Combined Altitude Temperature and Humidity Testing of the Solid State Flight Data Recorder (Ssfdr) for the Su-30 MKI Aircraft

The Solid State Flight Data Recorder (SSFDR) unit was subjected to CATH test in a Combined Altitude, Temperature and Humidity chamber. This unit was developed by M/S SLN Technologies Pvt Ltd Bangalore, for SU-30 MKI Aircraft to HAL,Korwa. This unit has LRU's namely, 1. Data Acquisition Unit(DAU), 2. Recorder Unit (RU) and 3. Control and Indication Unit (CIU). The CATH test was done as per MIL-STD 810F, Method 520.2. After conditioning, the functional test was carried out by the firm and the unit was handed over to them

Environmental Qualification of Buffer Amplifier Unit Using CATH Test Facility for SARAS Aircraft Program

The Buffer Amplifier Unit (BAU) was subjected to Temperature variation and Altitude tests in a Combined Altitude, Temperature and Humidity chamber. This unit was design and developed by Aerospace Electronics Division (ALD), NAL for Saras Aircraft. These tests were done as per RTCA - DO160E, Cat.C, Sec.5.3.1 & Sec. 4.6.1. After conditioning, the functional test was carried out by the firm and the unit was handed over to the firm

Environmental Conditioning of Polymer Composites for Aerospace and Non-Aerospace Applications

Environmental conditioning of polymer composites involves subjecting these material to different conditions like Temperature, Humidity, Altitude, Rain, Fungus, Dust, Salt etc to asses their performance demanded by an application. A conditioning process that simulates the real aging (natural weathering) requires months or even years, which is experimentally unacceptable. Therefore accelerated aging methods have been developed that takes several days or a few weeks. During exposure to various conditions like Thermal Shock, Humidity/Temperature or the combined effect of Altitude, Temperature and Humidity (CATH), the material properties will be affected. This is due to the effect of absorbed moisture in those conditions. This paper brings out the details of qualification tests carried out on prototype Radomes (4Nos) of military Aircraft and representative specimens after painting with an antistatic anti rain erosion paint as per the RCMA approved QTP under the CRI inspection. Some information on the unique Environmental Test Facility available at FRP Division, NAL are also presented. Environmental tests on variety of components (both structural and electronics type of applications) for end user community ranging from inhouse, inter division (ALD, STTD and ACD), premier Defense Establishment (ADRDE, SAC and ADA), public sector units (HAL and BEL) to private industries (Flow tech, SLN Technologies Pvt. Ltd., FLIC Microwave Pvt. Ltd., Spectrum Info Tech Pvt. Ltd., and Data Pattern (India) Pvt. Ltd.)

Post curing and NDT support services for HANSA-3 Aircraft (coded-011) series productionisation program

With reference to the above, after receiving composite components from C-CADD, NDT was carried out using the instrument (Woodpecker-632) on the composite parts of the Hansa Aircraft. NDT was carried out as per standard procedure (Ref : NAL PD RP 9901 available with CQCM Hansa-3 project)

HANSA-3 aircraft series productionisation program-support services (Postcure and NDT qualification)

With reference to the above, after receiving composite components from C-CADD (F) NDT was carried out using the instrument (WoodPecker-632) on the composite parts of the Hansa aircraft

