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In August 1908, a white mob attacked Springfield, Illinois’s Black community, destroying homes and businesses and lynching two Black men. National outrage over the violence helped spur the movement that created the NAACP the following year.
MORE →Reflects the personal views, recollections, and perspective of the author, Mike Davis.
This is a personal recollection on the Move fire on May 13, 1985
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| Country of origin | Soviet Union |
|---|---|
| First flight | 1967 |
| Designer | OKB-1, V. M. Melnikov |
| Manufacturer | Voronezh Mechanical Plant |
| Application | Upper Stage |
| Associated LV | N1, Proton-K, Proton-M, Zenit |
| Predecessor | S1.5400 |
| Status | In Production |
| Liquid-fuel engine | |
| Propellant | LOX / RG-1 |
| Cycle | Oxidizer-rich staged combustion |
| Configuration | |
| Chamber | 1 |
| Performance | |
| Thrust, vacuum | 79.46 kilonewtons (17,860 lbf) |
| Specific impulse, vacuum | 353 s |
| Burn time | up to 600 s |
| Dimensions | |
| Dry mass | 300 kilograms (660 lb) |
| Used in | |
| Block D | |
| References | |
| References | [1][2][3][4] |
The RD-58 (Russian: Ракетный Двигатель-58, romanized: Raketnyy Dvigatel-58, lit. 'Rocket Engine 58', GRAU index: 11D58) is a rocket engine, developed in the 1960s by OKB-1, now RKK Energia. The project was managed by Mikhail Melnikov, and it was based on the previous S1.5400 engine, which was the first staged combustion engine in the world.[1] The engine was initially created to power the Blok D stage of the Soviet Union's abortive N1 rocket.[5] Derivatives of this stage are now used as upper stages on some Proton and Zenit rockets.[6] An alternative version of the RD-58 chamber, featuring a shorter nozzle, was used as the N1's roll-control engine.
The RD-58 uses liquid oxygen as the oxidizer and RG-1 as fuel in an oxidizer-rich staged combustion cycle. It features a single gimbaled chamber, radial centrifugal pumps with auxiliary booster pumps, and an oxygen-rich preburner.[7] Recent modifications include a lightweight carbon-composite nozzle extender developed by NPO Iskra.[8][9][10]
The Buran spacecraft used two of an evolution of the RD-58M, called 17D12, as its main orbital correction engines. Instead of RG-1, it burned Syntin, and could be ignited 15 times.[11][12] It is assumed that it was the base for the RD-58S, which had practically the same specifications and powered the Blok DM-2M.[13] But the manufacturer states that the engine is compatible with both propellants.[1]
The current version of the engine is the RD-58M (manufacturer designation 11D58M), which has slightly reduced thrust, but increased isp. An even newer version is under development and is known as the RD-58MF (manufacturer designation 11D58MF). It will reduce thrust to 49.03 kilonewtons (11,020 lbf) to keep the same length but increase expansion ratio to 500:1. This will enable it to gain 20s of isp (to an expected 372s). It will eventually fly on the Blok DM-03.[14] This new version of the engine will be built in the Krasnoyarsk Machine-Building Plant.[15][16] During a November 2014 interview, Vladimir Kolmykov, the Deputy General Director of the Chemical Division of Krasnoyarsk Machine-Building Plant, stated that the production of Block-DM was suspended during that year, but work on the stage and development of the RD-58MF will resume during 2015.[17]
This engine has had many versions through the years:
| Name | RD-58 | RD-58M | RD-58M (Carbon Composite Nozzle) |
RD-58S | RD-58Z | RD-58MF | 17D12 |
|---|---|---|---|---|---|---|---|
| Index | 11D58 | 11D58M | 11D58S | 11D58Z | 11D58MF | ||
| Development years | 1964–1968 | 1970–1974 | 2000–2004 | 1986–1995 | 1981–1990 | 2002–2009 | 1981–1987 |
| Engine Type | Oxidizer-rich stage combustion upper stage liquid rocket engine | Orbital correction liquid rocket engine | |||||
| Propellant | RG-1/LOX | RG-1/LOX | RG-1/LOX | Syntin/LOX | RG-1/LOX | RG-1/LOX | Syntin/LOX |
| O/F | 2.48 | 2.48 | 2.82 | ? | 2.6 | 2.82 | ? |
