scholarly journals Refining the aerodynamic moment of the missile based on flight test results

2021 ◽  
pp. 47-56
Author(s):  
V. N. Akimov ◽  
A. A. Kostyukov ◽  
E. N. Kravchuk ◽  
K. O. Rozantsev
Keyword(s):  
Mathematical Simulation ◽  
Test Data ◽  
Gas Dynamics ◽  
Flight Test ◽  
Research Paper ◽  
Test Results ◽  
Flight Tests ◽  
Aerodynamic Moment ◽  
Simulation Results

This research paper is intended to refine the aerodynamic moment of the missile based on an analysis of flight tests and results of gas dynamics software computations. The paper compares mathematical simulation results with flight test data in order to demonstrate an improved convergence due to the proposed refinement.

Dynamic Simulation and Ground Testing of the Autonomous Vertical Air-Launch Sled Concept

2020 ◽  
Author(s):  
Peter Lee ◽  
Nesrin Sarigul-Klijn
Keyword(s):  
Dynamic Response ◽  
Flight Test ◽  
Front Wheel ◽  
Lateral Stability ◽  
Test Results ◽  
Flight Tests ◽  
Ground Testing ◽  
Remotely Piloted Aircraft ◽  
Correct Path ◽  
Measures Of Performance

Abstract A unique towed air-launch concept called the vertical air-launch sled is studied using a 1/32nd scale vehicle. The sled allows a launch vehicle carried by it to be towed to an altitude by a mother aircraft using a standard towline. The focus was to design and test autonomous tow taxi and takeoff phase of flight using simulations and flight tests. In order to study the scaling validity, experimental flight test data was compared to the theoretically predicted dynamic response of the scaled system, as well as compared to a theoretically predicted dynamic response of the full-scale system. The towing aircraft is a 1/11th scale T-28 remotely piloted aircraft. Lateral stability, runway centerline following ability as well as tautness of the tow line are studied as measures of performance of the autonomous system designed. Test results are reported showing that the tow aircraft was able to tow the vehicle along the correct path. It is identified that the rudder servos were saturated in adjusting the trajectory and future flight tests will include implementing front wheel steering into the system to alleviate the rudder servos saturation. Duration of the flight tests will be increased to better evaluate the automatic controller.

Collaborative Autonomy for Mapping, Search, and Pursuit

2016 ◽  
Vol 04 (02) ◽  
pp. 167-184
Author(s):  
John G. Mooney ◽  
Stephen Haviland ◽  
Eric N. Johnson
Keyword(s):  
Decision Making ◽  
Flight Test ◽  
Detection Technique ◽  
Test Results ◽  
Flight Tests ◽  
Simulation Tools ◽  
Autonomous Decision ◽  
Location Detection ◽  
Collaborative Autonomy

This paper describes the development and flight tests of a multi-aircraft collaborative architecture, focused on decentralized autonomous decision making to solve a scenario-driven challenge problem. The architecture includes two search coverage algorithms, a hide location detection technique, behavior estimation, and a target manipulation algorithm. The architecture was implemented on a pair of Yamaha RMAX helicopters outfitted with modular avionics, as well as an associated set of simulation tools. Simulation and flight test results for single- and multiple aircraft scenarios are presented. Further work suggested includes identification and development of more sophisticated evader models and pursuit algorithms.

Wavelet Neural Network with PLS Feature Extraction and its Application in Aerodynamic Modeling for Aircraft Stall

2014 ◽  
Vol 602-605 ◽  
pp. 3131-3134
Author(s):  
Xu Sheng Gan ◽  
Xue Qin Tang ◽  
Hai Long Gao
Keyword(s):  
Neural Network ◽  
Feature Extraction ◽  
Least Squares ◽  
Partial Least Squares ◽  
Test Data ◽  
Flight Test ◽  
Data Simulation ◽  
Aerodynamic Modeling ◽  
Aerodynamic Model ◽  
Simulation Results

