PROPELLANTS
NITRO CELLULOSE PROPELLANT FOR CARTRIDGES
Type Shape Of Propellant Type Of Cartridge Charge Weight (t/mil.rd.) Maximum Pressure Muzzle Velocity Bulk Density (gm/lit)
NC 1140 Monotubular 7.62 mm 3 331 MPa 826 m/Sec 800
NC 1058 Monotubular 30 mm ADEN 50 19 tsi 2560 f/Sec 895
NC 1066 Monotubular 40 mm L-70 500 403 MPa 1000 m/Sec 920
NC 688 Solid Grain 9 mm PISTOL 0.5 193 MPa 396 m/sec 600
 
PROPELLANTS FOR SPORTING
Ammunition System Charge Weight Pressure Muzzle Velocity
RF Ball 0.22" (SPA-I) 65 mg Not recorded 305 ± 23 m/s
SA 0.380" Ball Rev. (SPA-II) 500 ± 30 mg
(for 5.56 mm blank SAA)
Mean not >193.0 396 ± 15 m/s
(for 9mm SAA)
SA 12 Bore Cartg. (SPA-III) 1.608 gm Max not > 208.44 (for 9mm SAA) 1045 ± 25 ft/s
 
BALL POWDER PROPELLANT FOR 7.62 MM & 5.56 MM CARTRIDGES
Parameters 7.62 mm 5.56 mm
NC : NG 88 : 10 88 : 10
Size Micron 710 - 425 610 - 500
Shape Spherical Spheroidal
Flash Reducer As Reqd As Reqd
Grains Graphited Graphited
NC-NG BASED ROCKET PROPELLANTS
Size Shape Charge Weight (Kg) Maximum Pressure Max Thrust (Kg/Cm2)
68 mm Monotubular Star Centred Inhibited On Outer Surface 1.5 Kg/Rd. 285 500 at -40°C
750 at +66°C
122 mm GRAD Monotubular With One Front and One Rear Grain 20 Kg/Set 10.6 Mpa 5500
 
NC & NG DOUBLE BASE BALLISTITE PROPELLANTS
Type Type Of Cartridge Charge Weight (gm/rd.) Maximum Pressure (MPa) Muzzle Velocity m/sec Bulk Density (gm/lit)
NGB-051 81 mm Mortar (Primary) 7.6 10 70 665
NGB-221 81 mm Mortar (Secondary) 108 59 295 685
NGB-011 120 mm Mortar (Primary) 78 20 119 710
NGB-241 120 mm Mortar (Secondary) 600 101 335 735
NGB-204 84 mm Carl Gustaf 360 680 Bar 305 --
 

105 mm CARTRIDGE

Ammunition PROPELLANT SCM V OF A m/s P MEAN MPa P MAX MPa RANGE Km
105 mm IFG NC N017 +N/S
123-043 +N/S
164-048
CH.1-384 g
CH.2-228 g
CH.3-280 g
CH.4-596 g
CH.5-802 g
230.40

300.30

372.40

477.80

595.80
-

-

142-
162
213-
227
323-346
-

-

not > 170
not > 235
not >
354
5.5

7.1

9.4

11.9

15.0
105 mm IFG SC NQ/M 054 3.135 Kg 703.1 not > 322.0 not > 330.0 17
105 mm TK HESH NQ/S 156-056 2.382 Kg 731.82 160.6-172.9 not > 185.3 8
105 mm DS/T NQ/M 028 4.060 Kg1544.1 370-388 not > 397 3.5
106 mm RCL T-28 3.610 Kg 506.6 not > 77.8 not > 81 3.11
 
