97 RAIDER® flight dynamics model in State-Space GenHel and to correlate the model with flight test data. State-Space GenHel (SSGH) is an upgraded version of legacy GenHel with a series of new/enhanced modeling capabilities. The S-97 model has been used to support conceptual, preliminary, and detailed air vehicle design, control laws (CLAWS) design and tuning, handling qualities evaluation, flight loads development, system integration lab (SIL) testing, flight testing, and test pilot training. During the ongoing flight test program, the SSGH model has been continuously updated to improve correlation with the test data. The correlation spans a wide range of flight conditions including hover, low speed flight, level flight, chirp tests at different speeds, and various maneuvers. A series of reduced-order models and corrections were implemented in SSGH to capture the complicated physics missed in the baseline model. High-fidelity analytical tools and component test data were used to derive the parameters for these reduced-order models and corrections, with which the model-data correlation has been significantly improved. The paper also discusses the challenges in tip clearance prediction and in modeling the rotor on propeller interference. This study shows that an engineering model, continuously improved using appropriate methods, can capture the flight dynamics characteristics of a high-speed compound helicopter with sufficient accuracy for supporting CLAWS design and flight test.
{"title":"S-97 RAIDER® GenHel Model Development and Correlation with Flight Test Data","authors":"H. Xin, A. Black, T. Herrmann, Patricia Jaeger, M. Luszcz, T. Smith, A. Thorsen, Chi Zhang","doi":"10.4050/f-0077-2021-16825","DOIUrl":"https://doi.org/10.4050/f-0077-2021-16825","url":null,"abstract":"\u0000 Flight dynamics models for engineering simulation are vital to rotorcraft design and testing. This paper focuses on a multi-year effort to develop and improve the S-97 RAIDER® flight dynamics model in State-Space GenHel and to correlate the model with flight test data. State-Space GenHel (SSGH) is an upgraded version of legacy GenHel with a series of new/enhanced modeling capabilities. The S-97 model has been used to support conceptual, preliminary, and detailed air vehicle design, control laws (CLAWS) design and tuning, handling qualities evaluation, flight loads development, system integration lab (SIL) testing, flight testing, and test pilot training. During the ongoing flight test program, the SSGH model has been continuously updated to improve correlation with the test data. The correlation spans a wide range of flight conditions including hover, low speed flight, level flight, chirp tests at different speeds, and various maneuvers. A series of reduced-order models and corrections were implemented in SSGH to capture the complicated physics missed in the baseline model. High-fidelity analytical tools and component test data were used to derive the parameters for these reduced-order models and corrections, with which the model-data correlation has been significantly improved. The paper also discusses the challenges in tip clearance prediction and in modeling the rotor on propeller interference. This study shows that an engineering model, continuously improved using appropriate methods, can capture the flight dynamics characteristics of a high-speed compound helicopter with sufficient accuracy for supporting CLAWS design and flight test.\u0000","PeriodicalId":273020,"journal":{"name":"Proceedings of the Vertical Flight Society 77th Annual Forum","volume":"53 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"117266697","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}
Pub Date : 2021-05-10DOI: 10.4050/f-0077-2021-16731
T. Fitzgibbon, G. Barakos, M. Woodgate
This paper presents the demonstration of a high-fidelity optimisation framework applied to the AH-64A rotor blade planform. The framework implementation includes an adjoint-harmonic balance method, which allows for efficient performance predictions and evaluation of the design sensitivities for unsteady rotor flows, whilst maintaining the f idelity of the Navier-Stokes equations. A re-design of the AH-64A blade is performed, leading to significant performance benefits, and showing the great potential of high-fidelity CFD coupled with optimisation methods. The key design features that lead to performance improvements in hover and forward flight are discussed, including the advantages and disadvantages of blades with an offloaded blade tip. The influence of the optimisation setup, including the impact of the blade surface parameterisation, treatment of trim and number of harmonic balance modes within the CFDsolution on the final optimised shape is analysed throughout the paper.
