Indian Hypersonic Technology thread.

[ganimi kawa]

Ok guys, first of all sorry for the extreme delay in writing this post about HSTDV and it's progress so far (esp. the scramjet testing.)

I could not keep my promise courtesy my HoD, may he miss all world cup matches !


I've decided to start a different thread as we have more than 2 projects in hypersonics and it will be a good exercise to pool all the available data together.


Anyways, for those of you who do not know anything about the project, here is a brief intro of the project (quoting AWST article-11/05/2007, page 65 and a paper by K. P. J. Reddy,D o Aero Eng,IISc for most of the details.)




HSTDV


The project

*Hypersonic Technology Demonstrator Vehicle (HSTDV) is an unmanned scramjet demonstration aircraft for hypersonic flight (Mach 6.5).

*It is intended to attain autonomous scramjet flight for 20 sec., using a solid rocket launch booster. The eventual target is to reach Mach 6.5 at an altitude of 32.5 km.



* Objectives of the program are--

1.proving the design and performance of the scramjet engine

2.Proving associated technology like---aerodynamic design, aero-thermal design, materials and hot structures at hypersonic flight Mach numbers.



* The HSTDV mission-
It involves launching the hypersonic air-breathing vehicle
called Cruise Vehicle (CV) to a Mach number of 6.5 at an
altitude of 30-35 km using a rocket launch vehicle. A single
scramjet engine burning kerosene fuel powers the cruise vehicle
for a sustained operation of 20 second duration.

The details of the HSTDV design and flight test are given in this figure.

Compare this with the photo of the actual model...

Comin up, the structure of HSTDV........

 

[ganimi kawa]

STRUCTURE


Please refer to this diagram (neglect the numbers!) and the earlier pics.

1.The 1-metric-ton, 5.6-meter (18-ft.)-long air vehicle under construction features a flattened octagonal cross section with mid-body stub-wings and raked tail fins and a 3.7-meter rectangular section air intake.

2.The scramjet engine is located under the mid-body, with the aftbody serving as part of the exhaust nozzle.


3.Two parallel fences in the forebody are meant to reduce spillage and increase thrust. Part span flaps are provided at the trailing edge of the wings for roll control.

4.A deflectable nozzle cowl at the combustor end can deflect up to 25 deg. to ensure satisfactory performance during power-off and power-on phases.

5.Materials---Surfaces of the airframe’s bottom, wings and tail are made of titanium alloy, while aluminum alloy comprises the top surface. The inner surface of the double-wall engine is niobium alloy and the outer surface is nimonic alloy.

6.Propulsion---a.Two types of combustor—strut-based and ramp-cavity-based were under evaluation, and eventually strut based version was chosen (more on this later)
b.The nozzle features a cowl extension and fence to improve vehicle performance.
c.The solid booster (for achieving initial velocity), under construction, is a derivative of the S9 that powers India’s Agni ballistic missile and PSLV launch vehicle.


Coming up, details of the successful scramjet round testing at DRDL.

 

[ganimi kawa]

SUCCESSFUL SCRAMJET COMBUSTOR TEST --


(Ref-- Design, Development and Testing of Scramjet Combustor for HSTDV Mission of 20 s Duration by C. Chandrasekhar,DRDL, Hyderabad)



A scramjet (supersonic combustion ramjet) is a variant of a ramjet airbreathing combustion jet engine in which the combustion process takes place in supersonic airflow. As in ramjets, a scramjet relies on high vehicle speed to forcefully compress and decelerate the incoming air before combustion (hence ramjet), but whereas a ramjet decelerates the air to subsonic velocities before combustion, airflow in a scramjet is supersonic throughout the entire engine.







*Steps taken in developing the Scramjet combustor for the HSTDV.


1. Successful Development of Vitiated Air heater Facility for Testing
Scramjet Combustor.

*To evaluate the performance of the scramjet combustor
experimentally, the ground based test facility is required
which can simulate the test gas at the desired flight conditions.

* A gas turbine combustor based vitiated air heater was
developed by utilising an existing GTX combustor
and commissioned.

*This has been a work horse for conducting a series of static tests of scramjet combustor.






2. DESIGN AND DEVELOPMENT OF STRUT BASED SCRAMJET COMBUSTOR

Scramjet combustor design and realisation is one of
the complex tasks of hypersonic air-breathing vehicle. As
it is a contemporary area of work, information is classified
and not available in open literature.


a.The scramjet combustor was constructed using INCO-718 and Nimonic C-263 materials.

b. Also two sets of fuel injection struts; one set using INCO-718 alloy and the second set using Nimonic C-263 alloy with Yttria Stabilised Zirconia (YSZ) coating were constructed in coordination with DOE
and outside agencies.

Coming up, details of the test and overall achievements in developing the scramjet.

 

[Firemaster]

SUCCESSFUL SCRAMJET COMBUSTOR TEST --


(Ref-- Design, Development and Testing of Scramjet Combustor for HSTDV Mission of 20 s Duration by C. Chandrasekhar,DRDL, Hyderabad)



A scramjet (supersonic combustion ramjet) is a variant of a ramjet airbreathing combustion jet engine in which the combustion process takes place in supersonic airflow. As in ramjets, a scramjet relies on high vehicle speed to forcefully compress and decelerate the incoming air before combustion (hence ramjet), but whereas a ramjet decelerates the air to subsonic velocities before combustion, airflow in a scramjet is supersonic throughout the entire engine.







*Steps taken in developing the Scramjet combustor for the HSTDV.


1. Successful Development of Vitiated Air heater Facility for Testing
Scramjet Combustor.

*To evaluate the performance of the scramjet combustor
experimentally, the ground based test facility is required
which can simulate the test gas at the desired flight conditions.

* A gas turbine combustor based vitiated air heater was
developed by utilising an existing GTX combustor
and commissioned.

*This has been a work horse for conducting a series of static tests of scramjet combustor.






2. DESIGN AND DEVELOPMENT OF STRUT BASED SCRAMJET COMBUSTOR

Scramjet combustor design and realisation is one of
the complex tasks of hypersonic air-breathing vehicle. As
it is a contemporary area of work, information is classified
and not available in open literature.


a.The scramjet combustor was constructed using INCO-718 and Nimonic C-263 materials.

b. Also two sets of fuel injection struts; one set using INCO-718 alloy and the second set using Nimonic C-263 alloy with Yttria Stabilised Zirconia (YSZ) coating were constructed in coordination with DOE
and outside agencies.

Coming up, details of the test and overall achievements in developing the scramjet.

an offtopic question , has india developed single crystal nickel super alloy blades required for gasturbine engines?

and if drdo has developed this technology, is it upto or on par with world class standards ?

and suppose if we have to develop an engine in 150kN class then the blades for 90kN engine would work or we have to develop different and more tougher blades.
please clarify me on this questions. thanks in advance.

much of hope from kinetic ,ganimi kava,indian army,spark,xinix,connanxlrc1000

 

[jayron]

Thanks for the info Ganimi. Some of the image links seem to be broken. Can you please repost them?

 

[GLOBAL HAWK]

Thanks for the info Ganimi. Some of the image links seem to be broken. Can you please repost them?

Yeah i see only 2