scholarly journals THE DATA ACQUISITION ROLE ON STATIC TEST FOR VALIDATION OF RX320 ROCKET MOTOR DESIGN

2021 ◽  
Vol 6 (1) ◽  
pp. 9-18
Author(s):  
Setiadi Setiadi ◽  
Bagus Wicaksono ◽  
Kurdianto Kurdianto ◽  
Bagus H. Jihad
Keyword(s):  
Data Acquisition ◽  
Numerical Data ◽  
Flight Test ◽  
Rocket Motor ◽  
Chamber Pressure ◽  
Material Strength ◽  
Physical Force ◽  
Static Test ◽  
Static Testing ◽  
Calculation Results

Data Acquisition System has a significant role, especially in static testing of a rocket, determining whether a rocket is declared eligible to fly or not based on the static rocket test. Static testing of the RX320 rocket involves several numerical data instrumentation components, including the Yokogawa DL850 and the CDA900 Signal Conditioner, and the PT750 Pressure sensor. It has functions to accept the physical force that occurs, measure and record the value of the Pressure force in the RX 320 Rocket Chamber at the time Static test during burning time is performed. From the record value of the RX 320 chamber pressure, it can be stated that the RX 320 is suitable for the rocket flight test. The calculation results of the chamber pressure design and the results of measurement and recording of RX320 static test data indicate that the Pressure Chamber RX320 value is still within the safe limits of the RX320 Rocket motor tube material strength.

An analytical and experimental study of a hybrid rocket motor

2014 ◽  
Vol 228 (13) ◽  
pp. 2475-2486 ◽  
Author(s):  
Hadi Rezaei ◽  
Mohammad Reza Soltani
Keyword(s):  
Flow Rate ◽  
Low Cost ◽  
Specific Impulse ◽  
Combustion Products ◽  
Rocket Motor ◽  
Chamber Pressure ◽  
Hybrid Rocket ◽  
Hybrid Rocket Motor ◽  
Chemical Propulsion ◽  
Rate Case

The hybrid rocket motor is a kind of chemical propulsion system that has been recently given serious attention by various industries and research centers. The relative simplicity, safety and low cost of this motor, in comparison with other chemical propulsion motors, are the most important reasons for such interest. Moreover, throttle-ability and thrust variability on demand are additional advantages of this type of motor. In this paper, the result of an internal ballistic simulation of hybrid rocket motor in a zero-dimensional form is presented. Further to validate the code, an experimental setup was designed and manufactured. The simulation results are compared with the experimental data and good agreement is achieved. The effect of various parameters on the motor performance and on the combustion products is also investigated. It is found that increasing the oxidizer flow rate, increases the pressure and specific impulse of the motor; however, the slope of the specific impulse for the high flow rate case reduces. In addition, by increasing the combustion chamber pressure, the specific impulse is increased considerably. The initial diameter of the fuel port does not have significant effect on the pressure chamber and on the specific impulse. Addition of a percentage of an oxidizer like ammonium perchlorate to the fuel increases the specific impulse linearly.

scholarly journals Development of a Simple, Self-Contained Flight Test Data Acquisition System

1981 ◽  
Author(s):  
Ronald R. L. Renz ◽  
Robert Clarke ◽  
Mark A. Mosser ◽  
Jan Roskam ◽  
Dale Rummer
Keyword(s):  
Data Acquisition ◽  
Test Data ◽  
Flight Test ◽  
Data Acquisition System ◽  
Acquisition System

scholarly journals Numerical and Experimental UAV Structure Investigation by Pre-Flight Load Test

Sensors ◽  
2020 ◽  
Vol 20 (11) ◽  
pp. 3014 ◽  
Author(s):  
Artur Kurnyta ◽  
Wojciech Zielinski ◽  
Piotr Reymer ◽  
Krzysztof Dragan ◽  
Michal Dziendzikowski
Keyword(s):  
Computer Aided Design ◽  
Flight Test ◽  
Load Test ◽  
Load Spectrum ◽  
Static Test ◽  
Multi Stage ◽  
Post Test ◽  
Cad Modelling ◽  
Ground Test ◽  
Load Tests