{"title":"Optimisation of the AH-64A Blade Planform Based on High-Fidelity CFD Methods ","authors":"T. Fitzgibbon, G. Barakos, M. Woodgate","doi":"10.4050/f-0077-2021-16731","DOIUrl":"https://doi.org/10.4050/f-0077-2021-16731","url":null,"abstract":"\u0000 This paper presents the demonstration of a high-fidelity optimisation framework applied to the AH-64A rotor blade planform. The framework implementation includes an adjoint-harmonic balance method, which allows for efficient performance predictions and evaluation of the design sensitivities for unsteady rotor flows, whilst maintaining the f idelity of the Navier-Stokes equations. A re-design of the AH-64A blade is performed, leading to significant performance benefits, and showing the great potential of high-fidelity CFD coupled with optimisation methods. The key design features that lead to performance improvements in hover and forward flight are discussed, including the advantages and disadvantages of blades with an offloaded blade tip. The influence of the optimisation setup, including the impact of the blade surface parameterisation, treatment of trim and number of harmonic balance modes within the CFDsolution on the final optimised shape is analysed throughout the paper.\u0000","PeriodicalId":273020,"journal":{"name":"Proceedings of the Vertical Flight Society 77th Annual Forum","volume":"57 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"117308724","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}
Pub Date : 2021-05-10DOI: 10.4050/f-0077-2021-16705
M. Floros, Hao Kang
Coaxial, counter-rotating rotors from six to nine inches in diameter were evaluated to measure thrust and torque with variations in rotor spacing, thrust level, and the propeller pitch of the upper and lower rotors. The upper rotor was trimmed to specific thrust targets while the lower rotor was trimmed to produce zero overall torque. For the range of propeller pitch models tested, the data showed that increasing the propeller pitch on the lower rotor decreased the combined thrust of the coaxial system, but increased its efficiency. The rotor efficiency was insensitive to thrust level and rotor spacing, down to 0.116R. The lower rotor share of the overall thrust increased with increasing rotor diameter and with decreasing lower rotor pitch.
{"title":"Experimental Evaluation of Coaxial Micro-UAS Propellers","authors":"M. Floros, Hao Kang","doi":"10.4050/f-0077-2021-16705","DOIUrl":"https://doi.org/10.4050/f-0077-2021-16705","url":null,"abstract":"Coaxial, counter-rotating rotors from six to nine inches in diameter were evaluated to measure thrust and torque with variations in rotor spacing, thrust level, and the propeller pitch of the upper and lower rotors. The upper rotor was trimmed to specific thrust targets while the lower rotor was trimmed to produce zero overall torque. For the range of propeller pitch models tested, the data showed that increasing the propeller pitch on the lower rotor decreased the combined thrust of the coaxial system, but increased its efficiency. The rotor efficiency was insensitive to thrust level and rotor spacing, down to 0.116R. The lower rotor share of the overall thrust increased with increasing rotor diameter and with decreasing lower rotor pitch.","PeriodicalId":273020,"journal":{"name":"Proceedings of the Vertical Flight Society 77th Annual Forum","volume":"20 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115320131","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}
Pub Date : 2021-05-10DOI: 10.4050/f-0077-2021-16796
W. Geyer, Barbara Gordon, C. Mattei, Dwight Robinson
The U.S. Naval Test Pilot School (USNTPS) qualifies engineering test pilots and flight test engineers for the Department of Defense (DoD) and foreign militaries. The school operates UH-72A and UH-60L aircraft as core rotary wing platforms used for airborne instruction in performance, flying qualities (FQ) and advanced flight control systems flight testing. The stability and control portion of the syllabus teaches both time and frequency domain flight test techniques in the evaluation of aircraft handling qualities (HQ); however, only classic time domain techniques have been instructed in the aircraft to support the curriculum. As frequency domain testing has become common practice across the DoD and within industry, the importance of providing entry level instruction in those flight test techniques cannot be overstated. Having students conduct many of the frequency domain test techniques in the aircraft is not practical. Providing adequate control measures such as real-time data monitoring and instructor pilot involvement on each flight to ensure safe execution would place an unrealistic burden on the USNTPS staff and adversely impact the airworthiness of the school’s aircraft. The USNTPS simulation laboratory recently received a high fidelity UH-60 flight dynamics simulation model enabling the instruction of frequency domain flight test techniques and the collection of predictive HQ data as defined within the ADS-33E-PRF, Handling Qualities Requirements for Military Rotorcraft. These data are used to support assigned HQ flights flown on Naval Test Wing Atlantic’s ADS-33 Mission Task Element course. Conducting systems identification testing and the subsequent development of a high fidelity UH-72A flight dynamics simulation model allows the execution of the entire Low Airspeed FQ exercise across both core platforms. Simulator-based predictive HQ data are now utilized in support of assigned HQ flights in the respective aircraft. This paper covers the development of the UH-72A simulation model, flight test efforts supporting that development and the successful integration of the model as a means to collect predictive HQ data in support of the Low Airspeed FQ exercise at the USNTPS.