LARGER CARTRIDGES

Ammunition

PROPELLANT SCM V OF A m/s P MEAN MPa P MAX MPa

RANGE Km

130 mm FVC NQ/S251- 084 + NQ/M254 CH.1-11.455 Kg

CH.FULL-11.155+ 2.215 Kg
822


943.2
255


355-370
-


not > 389

22.44


27.49

130 mm RVC AP043+AP/S 376-117

CH.4- 1000 +3067 g

CH.3-1000+ 3067+ 1294 g

CH.2- 1000+ 3067+ 1294+ 1256 g

528.2


622.8


708.7

not<120


268-284
not >131

-


not > 304
13.36


16.40


19.13
 
Propellant for 73 mm Heat AMMN
CHEMICAL COMPOSITION
1. NC% 59 ± 1.0
2. NG% 30.0 ± 0.5
3. DNT% 9.0 ± 0.5
4. Carbamite 2.0 ± 0.2
5. Mono basic Lead Stearate 2.0 ± 0.5
6. Chalk 0.35 ± 0.05
7. Pot. Sulphate 0.5 ± 0.05
8. Carbon Black 0.5 ± 0.05
9. Zinc Stearate 0.08
10. Candililla Wax 0.075
11. Volatile Matter (max) 0.5
12. Ash Content (Max) 0.5
(Sl. No. 5 to 10 added on 100 parts of basic composition)
 
a) Length in mm 216 ± 0.2
b) External dia in mm 43 ± 0.5
c) Internal dia in mm i) 10.5 ± 0.6
ii) 12 (igniter end)
d) Fuze hole dia in mm 12.0 ± 0.2
e) Grain hole dia in mm 10.5 ± 0.6
f) Perpendicular hole dia to centre axis helically 4.0 mm
g) Hole position 36 mm distance from each hole by maintaining 72 deg
h) Eccentricity To be checked visually
i) w + b i) Fuze hole in mm 15.15 to 15.82
ii) Prop hole in mm 15.7 to 16.8
j) Density 1.6
k) Cal Val 928 ± 15
 
BALLISTIC PARAMETERS
1. Maximum Pressure (Pmax) kg/cm2 250
2. Maximum Thrust (Fmax) kgf 425
3. Ignition delay (Milli second) max 50
4. AV Pressure P av kg/cm2 max 150
5. AV Thrust F av kgf, max 250
6. Burning time T (10%) second 0.44 ± 0.03
7. Total impulse (F dt 10%) kg/sec min 100
 
SB PROPELLANTS
SB PROPELLANT, HEPTATUBULAR, FOR 30 MM NAVAL AMMUNITION
Ballistics
Velocity of adjustment at 27º C 1076 m/sec
MD in MV (10 RD Series) 6.0 m/sec
AC Mean pressure 360-375 MPa at 27ºC
Single RD pressure at 27º C ≤ 385 MPa
Single RD pressure at 55º C ≤ 410 MPa
 
SB PROPELLANT, HEPTATUBULAR, FOR 23 mm GHASHA AMMUNITION
Ballistics
Average Muzzle Velocity 720 ± 10 m/sec
Mean Pressure 3000 Kg/cm²
 
SB PROPELLANT FOR KNOCKOUT ENGINE CHARGE FOR KONKURS MISSILE
Propellant is tubular with central grain and peripheral grain
Charge Mass 670 gm
Central grains 180 gm
Peripheral Grain 500 gm
Velocity 64 m/sec (min)
Pressure 425 kg/cm² (max)
 
SB PROPELLANT CHARGE M4A2 IN WHITE BAG, CYLINDRICAL AND PERFORATED PROPELLANT GRAIN USED IN 155 MM BOFORS HOWITZER GUN
Ballistic Requirements
Pressure
P mean 218 Mpa
P average 153 to 190 Mpa
 
Muzzle Velocity
Zone MV
3 274 m/s
4 347 m/s
5 403 m/s
6 482 m/s
7 569 m/s
 
SB MONOTUBULAR PROPELLANT, CHARGE M3A1 IN GREEN BAG. CYLINDRICAL AND PERFORATED PROPELLANT GRAIN USED IN 155 MM BOFORS HOWITZER GUN
Ballistic Requirements

