Space
Contributing Space Sector with World Class Technology

India’s economic progress has made its space programs more visible and active as the country aims for greater self-reliance in space technology in near future. Captronic Systems is completely committed to this mission and offers test and measurement systems, built on world class technology, designed, and developed specifically for individual space programs and research requirements.

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What Makes Us Different?

Associated with all major Indian Space Programs

In-depth understanding of complex requirements

 

 

Superlative Quality Systems

Leveraging Skilled Workforce

Sector Categories

Captronic Systems is completely committed to ISRO’s mission of harnessing space technology for national development, while pursuing space science research and planetary exploration. In tight synchronization with various space projects Captronic Systems offers test systems for Research/Modeling, Design Simulation, Verification/Validation, Integration and Production.

Hardware in Loop Simulation

Automated Test Equipment

Data Acquisition Systems

Hardware in Loop Simulation (HILS)

CUSCE Checkout System

The Cryo Upper Stage Control Electronics checkout system is used for the testing and validation of the CUSCE package. The communication between checkout and control electronics package is using MIL 1553 standards. The checkout acts as the bus controller and the CUSCE will be configured as a remote terminal.

Various tests conducted include Protocol Tests, RT Response Tests, Error Injection Test, Load Test, RAM Check, Input Sensor Check, EGC Linearity Check, Drive MRC/AVR Actuator, Frequency Response Test, Step Response Test, Calibration of EGC pot, Calibration of RTD’s etc. 

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Frequency Response Analysis of Control Electronics

This FRA system provides versatile, accurate measurement of gain and phase response with respect to frequency across multiple response channels.

Frequency Response Analysis System provides useful insights into stability and performance characteristics of control electronics.

Different display panels like Gain vs. Frequency Plotter, Phase vs. Frequency Plotter, Response Table, Result Window are available along with Normal Sweep Configuration, Custom Sweep Configuration, Generator Mode etc. Software is extremely user friendly and the system is modular in nature to accommodate future requirements.

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Inertial guidance unit test system

LIRAP (Laser Gyro based Inertial Referencing and Accelerometer Package)test system is conceived as HILS system for the evaluation of LIRAP system in all phases of development and production i.e. During designer level test and evaluation (T&E), Package level T&E and integrated level T&E with other satellite systems.

The checkout shall support the tests such as drift tests, rate test, multi-position tests, power supply variation tests, 1553B link tests etc. Checkout shall automate the AMS operation required for tests such as rate test, multi position test and drift test.

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More Projects under Space HILS.

Solar Array Drive Assembly Test System

The SADA checkout HILS system has both hardware and software segments to power and operate the sub systems to generate Tele-Commands, TM/AOCS, Angle Position readout processing, evaluate the subsystem performance, safety interlocks and to generate test results in report form.

Based on the NI cRIO architecture, the system can carry out different tests such as Preliminary tests, Complete Functional Tests, Thermo-vacuum Test Setup, Slip Ring noise, friction measurements, continuity ,isolation ,insulation of electronics etc.

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Automated Test Equipment

Burn Rate Evaluation System

Burn Rate Evaluation System performs Acoustic Emission Test and Ultrasonic Test. The Acoustic Emission Test is used to determine the burn time of a solid propellant strand of known length under a desired pressure in a combustion chamber.  

The Ultrasonic Test is used to determine the instantaneous burn rate of the solid propellant strand of known initial length. This is carried using the ultrasonic method used is the ultrasonic Pulse-Echo technique.

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Continuity Tester

It is an electrical test equipment used to determine if an electrical path can be established between two points; or if a path exists between two points, and if it exists, does the value fall under pre-defined limits.  This system is capable of measuring resistance between 350 pins with a measurement speed of 5 measurements per second. System consists of NI matrix modules and a 7½-Digit DMM card capable of 1.8MS/second.

System is designed keeping all customer requirements in mind with maximum scalability and modularity. Users have the freedom to configure custom harness and custom test criteria. System also logs all test data into a database for future reference and tracking.

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Semiconductor Test System

Semiconductor Test Systems is used for testing of military grade electronics for research and development in space applications. It is a state of the art mixed signal tester system. It tests mixed signal semiconductor devices such as ADC and DAC, both digital and analog components. 