| Chamber Pressure | 7.8 MPa (1,130 psi) | 7.75 MPa (1,124 psi) | 7.9 MPa (1,150 psi) | 7.94 MPa (1,152 psi) | 7.8 MPa (1,130 psi) | 7.9 MPa (1,150 psi) | 7.94 MPa (1,152 psi) |
| Thrust (Vac) | 83.4 kN (18,700 lbf) | 83.4 kN (18,700 lbf) | 85 kN (19,000 lbf) | 86.3 kN (19,400 lbf) | 71 kN (16,000 lbf) | 49.03 kN (11,020 lbf) | 86.24 kN (19,390 lbf) |
| Isp (Vac) | 349 s (3.42 km/s) | 356 s (3.49 km/s) | 361 s (3.54 km/s) | 361 s (3.54 km/s) | 361 s (3.54 km/s) | 372 s (3.65 km/s) | 362 s (3.55 km/s) |
| Nozzle Expansion | 189 | 189 | 280 | 189 | 189 | 500 | 189 |
| Ignitions | 4 | 4 | 7 | 5 | 5 | ? | 15 |
| Burntime | 600 seconds | 720 seconds | 1200 seconds | 680 seconds | 660 seconds | ? seconds | 680 seconds |
| Length | 2.27 m (89 in) | 2.27 m (89 in) | 2.72 m (107 in) | 2.27 m (89 in) | 2.27 m (89 in) | 2.27 m (89 in) | |
| Diameter | 1.17 m (46 in) | 1.17 m (46 in) | 1.4 m (55 in) | 1.17 m (46 in) | 1.17 m (46 in) | 1.17 m (46 in) | |
| Weight | 300 kg (660 lb) | 310 kg (680 lb) | 340 kg (750 lb) | 310 kg (680 lb) | 300 kg (660 lb) | 230 kg (510 lb) | |
| Used on | N-1 and Blok D | Blok DM | Blok DM-SL since 2003 and Blok DM-SLB | Blok DM-2M | Blok DM-SL | 11S861-03 | Buran |
| First Launch | 1967-03-10 | 1974-03-26 | 2003-06-10 | 1994-10-13 | 1999-03-28 | ? | 1988-11-15 |
| Status | Retired | Retired | In Production | Retired | Retired | In Production | Retired |
| References | [2][5][6][7][8][9][11][12][13][14][18][19][20][21][22][23][25] | ||||||
| Liquid fuel |
|  | ||||||||||||||||
|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|
| Solid fuel |
| |||||||||||||||||
| ||||||||||||||||||
Spacecraft engines and motors | ||
|---|---|---|
| Liquid fuel engines |  | |
| Solid propellant motors | ||
| Related articles | ||
Source: Wikipedia. Article content is retrieved live through the MediaWiki API.
The RD-58 (Russian: Ракетный Двигатель-58, romanized: Raketnyy Dvigatel-58, lit. 'Rocket Engine 58', GRAU index: 11D58) is a rocket engine, developed in the 1960s by OKB-1, now RKK Energia. The project was managed by Mikhail Melnikov, and it was based on the previous S1.5400 engine, which was the first staged combustion engine in the world. The engine was initially created to power the Blok D stage of the Soviet Union's abortive N1 rocket. Derivatives of this stage are now used as upper stages on some Proton and Zenit rockets. An alternative version of the RD-58 chamber, featuring a shorter nozzle, was used as the N1's roll-control engine. The RD-58 uses liquid oxygen as the oxidizer and RG-1 as fuel in an oxidizer-rich staged combustion cycle. It features a single gimbaled chamber, radial centrifugal pumps with auxiliary booster pumps, and an oxygen-rich preburner. Recent modifications include a lightweight carbon-composite nozzle extender developed by NPO Iskra. The Buran spacecraft used two of an evolution of the RD-58M, called 17D12, as its main orbital correction engines. Instead of RG-1, it burned Syntin, and could be ignited 15 times. It is assumed that it was the base for the RD-58S, which had practically the same specifications and powered the Blok DM-2M. But the manufacturer states that the engine is compatible with both propellants. The current version of the engine is the RD-58M (manufacturer designation 11D58M), which has slightly reduced thrust, but increased isp. An even newer version is under development and is known as the RD-58MF (manufacturer designation 11D58MF). It will reduce thrust to 49.03 kilonewtons (11,020 lbf) to keep the same length but increase expansion ratio to 500:1. This will enable it to gain 20s of isp (to an expected 372s). It will eventually fly on the Blok DM-03. This new version of the engine will be built in the Krasnoyarsk Machine-Building Plant. During a November 2014 interview, Vladimir Kolmykov, the Deputy General Director of the Chemical Division of Krasnoyarsk Machine-Building Plant, stated that the production of Block-DM was suspended during that year, but work on the stage and development of the RD-58MF will resume during 2015.
