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Wax Based Collapsible Mandrel

Solid propellants are widely used for rockets and missiles.
Complex grain geometry requires propellant machining.
Machining is a slow, costly, hazardous and dangerous process.
Wax mandrel - simple design, non hazardous, can be casted/machined to any shape, reduces propellant realisation time and manufacturing cost.
Few hours of wax decoring time compared to up to 30 days of machining time.

Capability

Mandrel of up to 2 meters in length and 300 mm in diameter have been realised.
Propellant quantity of up to 55 kg has been casted using wax mandrel.

Wax Based Hybrid Rocket

Combination of solid and liquid rocket.
Liquid oxidiser, solid fuel.
Specific Impulse comparable to LOX-RP1 engine.
Less complex than a liquid rocket.
More safe and flexible than a solid rocket.
Sea level specific impulse of 300 s achieved.
Can be made an earth storable system.

Capability

Grains up to 1.3 m in length and 300 mm in diameter have been realised.
Hybrid rocket up to 1 kN sea level thrust has been tested.

60 bar pressure and 1 kN thrust

60 bar pressure and 1.5 kN thrust

Low Temperature Gas Generator

Gas generator with temperatures as low as 150 ̊C for various defence and aerospace applications.
Simpler design.
Standalone system with no need of system like compressor or gas bottles.

Applications

Inflatable Decoys
- Rapid deployment.
- Standalone system.
UAV landing
- Soft landing of fixed wing UAVs.
- No need of runway.
- Operational capability in all terrain.
Mid air restart of gas turbine engines.
Starting of small gas turbine engines which is currently done using compressed air.
Starting of turbo-pump system of a liquid rocket.
Recovery of test torpedoes.

60 lit Kevlar bag filling test for VSSC (ISRO)

Impulse Thruster

Ideal for short duration high thrust pulses.
Propellant with high density of 2100 kg/m3.
Burn rate - 100 mm/s @ 80 bar.

Applications

For stability during initial launch phase of missile.
High manoeuvrability during endgame of air defence missile.

Capability

Developed a thruster with an average thrust of 5 kgf and duration of 0.1 second.
Thruster delivers a total impulse of 5 Ns.

Thruster body.jpg

HTPB Based Propellant

Solid Propellant

Both aluminised and non-aluminised HTPB based composite propellant.
Aluminised propellant – High density, High Isp (240-245 s).
Non-aluminised propellant – Reduced smoke, Isp (220-225 s).
High burn rate of up to 18 mm/s at 70 bar.

Fuel-rich Propellant

Low oxidiser loading, high metal loading.
Increased ramjet Isp.
High burn rate of around 8 mm/s at 70 bar.

Wired Propellant

Metal wire inclusion along the length in HTPB based propellant.
Burn rate augmentation of 4-5 times compared to base propellant burn rate.
Possibility of making port burning into end burning grain (100% volumetric loading.

wired propellant1.jpg

Wear Additive Liner

To reduce barrel wear of artillery gun.
With our wax, operating temperature of over 65 ̊C is possible.
Increases barrel life/rate of fire.
More rounds can be fired from the same gun.
Half the cost of current liner.
Combines tin foil and liner into 1 part – ease in assembly.

Aluminum Based Igniter

Alternate to high cost BKNO3 igniter.
No compromise on the igniter performance.
Density, burn rate, pressure index and crushing load similar to BKNO3 igniter.
Calorific value 20% higher than BKNO3 igniter.
3-4 times lower cost than BKNO3.
No change in performance up on isothermal ageing at 60 ̊C for 25 days.

Gas Generator Cartridge

For separation bolts used in missiles and launch vehicles.
Reduced shock load compared to pyro cartridge.
Shock reduction of up to 8 times compared to pyro cartridge has been achieved.
Reduced structural weight.
GG cartridge externally same as that of a pyro cartridge, same thread and electrical connections.
No change in current system for accommodating GG cartridge.

Separation Bolt test using GG cartridge at ASL (DRDO), Hyderabad

Wing deployment using GG cartridge at JSR Dynamics, Nagpur

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