Vertical Wind Tunnel for Prediction of Rocket Flight Dynamics

Bryson, Hoani; Sültrop, Hans Philipp; Buchanan, George; Hann, C.E.; Snowdon, Malcolm; Rao, Avinash; Slee, Adam; Fanning, Kieran; Wright, D. C. H.; McVicar, Jason John; Clark, B A J; Harris, G. D.; Chen, Xiaoqi

doi:10.3390/aerospace3020010

Cited by 7 publications

(3 citation statements)

References 12 publications

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“…various heads shapes preliminary chosen by CFD computations [10] or specific interaction, e.g. lateral jets [11] or transient responses for manuevers [12] appear. For such situations experimental investigation is used to numerical model calibration and for a satisfactory agreement between model and tests' results the simulations can be then treated as a good design and qualitative approach.…”

Section: State Of the Artmentioning

confidence: 99%

Wind Tunnel Tests of Influence of Boosters and Fins on Aerodynamic Characteristics of the Experimental Rocket Platform

Ruchała

Placek

Stryczniewicz

et al. 2017

Transactions on Aerospace Research

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The paper presents results of wind tunnel tests of the Experimental Rocket Platform (ERP), which is developed in Institute of Aviation. It is designed as an easy accessible and affordable platform for microgravity experiments. Proposed design enables to perform experiments in microgravity for almost 150 seconds with apogee of about 100 km. The full-scale model of the ERP has been investigated in the T-3 wind tunnel in Institute of Aviation. During the investigation, the aerodynamic loads of the rocket has been measured for the angle of attack up to 10° and the different rotation angle around the longitudinal axis (up to 90°, depending on the configuration). Three configurations has been investigated: • without fins and boosters • with fins and without boosters • with fins and boosters Additionally, the measurements of velocity field around the ERP using the Particle Image Velocimetry (PIV) has been performed. Based on the wind tunnel test, an influence of fins and boosters on aerodynamic characteristics of the rocket has been described. Results of the wind tunnel tests show relatively high contribution of boosters in total aerodynamic drag. Some conclusions concerning performance and stability of the rocket have been presented.

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Section: State Of the Artmentioning

confidence: 99%

Wind Tunnel Tests of Influence of Boosters and Fins on Aerodynamic Characteristics of the Experimental Rocket Platform

Ruchała

Placek

Stryczniewicz

et al. 2017

Transactions on Aerospace Research

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“…The double returns vertical wind tunnel is a kind of vertical wind tunnel, and has wide application in parachute training, helicopter rotor test, flight experience and other fields [1][2][3][4] . Due to the fast development of new type helicopter, parachute training and requirement of better flight experience, vertical wind tunnel has got more and more input and application.…”

Section: Introductionmentioning

confidence: 99%

Research on General Structure of Double Returns Vertical Wind Tunnel

Shen,

Zhang,

Qiu

et al. 2023

J. Phys.: Conf. Ser.

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Vertical wind tunnels play very important role in parachute training, helicopter rotor test, flight experience and other aspects, among which the double returns vertical wind tunnel has spread widely due to its low lose and low running cost. By using innovative structure design and finite element method, the general layout, research on design of supports and important sections are completed. The design part mainly describes glass flight section, integrated fan section, wind speed adjust device, ventilation door and the whole raft foundation structure. The dynamic debugging results show that the double return vertical wind tunnel has rational design, little vibration and high efficiency.

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“…Sebelum diuji terbang, maka perlu dilakukan simulasi gerak roket dalam terowongan angin untuk menentukan nilai parameter-parameter kendali roket[6] [7]. Rancangan terowongan angin yang digunakan untuk melakukan simulasi gerakan roket kendali ditunjukkan pada Gambar 5.…”

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Perancangan Sistem Roket Kendali Berpemandu Inframerah Menggunakan Metode Pengolahan Citra Yang Disimulasikan Dalam Terowongan Angin

2018

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AbstrakRoket kendali adalah sistem senjata berbasis roket yang memiliki pengendalian otomatis untuk mencari target dan menyesuaikan arah terbangnya. Pada Penelitian ini dirancang sebuah prototipe sistem roket kendali dengan sensor pelacakan sasaran inframerah menggunakan kamera webcam yang dimodifikasi dengan penggantian lensa bawaan dengan lensa tapis pelewat sempit 940 nm. Kamera tersebut diakses menggunakan Raspberry Pi untuk selanjutnya dilakukan proses penapisan citra menggunakan metode pengambangan parameter HSV. Mikrokontroler atmega328 dipasang untuk mengendalikan pergerakan 4 buah servo canard menggunakan metode kendali PID. Dilakukan pula pengambilan parameter IMU 9-DOF dari sensor giroskop dan akselerometer MPU-6050 serta kompas HMC5883l untuk ditampilkan dalam antarmuka C#. Parameter data pelacakan sasaran dan IMU dikirimkan ke komputer menggunakan modul telemetri APC220. Sistem roket kendali yang dirancang kemudian disimulasikan gerakannya dalam terowongan angin. Keluaran dari penelitian ini menghasilkan prototype sistem roket kendali dengan instrumen pelacakan inframerah yang mampu melacak sasaran inframerah 940 nm dengan kecepatan pelacakan sebesar 49,81 FPS. Parameter pengambangan HSV untuk sasaran inframerah 940 nm bernilai hue 0-153, saturation 0-32 dan value 179-255. Parameter PID yang digunakan dalam simulasi dengan kecepatan angin 9±4 m/s bernilai kp = 7, ki = 0, dan kd = 50. Data dari telemetri dapat ditampilkan dalam odometri 2D menggunakan C#. AbstractMissile are rocket-based weapon systems that have automatic controls to find targets and adjust its flight direction. This Research is design a guided missile prototype system with seeker made from modified webcam camera by replacing default lenses with narrow-band pass filter lenses 940 nm. This camera is accessed by Raspberry Pi than process the image with thresholding HSV parameters of the captured image. Control rocket using atmega328 that command 4 canard servos by PID control method. This system also taking 9-DOF IMU parameters using MPU-6050 as gyroscope and accelerometers and HMC-5883l as magnetometer and shown it in C# GUI. All data parameter are delivered to computer wirelessly using telemetry module APC220. This prototype then simulated its movements in wind tunnel. The output of this project resulted an infrared tracking instrument capable of tracking infrared targets with a wavelength of 940 nm with 49.81 FPS tracking speed. The appropriate HSV filtering parameters for 940 nm infrared targets are hue 0-153, saturation 0-32 and value 179-255. The PID parameters kp = 7, ki = 0, and kd = 50 are suitable for wind speed around 9 ± 4 m/s. Data from telemetry can be displayed in 2D odometry using C#.

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Vertical Wind Tunnel for Prediction of Rocket Flight Dynamics

Cited by 7 publications

References 12 publications

Wind Tunnel Tests of Influence of Boosters and Fins on Aerodynamic Characteristics of the Experimental Rocket Platform

Wind Tunnel Tests of Influence of Boosters and Fins on Aerodynamic Characteristics of the Experimental Rocket Platform

Research on General Structure of Double Returns Vertical Wind Tunnel

Perancangan Sistem Roket Kendali Berpemandu Inframerah Menggunakan Metode Pengolahan Citra Yang Disimulasikan Dalam Terowongan Angin

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