{"title":"Development of UH-72A Simulator Model in Support of ADS-33 Training","authors":"W. Geyer, Barbara Gordon, C. Mattei, Dwight Robinson","doi":"10.4050/f-0077-2021-16796","DOIUrl":"https://doi.org/10.4050/f-0077-2021-16796","url":null,"abstract":"\u0000 The U.S. Naval Test Pilot School (USNTPS) qualifies engineering test pilots and flight test engineers for the Department of Defense (DoD) and foreign militaries. The school operates UH-72A and UH-60L aircraft as core rotary wing platforms used for airborne instruction in performance, flying qualities (FQ) and advanced flight control systems flight testing. The stability and control portion of the syllabus teaches both time and frequency domain flight test techniques in the evaluation of aircraft handling qualities (HQ); however, only classic time domain techniques have been instructed in the aircraft to support the curriculum. As frequency domain testing has become common practice across the DoD and within industry, the importance of providing entry level instruction in those flight test techniques cannot be overstated. Having students conduct many of the frequency domain test techniques in the aircraft is not practical. Providing adequate control measures such as real-time data monitoring and instructor pilot involvement on each flight to ensure safe execution would place an unrealistic burden on the USNTPS staff and adversely impact the airworthiness of the school’s aircraft. The USNTPS simulation laboratory recently received a high fidelity UH-60 flight dynamics simulation model enabling the instruction of frequency domain flight test techniques and the collection of predictive HQ data as defined within the ADS-33E-PRF, Handling Qualities Requirements for Military Rotorcraft. These data are used to support assigned HQ flights flown on Naval Test Wing Atlantic’s ADS-33 Mission Task Element course. Conducting systems identification testing and the subsequent development of a high fidelity UH-72A flight dynamics simulation model allows the execution of the entire Low Airspeed FQ exercise across both core platforms. Simulator-based predictive HQ data are now utilized in support of assigned HQ flights in the respective aircraft. This paper covers the development of the UH-72A simulation model, flight test efforts supporting that development and the successful integration of the model as a means to collect predictive HQ data in support of the Low Airspeed FQ exercise at the USNTPS.\u0000","PeriodicalId":273020,"journal":{"name":"Proceedings of the Vertical Flight Society 77th Annual Forum","volume":"62 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115557909","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}
Pub Date : 2021-05-10DOI: 10.4050/f-0077-2021-16894
Stefan Görlich, Rainer Arelt, Jan-Christoph Arent
The H160-B is the latest recently certified helicopter from Airbus Helicopters with extensive use of composite materials in the airframe. In this paper an overview of the fuselage architecture and its design will be provided. During the design phase emphasis was laid on close cooperation between all the involved engineering disciplines like architecture, design, stress, tooling, manufacturing simulation and production. Target was to achieve smaller tolerances resulting in better fit of the parts during assembly, increase first time right and show compliance with the latest airworthiness requirements. For composite parts this process will be shown using the examples of a main frame in prepreg technology and the Upper Deck Framework in RTM technology. The substantiation of the airframe was based on the similar new structure approach with analytical tools for numerical simulation that have been supported by tests of novel design features.