An aerodynamic modeling method based on WNN with Partial Least Squares (PLS) is proposed. In the method, PLS first is applied to extract the feature of original aerodynamic data samples, and then the obtained feature is used to establish the WNN aerodynamic model for aircraft stall from flight test data. Simulation results are given to illustrate that the proposed method is effective and feasible.

scholarly journals A Flight Test Method of Flammable Liquid Leakage and Discharge for Certain Aircraft

2018 ◽  
Vol 227 ◽  
pp. 01001
Author(s):  
Jiangtao Song ◽  
Yan Zhao ◽  
Yu Li
Keyword(s):  
Flight Test ◽  
Test Methods ◽  
Test Method ◽  
Test Equipment ◽  
Test Results ◽  
Successful Completion ◽  
Flammable Liquid ◽  
Flight Tests ◽  
Civil Aircraft ◽  
Certification Test

To guarantee the successful completion of airworthiness certification test for a certain type of aircraft, the leakage and discharge compliance criteria of flammable liquid were designed by studying airworthiness requirements and the design characteristic of the civil aircraft, where flammable liquid leakage zones and hazardous zones in which liquids are not allowed to enter were determined. Further the test equipments and the dyeing liquor for replacing flammable fluid were developed, and ground and flight test methods were proposed. Moreover, the above test equipment and methods were applied to flight tests of flammable liquid leakage and discharge for certain civil aircraft. The test results show that the test equipment is stable and reliable, and the flight test method can accurately demonstrate the flammable liquid leakage and discharge.

Comparison of Ductile Tearing Simulation With Complex Cracked Pipe Test Data

2016 ◽  
Vol 139 (1) ◽  
Author(s):  
Kyung-Dong Bae ◽  
Ho-Wan Ryu ◽  
Yun-Jae Kim ◽  
Jong-Sung Kim
Keyword(s):  
Test Data ◽  
Mouth Opening ◽  
Fracture Toughness Test ◽  
Test Results ◽  
Ductile Tearing ◽  
Load Line Displacement ◽  
Resistance Curves ◽  
Simulation Results ◽  
Complex Crack ◽  
Strain Model

This paper presents numerical ductile tearing simulation results of four complex cracked pipes made of two materials, performed at Battelle, Columbus, OH. In ductile tearing simulation, stress-modified fracture strain model is used, which is determined from tensile test results and fracture toughness test data. Overall good agreement is found in comparing simulation results with experimental load, crack length, and crack mouth opening displacements versus load-line displacement (LLD) data. The effect of the complex crack on J–resistance curves is discussed.

scholarly journals Mechanism and Improve Methods of Rudder Lock for Mechanically Controlled Aircraft

2018 ◽  
Vol 36 (3) ◽  
pp. 577-581
Author(s):  
Yan Liu ◽  
Ke Zhao ◽  
Jiangtao Huang
Keyword(s):  
Numerical Simulation ◽  
Control System ◽  
Flow Field ◽  
Test Data ◽  
Center Of Pressure ◽  
Flight Test ◽  
Flight Safety ◽  
Dorsal Fin ◽  
Simulation Results ◽  
Strong Vortex

Rudder Lock is a threat to flight safety, which should be carefully considered in the airworthiness certification. Since general aircrafts which are equipped with mechanical control system and controlled by unprofessional pilots becomes more and more popular, researches on rudder lock are still necessary. In this paper, a mechanically controlled medium sized transport is studied as an example. By analyzing the steady straight sideslip flight test data and flow field numerical simulation results, the mechanism of rudder lock is analyzed. Two aerodynamic improving methods including double-triangle dorsal fin and reducing set-back hinge balance are proposed. The flow field numerical simulation results show that double triangle dorsal fin can improve the stall characteristic of vertical tail, but the strong vortex will move the center of pressure forward, which worsens the rudder lock. Reducing set-back hinge balance can improve rudder lock effectively, while the hinge moment and rudder force will be increased, therefore the gearing ratio and tab should be carefully designed.

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