Design and Development of Labview based Environmental Test Chamber Controller

Abstract: Polymer composite materials are the most sought after materials for aerospace applications in view of their superior specific stiffness and specific strength properties. However, these materials are susceptible to the combined effects of temperature and humidity. Monitoring and control of these two parameters in an environmental test chamber, within a close tolerance for a stipulated duration to simulate the service conditions on the material is an essential part of qualification procedure for composites. At the Environmental Test Facility of CSIR-NAL, hitherto only data acquisition was possible through the computer, but the control activity required the operator to move physically to access the controller and provide the necessary change in inputs. The limitations have been successfully addressed by the design and implementation of a LabVIEW based software for monitoring as well as control of temperature and humidity in the environmental test chamber. This approach has eliminated the use of the existing DAQ and retransmission module hardware and further the controller itself is used as a DAQ device facilitating the control and functionalities such as data acquisition, storage, retrieval and presentation through LabVIEW software. Further, the need for physical movement of the operator to access the controller has been eliminated. In this paper, the development of a closed loop control algorithm and data acquisition protocol using LabVIEW is presented. The LabView has been used with an iTool Modbus Open Platform Communication (OPC) server for monitoring and control of temperature & humidity in the environmental test chamber. The innovative and novel controller has made the environmental conditioning process more efficient and cost effective. The accuracy achieved using the newly developed ETC is ± 0.5°C for temperature and ± 1% RH in case of humidity vis-avis the accuracy of ± 2°C and ± 3% RH, achieved with the old controller

Thermo-mechanical creep and recovery of CTBN–epoxy shape memory polymers under saline environment.

In the present study, the creep and recovery experiments of unmodified epoxy SMP and 5% carboxyl-terminated butadiene acrylonitrile (CTBN) modified epoxy SMPs were carried out after being exposed to saline environment (5% NaCl, 35 °C/98% RH). The creep results of the SMP specimens before and after exposure to saline environment, obtained through short-term tensile creep test at different temperatures (i.e., 25, 80, 103 and 120 °C) and loading conditions, were compared. Prior to exposure to saline environment, the creep strain was found to increase with increasing temperature and reached a maximum around the glass transition temperature (i.e., 103 °C). A higher creep recovery ratio was noticed in the CTBN-modified epoxy SMP particularly at high-temperature conditions. The creep strain was higher in saline environment at 25, 80 and 103 °C; however, at 120 °C both the SMPs could not withstand the applied load. The creep recovery ratio was unaffected by the saline environment in both the SMPs

CONDITIONING AND QUALIFYING A MICROWAVE - BIT (BUILT IN TEST) UNIT FOR USE IN THE TARANG SYSTEM [END USER-IAF]

The Microwave component -BIT (Built In Test) unit was subjected to CATH test in a Combined Altitude, Temperature and Humidity chamber. This unit was developed by M/s FLIC Microwaves Pvt Ltd, Hyderabad for BEL, Bangdore for use in Tarang Systems. The CATH test was done per MIL-STD 810F, Method 500.4 for acceptance by end user. While conditioning, the functional test (perform Frequency generation and Power Output measurements) was carried out by the firm and the unit was handed over to the firm

HANSA-3 aircraft series productionisation program - Damage repairs

This report brings out the support services rendered by the FRP Division to the ongoing HANSA-3 Series productionisation programme. The sub-components for the aircraft are being fabricated elsewhere, while important activities such as curing, NDT and other relevant quality aspects are being monitored by the FRP division. This report highlights the support services provided prior to qualification for HANSA-3 aircraft code - S1. No 007

Design Approach for FPGA based High Bandwidth Fibre Channel Analyser for Aerospace Application

Fibre Channel (FC) data transmission protocols are widely used as an interconnecting protocol to cater for the requirement of high-speed data transmission. FC has unique features like high bandwidth, strong anti-interference, flexible topology, distance insensitiveness and low latency. The highspeed, high reliability and low latency of FC communication protocol offers a promising solution for communication protocol in avionics environment. The video / data transmission system performance being critical in aerospace applications, verifying the data flow in the network is vital in order to prevent Hazardous Misleading Information being displayed to the pilot and endangering safety of flight. This paper puts forth a design approach for a receiver module of a Field Programmable Gate Array (FPGA) based high bandwidth Fiber Channel Analyser (FCA). The proposed design is to be implemented using Xilinx Spartan-6 FPGA SP605 evaluation board. The receiver module design addresses the requirements of transmission of soft real time video with resolution (VGA) and link speed with the incorporation of ethernet interface. The concept of developing a high bandwidth FCA for enhanced speed and quality of data, audio and video transmission in avionics system is critical and need of the hour. The outcome of such an effort can be utilized for multiple aerospace applications