Proton 8K82K/11S824 Credit - © Mark Wade Media Gallery

This four stage version of the Proton was a modification of the original Block D / 11S824M for launch of late 1980's Lavochkin OKB probes on missions to Mars. Guidance to the Block D-2 stage must be supplied by spacecraft.

Manufacturer: Chelomei. Launches: 3. Failures: 1. Success Rate: 66.67%. First Launch Date: 1988-07-07. Last Launch Date: 1996-11-16. Launch data is: continuing. Payload: 6,220 kg (13,710 lb). to a: transmartian trajectory. Associated Spacecraft: Fobos 1F, Mars M1. Liftoff Thrust: 8,847.000 kN (1,988,884 lbf). Total Mass: 710,710 kg (1,566,840 lb). Core Diameter: 4.15 m (13.61 ft). Total Length: 57.00 m (187.00 ft). Launch Price $: 70.000 million. in: 1994 price dollars.

• Stage Number: 1. 1 x Stage: Proton K-1. Gross Mass: 450,510 kg (993,200 lb). Empty Mass: 31,100 kg (68,500 lb). Thrust (vac): 10,470.158 kN (2,353,785 lbf). Isp: 316 sec. Burn time: 124 sec. Isp(sl): 267 sec. Diameter: 4.15 m (13.61 ft). Span: 7.40 m (24.20 ft). Length: 21.20 m (69.50 ft). Propellants: N2O4/UDMH. No Engines: 6. Engine: RD-253-11D48. Other designations: 8S810K.

• Stage Number: 2. 1 x Stage: Proton K-2. Gross Mass: 167,828 kg (369,997 lb). Empty Mass: 11,715 kg (25,827 lb). Thrust (vac): 2,399.216 kN (539,365 lbf). Isp: 327 sec. Burn time: 206 sec. Isp(sl): 230 sec. Diameter: 4.15 m (13.61 ft). Span: 4.15 m (13.61 ft). Length: 14.00 m (45.00 ft). Propellants: N2O4/UDMH. No Engines: 4. Engine: RD-0210. Other designations: 8S811K.

• Stage Number: 3. 1 x Stage: Proton K-3. Gross Mass: 50,747 kg (111,877 lb). Empty Mass: 4,185 kg (9,226 lb). Thrust (vac): 630.170 kN (141,668 lbf). Isp: 325 sec. Burn time: 238 sec. Isp(sl): 230 sec. Diameter: 4.15 m (13.61 ft). Span: 4.15 m (13.61 ft). Length: 6.50 m (21.30 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: RD-0212.

• Stage Number: 4. 1 x Stage: Proton 11S824F. Gross Mass: 16,900 kg (37,200 lb). Empty Mass: 1,800 kg (3,900 lb). Thrust (vac): 85.020 kN (19,113 lbf). Isp: 352 sec. Burn time: 610 sec. Diameter: 3.70 m (12.10 ft). Span: 3.70 m (12.10 ft). Length: 5.50 m (18.00 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RD-58M. Other designations: 11S824; Block D; D-1-e. Status: Out of production. Also known as Block D-2; article number 11S824F. Without guidance unit (navigation commands come from payload). Successor to 11S824M. Used for launch of Lavochkin Mars-bound spacecraft in 1988 and 1996.

1988 July 7 - 17:38 GMT - Launch Site: Baikonur. Launch Complex: LC200. Launch Pad: LC200/39. Launch Vehicle: Proton 8K82K / 11S824F. Model: Proton-K/D-2. LV Configuration: Proton-K/D-2/11S824F 356-02.

• Phobos 1 Nation: USSR. Program: Mars. Payload: 1F s/n 101. Mass: 6,220 kg (13,710 lb). Class: Planetary. Type: Mars. Spacecraft: Fobos 1F. Agency: MOM. Perigee: 2,628 km (1,632 mi). Apogee: 130,504 km (81,091 mi). Inclination: 50.80 deg. Period: 3,267.73 min. COSPAR: 1988-058A. USAF Sat Cat: 19281. Second of two missions to Mars' moon Phobos; carried 2 landers; planned to enter Mars orbit. Phobos 1 operated nominally until an expected communications session on 2 September 1988 failed to occur. The failure of controllers to regain contact with the spacecraft was traced to an error in the software uploaded on 29/30 August which had deactivated the attitude thrusters. This resulted in a loss of lock on the Sun, resulting in the spacecraft orienting the solar arrays away from the Sun, thus depleting the batteries. Left in solar Orbit (Heliocentric).References: 1, 2, 5, 6, 67, 118, 274, 296.