The Blok DM-03 (Russian: Блок ДМ-03, lit. 'Block DM-03', GRAU index: 11S861-03), is a Russian upper stage used as an optional fourth stage on the Angara A5 heavy-lift rocket. Three have been launched, the first in December 2010; the first two launches failed before fourth stage ignition, the first as a result of a problem with the Blok DM's fuel load. Some versions are also known as Orion. Initial versions of the Blok DM-03 are powered by a single RD-58M engine, burning RG-1 and liquid oxygen. The last evolution is powered by the improved RD-58MF, a less powerful but more efficient evolution of the venerable engine. It can carry 25% more propellant than the Blok DM-2, which it replaced as a Proton upper stage for some government launches. However most government launches and all commercial missions use the Briz-M instead. The payloads for the first two Blok DM-03 launches were groups of three Uragan-M satellites for the GLONASS programme, with further missions slated to carry three more Uragan-M satellites, and two Ekspress satellites on separate launches. The Blok DM can inject payloads into orbit more accurately than the Briz-M, making it better suited for launching satellites such as the Uragan-M which lack apogee motors. When production ended in 2012, five Blok DM-03 stages had been produced by RKK Energia, for use on Proton and potentially Zenit rockets. A new version of the upper stage is expected to be introduced once the five launches are complete; all five DM-03s have been slated for Proton launches between 2010 and 2015. During a November 2014 interview, Vladimir Kolmykov, the Deputy General Director of the Chemical Division of Krasnoyarsk Machine-Building Plant, stated that the production of Block-DM was suspended during that year, but work on the stage and development of the RD-58MF resumed during 2015.
Zenit (Ukrainian: Зеніт, Russian: Зени́т; meaning Zenith) was a family of space launch vehicles designed by the Yuzhnoye Design Bureau in Dnipro, Ukraine, which was then part of the Soviet Union. Zenit was originally built in the 1980s for two purposes: as a liquid rocket booster for the Energia rocket and, equipped with a second stage, as a stand-alone middle-weight launcher with a payload greater than the 7 tonnes of the Soyuz but smaller than the 20 tonnes payload of the Proton. The last rocket family developed in the USSR, the Zenit was intended as an eventual replacement for the dated Soyuz and Proton families, and it would employ propellants which were safer and less toxic than the Proton's nitrogen tetroxide/UDMH mix. Zenit was planned to take over crewed spaceship launches from Soyuz, but these plans were abandoned after the dissolution of the Soviet Union in 1991. Many of components of the Zenit rockets were produced in Russia. The Ukrainian space industry was highly integrated with that of Russia due to its Soviet heritage, but that cooperation was interrupted by the Russo-Ukrainian War beginning in 2014, which has effectively led to a hiatus in the Zenit program. The subsequent Russian invasion of Ukraine in 2022 saw damage to its manufacturing facilities due to Russian missile strikes, and what survived those strikes pivoted to producing military weapons. Zenit-3SL was launched by the Sea Launch consortium's floating launch platform in the Pacific Ocean and Zenit-2 was launched from Baikonur Cosmodrome in Kazakhstan. RD-171M engines of the Zenit's first and second stages as well as the upper stage of the Zenit-3SL rocket were supplied by Russia. An improved Zenit-3SLB rocket was used for commercial launches from Baikonur Cosmodrome beginning in April 2008, marketed as Land Launch. Zenit-3SL was launched 36 times with 32 successes, one partial success, and three failures. The first failure, the launch of a Hughes-built communications satellite owned by ICO Global Communications, occurred during the second commercial launch on March 12, 2000, and was blamed on a software error that failed to close a valve in the second stage of the rocket. The second failure occurred on January 30, 2007, when the rocket exploded on the Odyssey launch platform, seconds after engine ignition. The NSS-8 communication satellite on board was destroyed. On September 24, 2011 Zenit-3SL launched successfully from the Odyssey launch platform under a renewed Sea Launch project with RSC Energia as the majority stakeholder. The rocket delivered the European communication satellite Atlantic Bird 7 to its planned orbit. On February 1, 2013, another Zenit-3SL failed while launching the Intelsat 27 satellite.
Amanda Coetzer (born 22 October 1971) is a South African former professional tennis player. She was ranked as high as world No. 3 by the Women's Tennis Association, achieved in November 1997. Coetzer won nine WTA Tour titles in singles and nine in doubles, and reached three major singles semifinals (at the 1996 and 1997 Australian Opens and the 1997 French Open) and one major doubles final (at the 1993 US Open). Coetzer earned a reputation for regularly beating players who were ranked higher than her. By virtue of scoring so many upset wins in spite of her 5'2" (1.58m) stature, she gained the nickname: "The Little Assassin".
Before the 1921 destruction of Tulsa’s Greenwood District, Black residents had created a remarkable center of business and community life. The district included stores, professional offices, entertainment venues and homes owned by Black citizens. Understanding Greenwood means learning what was built—not only what was burned.
MORE →The Greenwood District.