Residency Status: US Citizen
1. Worked on thermal design and analysis of geosynchronous satellites of Indian Space Program at ISRO for 15 years as senior thermal scientist.
2. Thermal system design of high power density components of geo-synchronous satellites.
3. Strong programming experience in FORTRAN and C on UNIX based workstation such as IBM RS6000. Worked on various CAD packages such as AutoCAD, SDRC-IDEAS.
4. Thermal analysis of some of the critical components of the spacecraft for both transfer and in-orbit conditions.
5. Thermal control design using MLI, OSR, Al-blocks and heat pipes.
6. Thermal control issues like optical property degradation of materials such as OSR, MLI, low emittance tape, black and white paints have been studied.
7. Experience in thermal vacuum testing of satellites: Package thermal qualification level testing (hot and cold soak testing and thermal cycling) and on-orbit testing.
8. Transfer orbit as well as on-orbit temperature control of geo-synchronous satellite.
9. Post launch thermal analysis: thermal model correction.
10. As a part of my Ph.D. thesis, extensive research has been conducted to develop techniques and algorithms to optimize the design of thermal control system of the spacecraft. This technique is found to be highly useful in improving the thermal performance of the geo-synchronous satellites. Results of these studies are published in several reputed international journals.
11. Authored 5 technical reports (Department of Space, Government of India).
12. Authored 4 papers. These are published in the Journal of Spacecraft and Rockets under the publication of American Institute of Aeronautics and Astronautics (AIAA), U.S.A. and Journal of Aerospace Engineering, U.K.
13. Acted as a referee for the Journal of Aerospace Engineering, U.K.
Specialization: Optimization of thermal systems design of spacecraft components using sensitivity analysis. Expert in analysis and design of thermal control system for the electronic components of spacecraft systemsuch as, TWTA, Battery, Shunt regulator, Solar panel etc. Expert in developing Mathematical models for any thermal control system. Expert in the topics such as Calculus, Differential equations, Numerical analysis, Linear algebra.
1. Suresha, S., Gupta S.C., and Katti, R.A, "Thermal Sensitivity Analysis of Spacecraft Battery", Journal of Spacecraft and Rockets,AIAA, Vol. 34, No.3, May-June 1997, pp.384-390.
2. Suresha, S., Gupta S.C., "Calculation of Sensitivities in Thermal Control Systems with Nonlinear inequality Constraints", Journal of Spacecraft and Rockets, AIAA, Vol.35, No. 4, July-August 1998, pp.552-558.
3. "Effect of discontinuous heat loads during solar eclipse on transient thermal sensitivity analysis", AIAA, Vol. 36, No.6, November-December 1999, pp. 916- 918.
4. "Thermal Sensitivity Analysis of a 22N Bipropellant Thruster in Spacecraft", Proc Inst Mech Engs, Vol 213 part G, pp.321-335.
BAE Systems (TAC Contractor), Santa Clara, CA
Worked as a Vehicle software Engineer. Job involved the electrical system integration and testing of combat vehicles.
Functionality testing of RTD Sensors:
RTD sensors were used to activate AFES system in the vehicle. Tested the sensors both in automatic and manual mode. In automatic mode, sensor needs to give feed back to the control unit called RIU depending upon its temperature co-efficient resistance. Subsequently RIU system has to drive the AFES.
Firmware uploading on RIU and other LRUs:
Uploaded the firmwares on different LRUs (Line replacement units) using respective hardware application tools through Ethernet/RS232 communication ports. Participated in different system functionality testing relating to low and high voltage systems. Good knowledge of propulsion system of the vehicle. In-depth knowledge on network communication testing tools such as CANoe. Debugging Ethernet and CAN communication issues. Good knowledge on Hybrid Electric Drive.
Uploading and downloading of firmwares on the system using RS32 and Gigabit etthernet communication. Management of system configuration files developed in C++.
Santa Clara University, Santa Clara, CA (2003-2008)
Specializing in logic design and Digital Signal Processing. Design and Analysis of combinational as well as sequential logic circuits have been studied in depth. Initially, simple combinational logic circuits have been implemented using Xilinx Spartan FPGA. Subsequently, ALU (Adder/Subtractor) and Comparator designs were realized also with FPGA.