• 1F DPS Nation: USSR. Program: Mars. Payload: Dolgozhivushchaya PS. Spacecraft: Fobos 1F. Agency: UNKS. COSPAR: 1988-058xx. USAF Sat Cat: 19281. References: 279.

• Phobos 2 Nation: USSR. Program: Mars. Payload: 1F s/n 102. Mass: 6,220 kg (13,710 lb). Class: Planetary. Type: Mars. Spacecraft: Fobos 1F. Agency: MOM. Perigee: 850 km (520 mi). Apogee: 79,750 km (49,550 mi). Inclination: 1.00 deg. Period: 4,590.00 min. COSPAR: 1988-059A. USAF Sat Cat: 19287. First of two Mars missions to Mars' moon Phobos; carried two landers; entered Mars orbit 1/29/89; failed 3/27/89; extremely limited science data. Phobos 2 operated nominally throughout its cruise and Mars orbital insertion phases, gathering data on the Sun, interplanetary medium, Mars, and Phobos. Shortly before the final phase of the mission, during which the spacecraft was to approach within 50 m of Phobos' surface and release two landers, one a mobile 'hopper', the other a stationary platform, contact with Phobos 2 was lost. The mission ended when the spacecraft signal failed to be successfully reacquired on 27 March 1989. The cause of the failure was determined to be a malfunction of the on-board computer.References: 1, 2, 5, 6, 67, 118, 274, 296.

• 1F PPS Nation: USSR. Program: Mars. Payload: Prigayushchaya PS. Spacecraft: Fobos 1F. Agency: UNKS. COSPAR: 1988-059xx. USAF Sat Cat: 19287. References: 279.

• 1F DPS Nation: USSR. Program: Mars. Payload: Dolgozhivushchaya PS. Spacecraft: Fobos 1F. Agency: UNKS. COSPAR: 1988-059xx. USAF Sat Cat: 19287. References: 279.

• Mars-96 (Mars 8) Nation: Russia. Program: Mars. Payload: M1 s/n 520. Class: Planetary. Type: Mars. Spacecraft: Mars M1. Agency: VKS. Perigee: 110 km (60 mi). Apogee: 340 km (210 mi). Inclination: 51.60 deg. COSPAR: 1996-064A. USAF Sat Cat: 24656. Decay Date: 1996-11-18. The Mars 96 spacecraft was launched into Earth orbit, but failed to achieve insertion into Mars cruise trajectory and re-entered the Earth's atmosphere at about 00:45 to 01:30 GMT on 17 November 1996 and crashed within a presumed 320 km by 80 km area which includes parts of the Pacific Ocean, Chile, and Bolivia. The Russian Mars 96 mission was designed to send an orbiter, two small autonomous stations, and two surface penetrators to Mars.References: 4, 67, 118, 274, 296.

• MAS 1 Nation: Russia. Program: Mars. Payload: MAS s/n 520/1. Spacecraft: Mars M1. Agency: VKS. COSPAR: 1996-064xx. References: 279.

• Penetrator 1 Nation: Russia. Program: Mars. Payload: PN s/n 520/4. Spacecraft: Mars M1. Agency: VKS. COSPAR: 1996-064xx. References: 279.

• Penetrator 2 Nation: Russia. Program: Mars. Payload: PN s/n 520/5. Spacecraft: Mars M1. Agency: VKS. COSPAR: 1996-064xx. References: 279.

• MAS 2 Nation: Russia. Program: Mars. Payload: MAS s/n 520/2. Spacecraft: Mars M1. Agency: VKS. COSPAR: 1996-064xx. References: 279.

• McDowell, Jonathan, Jonathan's Space Home Page, Harvard University, 1997-present. Jonathan McDowell's complete on-line listing of all objects orbited and over 20,000 rocket launches Accessed at: http://www.planet4589.org/jsr.html.

• Isakowitz, Steven J,, International Reference to Space Launch Systems Second Edition, AIAA, Washington DC, 1991 (succeeded by 2000 edition). ISBN: 1563473534. Superseded by the later editions. More at amazon.com...

• Kaesmann, Ferdinand, et. al., Journal of the British Interplanetary Society, "Proton - Development of A Russian Launch Vehicle", 1998, Volume 51, page 3.

• Clark, P S, Journal of the British Interplanetary Society, "Soviet Spacecraft Masses for Deep Space Missions", 1985, Volume 38, page 25.

• Mission Planner's Manual - Proton Commercial Launch Vehicle, Space Commerce Corporation, Houston, TX 1989.

• Afanasyev, Igor, Novosti kosmonavtiki, "35 let RN Proton", 1998, Issue 5, page 40.

• Vladimirov, A, Novosti kosmonavtiki, "Tablitsa zapuskov RN 'Proton' i 'Proton K'", 1998, Issue 10, page 25.