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Buran evolution - wish I understood Russian!
http://www.buran.ru/htm/history.htm
There are some interesting stages in the evolution of the Energia/Buran design, the OS-120 resembling the American Shuttle in having three main engines but additionaly having two small (solid?) engines on either side of the orbiter, the OK-92 having a single engine and a pair of what appear to be landing jets, to the flown version. I wish they had done an English version of this page, trying to put it through Google language tools only translates part way. |
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Buran evolution - wish I understood Russian!
Cruithne3753 wrote: http://www.buran.ru/htm/history.htm There are some interesting stages in the evolution of the Energia/Buran design, the OS-120 resembling the American Shuttle in having three main engines but additionaly having two small (solid?) engines on either side of the orbiter I assume those are abort engines; some of our early shuttle designs had them also. (should have kept them, they might have saved Challenger). Though they don't point it out, most of their illustrations are linked to other pages on that website; here's the linked page on the OS-120: http://www.buran.ru/htm/os-120.htm , the OK-92 having a single engine and a pair of what appear to be landing jets, to the flown version. Here's the linked page to that: http://www.buran.ru/htm/ok-92.htm Including a cutaway of the jet engines. Pat |
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Buran evolution - wish I understood Russian!
On Sep 2, 6:59 pm, Cruithne3753
wrote: the OS-120 resembling the American Shuttle in having three main engines but additionaly having two small (solid?) engines on either side of the orbiter, Yes, they are small solids intended for an emergency rescue system. You have to read a fair amount down into http://www.buran.ru/htm/os-120.htm , but there you find The Soviet analog of the Space Shuttle orbital stage -- the OS-120 variant -- turned out heavier (full launch mass 155.35 t; mass in orbit 120 t, including 30 t payload; landing mass 89 t) because of the use of two pylon-mounted solid rockets in the tail section for the accident rescue system. These were intended for emergency separation of the orbiter from the fuel section if an emergency [accident] situation arose during the ascent phase. Space Shuttle - " -120" ( 155,35 , 120 30 , - 89 ) , |
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Buran evolution - wish I understood Russian!
wrote: According to the caption of the figure naming the parts(*) in http://www.buran.ru/htm/ok-92.htm, the single engine in the tail is, to my considerable surprise, a 470 mtf solid motor for an emergency rescue system. That's odd, because in this version the Energia has only three engines on the base of the core stage, so something regarding mass, isp, or burn duration is different from the flown version. On the US version of the Shuttle with the solid escape engines mounted on the wing, they would have been used for orbital insertion if not needed for an ascent abort. What impressed me about this variant of the Buran design was how much smaller the wing area was in comparison to the flown version. That's going to lead to higher heating and G loads during reentry. Thermal protection on those pods during reentry doesn't look any too easy either. It was the intention to possibly return the jet engines to either side of the flown Buran's tail at some future date as a improvement to the vehicle. The big problem they were running into was the whole launch system was coming in considerably heavier than planned (the same thing had happened with the N-1) particularly in regards to the recovery system planned to be used on the boosters to allow them to descend horizontally on land. I never have read the specifics of how this was was supposed to work, but the boosters had extensible landing legs, as shown on the cutaways on this page: http://www.buran.ru/htm/rocket.htm I don't know if the final landing was to use Soyuz-type solid fuel engines to cushion the impact, or some sort of crushable aluminum honeycomb material (the drawings make it look like the latter may be the case). Pat |
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Buran evolution - wish I understood Russian!
On Sep 3, 2:46 am, Pat Flannery wrote:
wrote: Thermal protection on those pods during reentry doesn't look any too easy either. The text says they had jettisonable thermal protective covers. (10 & 11 in the diagram). 15 is the emergency rocket motor nozzle. Actually, Bablefish does a semicomprehensible job with this, if you want to check it: 10 - expendable front fairing- silencer TRD - TURBOJET ENGINE D -30KP; [What is translated as "expendable" is better rendered "discardable" here.] 11 - expendable rear heatproof cover- silencer (it is shown on the right pod); 15 - nozzle RDTT - SOLID-PROPELLANT ROCKET ENGINE of the system of emergency recovery (SAS) Then the first bulleted item in the text below the figure comes out as # jettisoned on shch'-oy second of flight after the passage of the critical phase of flight RDTT - SOLID-PROPELLANT ROCKET ENGINE OF SAS with the initial thrust 470 t; That needs a little work: "shch'oy" is 56th (I guess the KOI-8 encoding of the numerals confused Bablefish), so it's # jettisoned on 56th second of flight after the passage of the critical phase of flight RDTT - SOLID-PROPELLANT ROCKET ENGINE OF SAS with the initial thrust 470 t; |
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Buran evolution - wish I understood Russian!