Hardware Description Language such as Verilog has been used to capture the schematic. Studied ASIC design philosophy and hardware verification procedures. Also the Digital Signal Processing techniques have been studying with a more emphasize on filtering design. Some of the analog circuits have been analyzed for their frequency response using SPICE tool.
Protnov Computer School,Mountain View, CA (2001 – 2002)
Worked on Software QA tests and test automation projects using SILK.
Indian Space Research Organization, India (1985-2000)
Worked in ISRO as a Project Manager for GSAT (geo-synchronous satellites) project. During the 15 years of career in ISRO, I worked on many different spacecraft projects as a Scientist, technical consultant and Project Manager.
Following electronic components have been designed for their temperatures for both transfer as well as in-orbit conditions:
Shunt regulator, SSPA, TWTA, Antenna, Solar Panel and house keeping packages of INSAT-2E and GSAT-2 satellite of Indian space program.
Each and every component of the spacecraft has to be maintained under certain temperature regimes during all the phases of the spacecraft such as transfer orbit and in-orbit conditions. To ensure this thermal control system design is envisaged.
Design of thermal control system for the spacecraft requires the development of mathematical model. Heat transfer in spacecraft systems is dominated by conduction and radiation modes of heat transfer. Mathematical model is developed using lumped parameter approach in conjunction with finite difference technique. Both coarse and detailed mathematical models have been developed depending on the problem such as panel level or package level analysis. Both steady state as well as transient models has been developed. Mathematical model for steady state results in system of algebraic equations and system of differential equations for transient problems. Both these types of equations are solved using numerical approach. Temperatures prediction has been done for transfer orbit as well as on-orbit conditions. Subsequently, temperatures are analyzed to design optimal radiator areas on the satellite equipment panel.
Design of Thermal Control System for High Power Density Packages
a) Development of Thermal Mathematical model
b) Calculation of Steady state and Transient Temperatures :
Design of thermal control system for high power density packages of the spacecraft such as Traveling Wave Tube Amplifiers (TWTA) and Solid State Power Amplifiers(SSPA) is an uphill task as all these components are to be maintained within a narrow temperature range and subjected to large amount of internal heat dissipation and external heat load boundary. In such situation, thermal management of these components has become an important task. In general thermal system design is envisaged with the help of thermal control systems such as heat pipes, Al- embedded blocks as heat sinks, OSR, MLI, selective tapes etc. In this particular situation, heat pipes, MLI and OSR are used to control the temperature of TWTAs and SSPAs. Heat pipe network has been embedded inside the equipment panel on which power density components are mounted. Surface of the equipment panel facing space is covered with MLI and OSR. Appropriate MLI and OSR sizing have been done to provide optimal radiator area. Surface facing the spacecraft is painted black to have more radiation coupling with spacecraft. Design of these thermal control elements is based on the thermal analysis under consideration. Thermal analysis of packages like these requires a usage of CAD tool such as I-DEAS. I-DEAS is generally available on UNIX workstations such as SGI, IBM and SUN. Simulation component of I-DEAS has been extensively used in this context.
Master modeler has been used to simulate SSPAs and TWTAs. These components are of different shapes and sizes. Initially sub-parts were created using primitive parts such as sphere, cube, cylinder etc. Heat pipe modeling was also done appropriately. Subsequently all these parts were modified, dimensioned and assembled together to form an object. Once all the objects are created they are stored in library.
Meshing module has been used to carry out solid mesh or surface mesh on the objects created. Both manual and mapped mesh has been used. Meshing results in the creation of different finite elements. These elements are grouped under different names. Finally all these objects are placed on the spacecraft panel which is also modeled and meshed in a similar fashion.
Thermal analysis module is used to simulate conduction couplings, radiation couplings, and orbital heating for thermal control elements such as heat pipes, MLI, heat sinks and OSR.
Finally Temperature prediction has been done using I-DEAS TMG. Both steady-state as well as transient temperatures were calculated from the above simulation model for both transfer as well as in-orbit conditions. Subsequently, the temperatures of all the components are analyzed to design optimal radiator areas for the components.
