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Castor 4
Thiokol solid rocket engine. Series of motors used as Delta strap-on boosters and as first and upper stages for low-cost all-solid-propellant designs. First flight 1975.

AKA: TX-526. Number: 342 . Thrust: 407.20 kN (91,542 lbf). Gross mass: 10,534 kg (23,223 lb). Unfuelled mass: 1,269 kg (2,797 lb). Specific impulse: 261 s. Specific impulse sea level: 228 s. Burn time: 54 s. Height: 9.07 m (29.75 ft). Diameter: 1.02 m (3.34 ft).

Thrust (sl): 355.700 kN (79,965 lbf). Thrust (sl): 36,274 kgf.

More at: Castor 4.
Subtopics
SICBM-1 Thiokol solid rocket engine.
Castor 4A engine Thiokol solid rocket engine. Out of production. Castor 4A improved Delta performance by 11% by replacing the old fuel with HTPB propellant. Used in Delta 6900; Atlas IIAS; Castor 4A. First flight 1982.
Castor 4AXL H-2A Solid propellant rocket stage. Provides supplemental thrust for H-2 or H-2A.
Castor 4B engine Thiokol solid rocket engine. Out of production. The Castor 4B, which incorporated thrust vector control in the series for the first time, was developed for ESA's Maxus (first flown in 1991). First flight 1982. Solid propellant rocket stage. Optimized for high altitude (Conestoga).
Castor 4AXL Thiokol solid rocket engine. In production. Strap-on booster version, first tested May 1992. Its 30% performance increase would improve performance of Atlas and other vehicles. First flight 2001. Solid propellant rocket stage. Provides supplemental thrust for H-2 or H-2A. Solid propellant rocket stage. Provides supplemental thrust for H-2 or H-2A.
Castor 4BXL Thiokol solid rocket engine. In Production. ORBEX version, combined the 4XL motor with 4B's TVC system (6 degree).
Castor 4XL Solid propellant rocket stage. Provides supplemental thrust for H-2 or H-2A.
Country: USA. Launch Vehicles: Athena H, Delta 3914, Delta 3910, Delta 3910/PAM, Delta 3913, Delta 3920, Delta 3920/PAM, Delta 3924, Delta 3920-8. Propellants: Solid. Stages: Castor 4. Agency: Thiokol.
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