On Sep 3, 5:51 am, " wrote:
On Sep 3, 2:46 am, Pat Flannery wrote: wrote: Thermal protection on those pods during reentry doesn't look any too easy either. The text says they had jettisonable thermal protective covers. (10 & 11 in the diagram). 15 is the emergency rocket motor nozzle. Actually, Bablefish does a semicomprehensible job with this, if you want to check it: 10 - expendable front fairing- silencer TRD - TURBOJET ENGINE D -30KP; [What is translated as "expendable" is better rendered "discardable" here.] 11 - expendable rear heatproof cover- silencer (it is shown on the right pod); 15 - nozzle RDTT - SOLID-PROPELLANT ROCKET ENGINE of the system of emergency recovery (SAS) Then the first bulleted item in the text below the figure comes out as # jettisoned on shch'-oy second of flight after the passage of the critical phase of flight RDTT - SOLID-PROPELLANT ROCKET ENGINE OF SAS with the initial thrust 470 t; That needs a little work: "shch'oy" is 56th (I guess the KOI-8 encoding of the numerals confused Bablefish), so it's # jettisoned on 56th second of flight after the passage of the critical phase of flight RDTT - SOLID-PROPELLANT ROCKET ENGINE OF SAS with the initial thrust 470 t; As an aside, they apparently have updated this site. Some of the new stuff shows CG of the Mig 105's pilot escape capsule and how it it configured in the air-frame. Neat stuff..........................Doc |
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Buran evolution - wish I understood Russian!
wrote: On Sep 3, 2:46 am, Pat Flannery wrote: wrote: Thermal protection on those pods during reentry doesn't look any too easy either. The text says they had jettisonable thermal protective covers. (10 & 11 in the diagram). 15 is the emergency rocket motor nozzle. Actually, Bablefish does a semicomprehensible job with this, if you want to check it: I tried to run the whole page through Babel Fish, but it would indicate that the page had some error on it that it couldn't translate. 10 - expendable front fairing- silencer TRD - TURBOJET ENGINE D -30KP; [What is translated as "expendable" is better rendered "discardable" here.] 11 - expendable rear heatproof cover- silencer (it is shown on the right pod); 15 - nozzle RDTT - SOLID-PROPELLANT ROCKET ENGINE of the system of emergency recovery (SAS) Then the first bulleted item in the text below the figure comes out as # jettisoned on shch'-oy second of flight after the passage of the critical phase of flight RDTT - SOLID-PROPELLANT ROCKET ENGINE OF SAS with the initial thrust 470 t; That needs a little work: "shch'oy" is 56th (I guess the KOI-8 encoding of the numerals confused Bablefish), so it's # jettisoned on 56th second of flight after the passage of the critical phase of flight RDTT - SOLID-PROPELLANT ROCKET ENGINE OF SAS with the initial thrust 470 t; If you check out the cutaway of the vehicle, it appears the escape motor is housed inside some sort of propellant tank structu http://www.buran.ru/images/gif/ok-92-7.gif There's something else odd about this design I just noticed...look how the strap-on boosters are located in comparison to the flown version: http://www.buran.ru/images/gif/ok-92-6.gif The bottom two are nearly on the far side of the core tankage from the orbiter, and this is going to require a lot of gimbaling of the core engines to get their thrust-line through the center of mass of the stack. The way they've got it designed the thing is going to try and flip over sideways on liftoff from a lack of thrust on the side the orbiter is on. Pat |
#9
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Buran evolution - wish I understood Russian!
wrote: As an aside, they apparently have updated this site. Some of the new stuff shows CG of the Mig 105's pilot escape capsule and how it it configured in the air-frame. Neat stuff..........................Doc I wasn't aware the MiG 105 had an escape capsule like the planned Spiral spacecraft incorporated. There would be no real need for it, as it was never used for high speed or high altitude flight, and I assumed it had a simple ejection seat. Here's the website page I have for it: http://www.buran.ru/htm/epos.htm And the structural cutaway doesn't seem to show an escape capsule: http://www.buran.ru/images/gif/epos_05.gif Do they have another new page on the MiG 105 testbed? The website took me a whole day to sift through and bookmark. Pat |
#10
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Buran evolution - wish I understood Russian!
On Sep 3, 1:44 pm, Pat Flannery wrote:
I tried to run the whole page through Babel Fish, but it would indicate that the page had some error on it that it couldn't translate. Da Fish, being a derivative of the Systran translation system the old and much-to-be-esteemed USAF Foreign Technology Division funded to translate technical Russian into English during the Cold War, does a fair job of translating technical Russian into English. But times having moved on beyond pure ASCII or KOI-8, it sometimes gets confused. And then there's still the problem that oftentimes it's necessary to *understand* what the source language is saying in order to translate it into the target language in an understandable fashion. |
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