Pressure

P max 119.04 Mpa
P average 90.2 to 109.4 Mpc
 

Velocity

Zone MV
1 207 m/s
2 235 m/s
3 271 m/s
4 316 m/s
5 319 m/s
 
NC-NG BASED PROPELLANTS FOR ROCKET
Type Specification
Booster propellant charge PZM used in Seat Ejection Cartridge for Aircraft Booster charge containing 11 nos. of single perforated cylindrical grains density of propellant > 1.58 gm/cm³
Total weight ≥ 2.17 Kgs
Pressure (kg/cm²) 35 70 105
Rate of burning in mm/Sec
Max - 19.0 21.2
Min 12.5 - 20.0
Propellant Pinaka for Multi Barrel Rocket system Composite Propellant : Oxidiser, binder & curing agent
In inhibited grain OD - 198 mm, ID - 115.3 mm (Front), L - 1364 mm (Front), R - 1366 mm & 102.3 mm (Rear)
WT - 54.25 Kg (Front)/ 51.25 KG (Rear)
Cal Val - 1500 Cal/Gm
Burning rate at 70 Kg/ cm²- 9.9 ± .15 mm/Sec
Range 39 Km
 
PROPELLANT 57 MM
USAGE Air to Air to Surface Rocket fired from Mig Air Craft.
Shelf-life 10 Years (Storage condition 27 degree ± 3 degree C.
Hazard Classification HD 1.3 C
 
CHEMICAL COMPOSITION
Nitrocellulose 58.0 ± 1.5 %
Nitroglycerine 29.8 ± 1.0 %
Diethly Phthalate 6.8 ± 0.7 %
Carbamite 2.9 ± 0.4 %
Basic Lead Stearate 2.0 ± 0.4 %
Carbon Black 0.5 ± 0.2 %
 
DIMENSIONS
Outer Diameter 45.1 to 45.6 mm
Inner Diameter 7.7 to 8.1 mm
Length 448 + 0.5 mm
       - 1.0 mm
Weight 1.105 to 1.130 kg.
 
BALLISTIC PARAMETER
Sl.No Parameter - 40 Degree C (Cold) + 65 Degree C (Hot)
1. Ignition Rise Time Min - 1ms
Max - 20 ms
Min - 1 ms
Max - 15 ms
2. Action Time Min - 500ms
Max - 450 ms
Min - 480ms
Max - 650 ms
3. Burning Time Min - 470ms
Max - 720 ms
Min - 430ms
Max - 600 ms
4. Maximum Chamber pressure 140 to 220 kg./cm2 150 to 300 kg./cm2
5. Maximum lgnition pressure Min 150 kg./cm2 Max 400 kg./cm2
6. Agerage Chamber pressure 100 to 200 kg./cm 2 150 to 250 kg./cm 2
7. Maximum Thrust 300 to 400 kg. 350 to 450 kg.
8. Maximum lgnition Thrust 400 to 510 kg. 600 to 800 kg.
9. Average Thrust 300 to 400 kg 350 to 450 kg
10. Action time Total Impulse 190 to 220 kg. Sec. 200 to 250 kg. Sec.
11. Ignition delay 05 to 40 ms  
 
MARKING PACKAGING
The Propellant charges are numbered serially with lot number and grain number and wrapped in paraffin waxed paper. Propellant charges are to be packed in approved materials only.The boxes must be lined with paper (kraft type) waxed confirming to the specification and inside of the box to be lined with corrugated paper for cushioning.
 
MISSILE PROPELLANTS
BOOSTER/SUSTAINER INHIBITED PROPELLANT FOR KONKURS MISSILE
Specification
Propellant weight (Kg) 3.35 ± 0.05
AV Thrust (Kgf) > 64
Max Press (Ksc) < 200
Total B.T. (Sec) >11.5
Total Impulse (Kgf.S) > 513
 
DB PROPELLANT FOR GYRO CHARGE USED IN KONKURS MISSILE

Ballistics

Pmax 485 Kg/ cm²
Time of burning 0.22 Sec
Flash Point 190 ºC
Calorific value 930 ± 15 K Cal/Kg
 