{"title":"H160 Composite Fuselage: Multidisciplinary Approach","authors":"Stefan Görlich, Rainer Arelt, Jan-Christoph Arent","doi":"10.4050/f-0077-2021-16894","DOIUrl":"https://doi.org/10.4050/f-0077-2021-16894","url":null,"abstract":"\u0000 The H160-B is the latest recently certified helicopter from Airbus Helicopters with extensive use of composite materials in the airframe. In this paper an overview of the fuselage architecture and its design will be provided. During the design phase emphasis was laid on close cooperation between all the involved engineering disciplines like architecture, design, stress, tooling, manufacturing simulation and production. Target was to achieve smaller tolerances resulting in better fit of the parts during assembly, increase first time right and show compliance with the latest airworthiness requirements. For composite parts this process will be shown using the examples of a main frame in prepreg technology and the Upper Deck Framework in RTM technology. The substantiation of the airframe was based on the similar new structure approach with analytical tools for numerical simulation that have been supported by tests of novel design features.\u0000","PeriodicalId":273020,"journal":{"name":"Proceedings of the Vertical Flight Society 77th Annual Forum","volume":"28 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123951254","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}
Pub Date : 2021-05-10DOI: 10.4050/f-0077-2021-16742
Calvin Lu, Justin Blanco, R. Celi, R. Gentili, B. Hatfield, Hyuk Oh, Jessica Mohlar, Ann C. Vanleer
Assessment of operator support technology is of great concern in order to enhance pilots’ safety and performance. Accordingly, the development of the Terrain Obstacle Avoidance Display (TOAD) guidance system is a specific example of such technology, and the present study was conducted to examine if TOAD decreases the operator’s mental workload, allowing for better decision-making capacity under conditions of stress, such as that induced by diminished cues during exposure to degraded visual environments (DVE). Specifically, we examined rotorcraft pilots’ cognitive workload during simulated flight with this visual assistive technology to understand the impact of TOAD on mental workload under variable conditions of challenge using a suite of physiological sensors, subjective ratings of work and flight performance. Collectively, the results for the biophysiological markers and subjective ratings revealed a reduction of the pilot’s cognitive workload when flying with the assistance of TOAD relative to flight without such assistance. In addition, the employment of assistive technology resulted in a trend toward a greater reduction of collisions. Overall, the results provide evidence of the effectiveness of TOAD assistive technology to enhance pilot safety and performance.
{"title":"Assessment of Augmented Operator's Mental Workload with Visual Assistive Technology in Simulated Rotorcraft Piloting Tasks","authors":"Calvin Lu, Justin Blanco, R. Celi, R. Gentili, B. Hatfield, Hyuk Oh, Jessica Mohlar, Ann C. Vanleer","doi":"10.4050/f-0077-2021-16742","DOIUrl":"https://doi.org/10.4050/f-0077-2021-16742","url":null,"abstract":"\u0000 Assessment of operator support technology is of great concern in order to enhance pilots’ safety and performance. Accordingly, the development of the Terrain Obstacle Avoidance Display (TOAD) guidance system is a specific example of such technology, and the present study was conducted to examine if TOAD decreases the operator’s mental workload, allowing for better decision-making capacity under conditions of stress, such as that induced by diminished cues during exposure to degraded visual environments (DVE). Specifically, we examined rotorcraft pilots’ cognitive workload during simulated flight with this visual assistive technology to understand the impact of TOAD on mental workload under variable conditions of challenge using a suite of physiological sensors, subjective ratings of work and flight performance. Collectively, the results for the biophysiological markers and subjective ratings revealed a reduction of the pilot’s cognitive workload when flying with the assistance of TOAD relative to flight without such assistance. In addition, the employment of assistive technology resulted in a trend toward a greater reduction of collisions. Overall, the results provide evidence of the effectiveness of TOAD assistive technology to enhance pilot safety and performance.\u0000","PeriodicalId":273020,"journal":{"name":"Proceedings of the Vertical Flight Society 77th Annual Forum","volume":"23 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125237157","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}