Development of Interface Program between I-DEAS and Harvard Graphics
Interface has been developed between I-DEAS and Harvard Graphics using 'C'. This program converts the temperature of I-DEAS stored in .unv file and TEMPF file to a format suitable for X-Y Plot using Harvard Graphics. This program is used for the generation of customized time v/s temperature data.
Thermal Vacuum Testing for Satellites
Important packages of the satellites were tested for hot and cold soak and thermal cycling conditions. Also, the thermal performance test has been done to verify the thermal mathematical model. Thermal mathematical model correction has been done based on the analysis of thermal performance test.
Post-Launch Thermal Analysis of Satellites
On-orbit temperatures of the packages are compared with the predicted temperatures and subsequently, the thermal mathematical model correction has been done with the help of thermal sensitivity studies.
Santa Clara University, Santa Clara, CA
MS in Electrical Engineering (March. 2008)
Graduate Certificate Program in Fundamental of Electrical Engg. (Dec. 2004)
Indian Institute of Science
Ph.D in Applied Mathematics (Sept. 1999)
Annamalai University (Sept. 1991)
MS in Physics (Electronics)
Registering is the only way of posting vacancies and obtaining contact details of candidates in our CV database.
All it takes is a few minutes and a credit card (Visa or American Express). To sign-up to this service, simply click on the Register link and fill in the form. You will then have instant access to our system after on-line payment where you will be able to complete the transaction in either US Dollars, UK Pounds or Euros.
All online credit/debit card transitions are handled through our secure third party payment processors at WorldPay. Worldpay are part of The Royal Bank of Scotland Group, the 5th biggest banking group in the world, WorldPay payment solutions are trusted by thousands of businesses, big and small worldwide.
Pricing starts at €450 (approx £400 or US$500 - use the convert tool for an exact conversion) for one month unlimited job postings and unlimited CV database access (for one user), with package discounts available if you have more permanent recruiting needs. For example, a Gold subscription will give you unlimited jobs posting and unlimited CV database access for one year at just over €250 per month!
2018 Pricing Structure (excluding VAT):
|1 month - Discovery||450 euros||convert|
|3 months - Bronze||1150 euros||convert|
|6 months - Silver||1950 euros||convert|
|12 months - Gold||3200 euros||convert|
If online payment is not convenient, give us a call at +33(0)622757477 or send us an email at firstname.lastname@example.org. We will set up an account for you and invoice you. Note that you can also pay through PayPal.
Please note that the posting of academic positions is free of charge. All you need to do is email us your job description and we will post it for you.
Spacelinks is based in France so the following European Union regulations regarding electronic commerce apply:
- if your business is located outside the EU, VAT does not apply to you
- if your business is located in France, you will be charged a 20% VAT
- if your business is located in the EU and you don't have a valid VAT registration number, you will be charged a 20% VAT
- if your business is located in the EU and you do have a valid VAT registration number, you won't be charged VAT provided you give us your VAT number (mandatory for invoicing)
For sales enquiries and general information, you can call us on +33(0)622757477.
Support is available Mon-Fri on +33(0)622757477 or via email. Out-of-hours support is provided only via email.
Please also note that we are located in France. Our normal office hours are 09:00 to 18:00 Monday to Friday. France timezone is GMT+1.
We are very serious about our job seekers privacy so only legitimate recruiters and employers are eligible for a recruiter account. All subscriptions requests will be manually approved and recruiter accounts constantly monitored. Users who enter inaccurate or incomplete information will not gain access to post jobs or search resumes. Sharing of login details with a third party will result in the suspension of the recruiter's account with no subscription refund.
Recruitment agencies are only eligible for a Gold package and recruitment agencies recruiting for companies already using Space Careers will not be accepted.
To ensure you are approved, please include the following on your application:
* The website address of your Company. Under construction websites will be rejected.
* Email - Must end in @yourcompany.com. Applications using free email accounts such as Hotmail, Yahoo or Gmail will be rejected.
Individual exceptions can be made on a case by case basis by emailing email@example.com. Accounts found not to be in compliance will be deleted.