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Delta 3000
Part of Thor Family
Delta 3924 no. 167
Delta 3924 no. 167
Delta 3924 no. 167 - COSPAR 1983-030
American orbital launch vehicle. The Delta 3000 series upgraded the boosters to Castor 4 solid propellant strap-ons, while retaining the Extended Long Tank core with RS-27 engine. The 3910 series used the TRW Lunar Module engine in the second stage, while the 3920 series reintroduced the Aerojet AJ110 Delta engine.

Status: Out of production. Payload: 954 kg (2,103 lb). Thrust: 3,046.20 kN (684,813 lbf). Gross mass: 185,382 kg (408,697 lb). Height: 35.00 m (114.00 ft). Diameter: 2.44 m (8.00 ft).

During the production run of the Delta 3000 series, production gradually transitioned from the 3910 model (with the TRW engine) to the 3920 model (with the Aerojet engine).

Payload: 954 kg (2,103 lb) to a GTO. Launch Price $: 16.300 million in 1977 dollars.

Stage Data - Delta 3000

  • Stage 0. 9 x Castor 4. Gross Mass: 10,534 kg (23,223 lb). Empty Mass: 1,269 kg (2,797 lb). Thrust (vac): 407.211 kN (91,545 lbf). Isp: 261 sec. Burn time: 54 sec. Isp(sl): 228 sec. Diameter: 1.02 m (3.34 ft). Span: 1.02 m (3.34 ft). Length: 9.07 m (29.75 ft). Propellants: Solid. No Engines: 1. Engine: Castor 4. Status: Out of Production.
  • Stage 1. 1 x Delta Thor RS27. Gross Mass: 84,368 kg (185,999 lb). Empty Mass: 4,360 kg (9,610 lb). Thrust (vac): 1,030.218 kN (231,602 lbf). Isp: 296 sec. Burn time: 223 sec. Isp(sl): 262 sec. Diameter: 2.44 m (8.00 ft). Span: 2.44 m (8.00 ft). Length: 22.37 m (73.39 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RS-27. Other designations: Extended Length Thor RS-27. Status: Out of Production.
  • Stage 2. 1 x Delta P. Gross Mass: 5,434 kg (11,979 lb). Empty Mass: 820 kg (1,800 lb). Thrust (vac): 41.923 kN (9,425 lbf). Isp: 301 sec. Burn time: 322 sec. Isp(sl): 0.0000 sec. Diameter: 1.38 m (4.52 ft). Span: 1.38 m (4.52 ft). Length: 5.97 m (19.58 ft). Propellants: N2O4/Aerozine-50. No Engines: 1. Engine: TR-201. Other designations: TR-201. Status: Out of Production.
  • Stage 3. 1 x Burner 2. Gross Mass: 774 kg (1,706 lb). Empty Mass: 116 kg (255 lb). Thrust (vac): 43.551 kN (9,791 lbf). Isp: 285 sec. Burn time: 42 sec. Isp(sl): 220 sec. Diameter: 0.66 m (2.16 ft). Span: 0.66 m (2.16 ft). Length: 0.84 m (2.75 ft). Propellants: Solid. No Engines: 1. Engine: Star 37. Status: Out of Production. Burner II was a launch vehicle upper stage developed by Boeing for the Air Force Space Systems Division. It was the first solid-fuel upper stage with full control and guidance capability developed for general space applications. Burner II was designed for use with the Thor booster, but was readily adapted for use on the complete range of standard launch vehicles. Its general assignment was to place small- and medium size payloads into orbit. The Burner II motor, guidance system and reaction control system were integrated to provide attitude stability and precise control of flight rate and burnout velocity for orbital injection and earth-escape missions. Boeing had delivered 8 flight vehicles under its original contract. Under terms of a follow-on contract, it built 6 additional flight models. Four Thor-Burner II combinations were launched successfully from Vandenberg Air Force Base, California. The third launch placed 2 unclassified satellites in Earth orbit. A SECOR satellite, built for the U.S. Army Corps of Engineers by the Cubic Corporation, and an Aurora satellite, developed by Rice University for the Office of Naval Research, were placed in circular orbits 3,300 km above the Earth. As integration contractor for the Air Force Space Experiment Support Program (SESP) Office, Boeing designed, built and tested the injection stage, or "payload dispenser," which carried the 2 satellites on top of a standard Burner II stage and placed them in precise orbits. The satellites were mounted on opposite sides of the injection stage, which housed a640 kgf thrust, solid-propellant rocket motor. The Burner II was used as an upper stage by NASA for deep space probes. Prime Contractor: The Boeing Company. Major Subcontractors Thiokol Chemical Corporation (solid rocket motor); Honeywell Inc. (pre-programmed inertial guidance system); Walter Kidde Co. (reaction control system).



Family: orbital launch vehicle. Country: USA. Engines: RS-27, AJ10-118K, TR-201. Spacecraft: GOES, AS 1000, NATO 3, ECS/OTS, Anik satellite, SMM, HS 376, Insat 1, Dynamics Explorer, SSTL-70, AS 3000, Landsat 4-5, IRAS, Exosat, AMPTE, SDI. Stages: Star 37. Agency: Douglas.
Photo Gallery

Delta 3910 no. 151  Delta 3910 no. 151
Delta 3910 no. 151 - COSPAR 1980-014


Delta 3925Delta 3925
Credit: Boeing



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