Pub Date : 2021-05-10DOI: 10.4050/f-0077-2021-16746
Z. Szoboszlay, Martine Godfroy-Cooper, J. Miller
The Degraded Visual Environment Mitigation (DVE-M) program was initiated to develop and evaluate numerous technologies that would enable rotorcraft to intentionally operate in poor visibility conditions. The goal was to provide recommendations to the Future Vertical Lift program and to various upgrade programs of the existing fleet of military rotorcraft. The DVE-M program was implemented by the U.S. Army Combat Capabilities Development Command Aviation and Missile Center (DEVCOM AvMC). Technologies developed and evaluated fell into one of three categories: 1) sensors and sensor fusion, 2) pilot cueing, 3) flight control and guidance. These technologies were integrated to work together to enable the pilot to operate in DVE. This paper focuses on the design of the cueing system only. It discusses reasons for the design choices and lessons learned. This paper also provides an overview of the flight demonstrations and simulations conducted for background.
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Pub Date : 2021-05-10DOI: 10.4050/f-0077-2021-16856
D. Specht, C. Johnson, N. Bouaynaya, G. Rasool
Location data about U.S. heliports is often inaccurate or nonexistent in the FAA's databases, which leaves pilots and air ambulance operators with inaccurate information about where to find safe landing zones. In the 2018 FAA Reauthorization Act, Congress required the FAA to collect better information from the helicopter industry under part 157, which covers the construction, alteration, activation and deactivation of airports and heliports. At the same time, there is no requirement to report private helipads to the FAA when constructed or removed, and some public heliports do not have up to date records. This paper proposes an autonomous system that can authenticate the coordinates in the FAA master database, as well as search for helipads in a designated large area. The proposed system is based on a convolutional neural network model that learns optimal helipad features from the data. We used the FAA's 5010 database and others to construct a benchmark database of rotocraft landing sites. The database consists of 9,324 aerial images, containing helipads, helistops, helidecks, and helicopter runways in rural and urban areas, as well as negative examples, such as rooftop buildings and fields. The dataset was then used to train various state-of-the-art convolutional neural network models. The outperforming model, EfficientNet-bθ, achieved nearly 95% accuracy on the validation set.
{"title":"Intelligent Helipad Detection from Satellite Imagery","authors":"D. Specht, C. Johnson, N. Bouaynaya, G. Rasool","doi":"10.4050/f-0077-2021-16856","DOIUrl":"https://doi.org/10.4050/f-0077-2021-16856","url":null,"abstract":"\u0000 Location data about U.S. heliports is often inaccurate or nonexistent in the FAA's databases, which leaves pilots and air ambulance operators with inaccurate information about where to find safe landing zones. In the 2018 FAA Reauthorization Act, Congress required the FAA to collect better information from the helicopter industry under part 157, which covers the construction, alteration, activation and deactivation of airports and heliports. At the same time, there is no requirement to report private helipads to the FAA when constructed or removed, and some public heliports do not have up to date records. This paper proposes an autonomous system that can authenticate the coordinates in the FAA master database, as well as search for helipads in a designated large area. The proposed system is based on a convolutional neural network model that learns optimal helipad features from the data. We used the FAA's 5010 database and others to construct a benchmark database of rotocraft landing sites. The database consists of 9,324 aerial images, containing helipads, helistops, helidecks, and helicopter runways in rural and urban areas, as well as negative examples, such as rooftop buildings and fields. The dataset was then used to train various state-of-the-art convolutional neural network models. The outperforming model, EfficientNet-bθ, achieved nearly 95% accuracy on the validation set.\u0000","PeriodicalId":273020,"journal":{"name":"Proceedings of the Vertical Flight Society 77th Annual Forum","volume":"16 7 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128190341","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}
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