This paper presents the preparation and execution of on-ground static and engine load tests for the composite unmanned aerial vehicle (UAV). The test was conducted for pre-flight structural strength verification of the remotely piloted aerial target named HORNET, after introducing some structural modifications. The ground tests were performed before the flight test campaign, to ensure the strength and operational safety of the modified structure. The panel method and Computer Aided Design (CAD) modelling were adopted for numerical evaluation of aerodynamic and inertial forces’ distribution to simulate loading scenarios for launch, flight and parachute deploying conditions during the static test. Then, the multi-stage airframe static test was prepared and executed with the use of a designed modular test rig, artificial masses, as well as a wireless strain measurement system to perform structure verification. The UAV was investigated with 150% of the typical load spectrum. Furthermore, an engine test was also conducted on a ground test stand to verify strain and vibration levels in correspondence to engine speed, as well as the reliability of data link and the lack of its interferences with wireless control and telemetry. In the article, data achieved from the numerical and experimental parts of the test are discussed, as well as post-test remarks are given.

scholarly journals Improving the design of the earthquake-proof suspension building

2018 ◽  
Vol 36 ◽  
pp. 01001 ◽  
Author(s):  
Taliat Azizov ◽  
Nadzieja Jurkowska
Keyword(s):  
Vertical Component ◽  
Numerical Data ◽  
High Rise ◽  
Calculation Results ◽  
Improved Design ◽  
Supporting Frame ◽  
Dynamic Strains

The proposal for improving the constructive scheme of the supporting frame of the suspension building has been considered. The strains in its bearing elements due to earthquakes are significantly less than in the traditional cantilever buildings. In former schemes the vertical components of strains develop during horizontal oscillations of the grounds. This disadvantage has been eliminated now. It is shown that in the improved design of the structure under the earthquake the vertical component of vibrations is practically absent, due to arrangement of the suspension device strictly vertically. The numerical data for calculation results with variation of some characteristics of the supporting frame and suspensions have been shown in order to allow adjusting the dynamic strains at the vibrations of the base. The scheme for installation the vertical elements of the frame have been proposed. Its usage will allow to build the high-rise suspension buildings.

Navier-Stokes Computation on a Pivoting Doors Thrust Reverser and Comparison With Tests

1992 ◽  
Author(s):  
L. Schreiber ◽  
M. Legras
Keyword(s):  
Flow Field ◽  
Complex Geometry ◽  
Numerical Data ◽  
Navier Stokes ◽  
Complex Flow ◽  
Static Test ◽  
Development Delay ◽  
Cfd Method ◽  
Thrust Reverser ◽  
Reverse Thrust

An engine thrust reverser must meet different aerodynamic requirements to take into account the engine and airplane integration. These requirements are: - Control of the exit area in order to assess a convenient engine compatibility during the reverser operation. - Generation of reverse thrust meeting the level specified by the airframe in order to slowdown the airplane. - Mimization of the reversed flow field interaction with the airplane structure such as wing and shutters. - Avoid the flow reingestion by the engine fan. In order to reduce the tests number, to decrease the development delay and to improve aerodynamic performance, SNECMA group (SNECMA and HISPANO-SUIZA) has decided to develop a CFD method adapted to pivoting doors thrust reverser aerodynamic calculation. This method uses a Navier-Stokes 3D solver (PHOENICS code) well adapted to complex geometry and complex flow field. The mesh is generated with an analytical method and only one domain is used. The computation has been completed assuming laminar viscosity. The numerical data got with this method have been compared to static test realized on a model similar to actual CFM56-5C four doors reverser. The comparison parameters are the static pressure on the doors, the flow rate and the axial reverse thrust.

Design of Data Acquisition Testing System for a Fixed Wing UAV Based on Radio-Frequency Technique and Labview

2013 ◽  
Vol 816-817 ◽  
pp. 550-553
Author(s):  
Xiang Zheng Li ◽  
Xi Wei Peng ◽  
Qing Bo Geng
Keyword(s):  
Radio Frequency ◽  
Data Acquisition ◽  
Flight Test ◽  
Analysis Data ◽  
Test System ◽  
Wireless Data ◽  
Labview Software ◽  
Wireless Data Acquisition ◽  
Vehicle Test ◽  
Data Acquisition And Processing

This paper discusses a system of data acquisition and processing based on radio frequency technology and labview. It is designed for data acquisition and transmission of UAV (Unmanned Aerial Vehicle) test system. It makes full use of the usefulness of labview in measurement field and the flexibility of wireless data transmission.Firstly this paper introduces the hardware and software of wireless data acquisition and transmission device. Then it introduces the design of labview software. Finally UAV test system uses this device to collect and analysis data, it provided a lot of useful information for the UAV flight test.

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