The system provides features like adding the IC details, configuring the tests, sequencing the tests and generating reports in different formats. Parameters like Offset error, Gain error, INL, DNL, Power Measurements etc. can be made. New Device under tests can be added and tested making the system completely scalable.

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More Projects under Space ATE 

Control Electronics Checkout System

It is an unique ATE which can do multiple testings like, testing of Servo cards used in Rocket Liquid engine CE(Control Electronics), Designer level testing of Integrated CE packages and Flight acceptance testing (FAT) of Rocket Liquid Engine Injection valves & Actuators.

The CE checkout system consists of a PXI based controller with PXI Input – Output modules, Relay Matrix, Relay Multiplexers assembled on a PXI chassis, External Power supplies and other equipment like Digital Multimeter, DC source etc. The PXI modules will communicate to the CEs & Actuators through checkout interface  

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Actuator Test System

This PXI based ATE is used for testing of high power actuators and its control electronics.The test includes sine response,frequency response,step response ,ramp response,linearity tests etc. It is a unique combination of Frequency Response Analyzer, Data Acquisition System and Fault Insertion Unit.

Apart from this functional tests the failure mode tests like LVDT and other sensor failure simulation,power supply failure,drive failure, compensator failure are simulated. The system is used for total control system characterization and compensator verification used in the electronics.

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Data Acquisition & Control Systems

Nozzle Test System

The main objectives of Nozzle Test Facility is to characterize various nozzle contours, DUT is instrumented by different types of sensors. A data acquisition system located in the field acquires signals from various sensors and data are stored locally as well as transferred to the control room in real time.

The DAQ receives digital inputs from the Facility automation PLC as trigger signals for starting the data acquisition. The system is designed to have client and server architecture. On field data is acquired on the 2 server systems located on field and transmitted over TCP/IP to the Control room for processing and backup storage.

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DAQ for Engine Combustion Research

The Data acquisition system acquires Different types of process parameters such as temperature, pressure, flow etc. they are also logged and displayed in graphical or tabular formats.

The system consists of two display nodes, data processing node, server, controller PC with data acquisition system and Ethernet switch. It uses a combination of NI PXI and cRIO form factors. Various Alarms, Sensor ranges, Filter, calibration settings etc. can be configured into the system. User can perform various analyses like FFT on the acquired data.

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Portable Parachute Data logger

The system is designed & developed with DC powered standalone DAQ system for acquiring pressure, vibration and temperature signals during the vertical descent of the CREW module using parachute which is done as a part of Atmospheric Reentry Experiment.

After the drop from a particular height, during the descent parachute opens and a trigger to start Data acquisition is enabled. The required data is acquired for around 180 seconds till the crew module reaches the ground. System is rugged, standalone, battery powered, compact for acquiring and storing real time data during the critical testing part of Rentry experiment.

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More Projects under Space DAS.

Water Calibration System

The Calibration System includes the monitoring of pressure at different points of the tank containing water (Inlet and Outlet). The water fed to the RCS is using outlet valves mostly solenoid valves. These solenoid valves are to be operated in certain sequence /timing based on the sequence configured.

Operation of solenoid valves is accompanied with the monitoring of current drawn by the same. The system also monitors the microswitch status 8 numbers reserved for it. The software contains features such as Calibration, automatic test sequence configurator, test panel and offline data analysis.

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Turbo Pump Testing System

The turbo pump DAQ & Control System is used for carrying performance tests of Seal and Bearing under cryogenic conditions. The test setup will help to analyze and study the Seal / Bearing. The test material will be placed in a test rig where the test fluid will be circulated. During the test duration that lasts close to one hour the system and test parameters are acquired and logged. The acquired parameters include temperature, Pressure, Flow and others. The test rig is driven by a motor whose speed is controlled by the system in an open/close loop.

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Portable Parachute Data logger

The system is designed & developed with DC powered standalone DAQ system for acquiring pressure, vibration and temperature signals during the vertical descent of the CREW module using parachute which is done as a part of Atmospheric Reentry Experiment.

After the drop from a particular height, during the descent parachute opens and a trigger to start Data acquisition is enabled. The required data is acquired for around 180 seconds till the crew module reaches the ground. System is rugged, standalone, battery powered, compact for acquiring and storing real time data during the critical testing part of Rentry experiment.

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System Gallery

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