BOOSTER POWDER CHARGE (5B-84) FOR MISSILE RZ – 61

One set comprising of 14 DB Prop grains of Total Weight = 280 Kgs

L (12 Grains) 1160 mm
(02 Grains) 1071.50 mm
OD (12 Grains) 122.80 mm
(02 Grains) 122.35 mm
ID (14 Grains) 33.8 mm
 

Ballistics

Thrust 20000 Kgf
Pressure Generated 60 KSC
Burning Time 3.3 to 3.8 Sec
Operating Temperature -25 ºC to + 40 ºC
 
SUSTAINER POWDER CHARGE FOR SUSTAINED THRUST OF SURFACE TO AIR MISSILE RZ – 61
(Composite Propellant)

Dimensions:

Wt. of Grain (Bare) 146.5 Kgs
Wt. of Inhibited & Finished Grains 150 Kgs
Length (Finished) 945 mm
Outer Dia 351.4 mm to 356.2 mm
Inner Dia 83 mm
Slots (Radial) 6 Nos.

Physical:

Pressure (Av) 51 Kg/ cm²
Thrust (Av) 1800 Kgf
Action Time 18-20 Sec
Burning rate at pressure 70 kg/ cm² 7.8 0.3 m/s
Burning rate at pressure 50 kg/ cm² 6.8 m/s
Density 1.76 gm/c
Cal. Val. 1530 Cal/gm
 
BASE BLEED CHARGES FOR 155 MM (NASCHEM) (Composite Propellant)
Mass of Inhibited Grain 1033 ~ 1035 gm
Burning rate (at normal temp & pressure) 0.90 to 1.10 mm/s
Stress 600 KN/ m²
Strain 30% min
Young Modulus 4500 KN/ m² min
Hardness 56 min
Density 1.50 to 1.60 gm/cm²
 
Propellant for 155 mm Ammunition (Double Base)
  Charge 8 Charge 9
Length 735 ± 5 mm 740 ± 5 mm
OD 6.40 ± 0.30 mm 12.1 ± 0.2 mm
Hole Dia 3.30 ± 0.30 mm 1.28 ± 0.04 mm
Web 1.55 ± 0.05 mm 2.02 ± 0.03 mm
Cal Val 700 ± 25 Cal/gm 800 ± 25 Cal/gm
Ballistics
V of A at 685 m/s at 210 C   827 m/s at 320 C
SD 3.2 m/s   3.5 m/s
ACP Mean 241 Mpa   309 Mpa
Range 19 Km   27 Km
 
TRIPLE BASE PROPELLANTS FOR 125 MM HE/HEAT/FSAPDS AMMUNITION
  For HE/HEAT For FSAPDS
Propellant NQ/S 400-100 3.0 kgs 4.86 Kgs
Propellant NQ/M-119 2.22 Kgs 2.32 Kgs
V of A 853.7 m/s 1512 m/s
ACP(mean) not > 388 MPa 400 ± 10 MPa
ACP(Max) not > 410 Mpa 415 MPa
 
JATO BOOSTER FOR CHUKER III (NAVY) INHIBITED GRAINS
Length 587 to 590 mm
Outer dia 116.0 to 118.08 mm
Inner dia 81.58 to 83.15 mm
Cal Val 990 ± 10 cal/g
Weight of grain 6.880 to 7.045 Kgs
Burning rate At 50 Kg/sq.cm = 18.2 mm/sec
At 70 Kg/sq.cm = 20.2 mm/sec
At 105 Kg/sq.cm = 22.8 mm/sec
Contact :
Marketing & Export Division
Ordnance Factory Board
Ayudh Bhawan
Government of India
Ministry of Defence
10A, S. K. Bose Road, Kolkata – 700 001, India.

Tel: 0091-33-2248 9027 / 2248 2103 / 2248 5077-80
Fax : 0091-33-2248 1748/2210 8235
Mail : ofbtrade@dataone.in
www.ofb.gov.in