RU2000102687A - METHOD FOR INTRODUCING USE OF USEFUL LOAD OF A MULTIFUNCTIONAL ROCKET-CARRIER OF A COMBINED DIAGRAM WITH MARCHED LIQUID ROCKET MOTOR INSTALLATIONS (RUNNER) - Google Patents
METHOD FOR INTRODUCING USE OF USEFUL LOAD OF A MULTIFUNCTIONAL ROCKET-CARRIER OF A COMBINED DIAGRAM WITH MARCHED LIQUID ROCKET MOTOR INSTALLATIONS (RUNNER)Info
- Publication number
- RU2000102687A RU2000102687A RU2000102687/28A RU2000102687A RU2000102687A RU 2000102687 A RU2000102687 A RU 2000102687A RU 2000102687/28 A RU2000102687/28 A RU 2000102687/28A RU 2000102687 A RU2000102687 A RU 2000102687A RU 2000102687 A RU2000102687 A RU 2000102687A
- Authority
- RU
- Russia
- Prior art keywords
- rocket
- blocks
- central
- block
- marching
- Prior art date
Links
- 239000007788 liquid Substances 0.000 title claims 6
- 238000010586 diagram Methods 0.000 title 1
- 239000003380 propellant Substances 0.000 claims 8
- 230000001133 acceleration Effects 0.000 claims 4
- 210000004279 Orbit Anatomy 0.000 claims 2
- 230000015572 biosynthetic process Effects 0.000 claims 2
- 238000005755 formation reaction Methods 0.000 claims 2
- 239000000446 fuel Substances 0.000 claims 2
- 238000000926 separation method Methods 0.000 claims 2
- 235000015842 Hesperis Nutrition 0.000 claims 1
- 235000012633 Iberis amara Nutrition 0.000 claims 1
- 240000004804 Iberis amara Species 0.000 claims 1
- 239000000969 carrier Substances 0.000 claims 1
- 230000000875 corresponding Effects 0.000 claims 1
- 239000002828 fuel tank Substances 0.000 claims 1
- 238000004519 manufacturing process Methods 0.000 claims 1
Claims (8)
где Vi - текущая скорость ракеты-носителя;
k - динамический коэффициент, равный 0,95...1,05;
V1 - скорость ракеты-носителя, при которой достигнут предельно допустимый скоростной напор;
ρl - плотность стандартной атмосферы, при которой достигнут предельно допустимый скоростной напор;
ρi - текущая плотность стандартной атмосферы на высоте полета.3. The method according to claim 1, characterized in that. that on the atmospheric portion of the trajectory, the flight altitude of the launch vehicle and its speed are measured, which determine the velocity head of the incoming air flow at a standard atmosphere density at flight altitude, and when the carrier rocket reaches a speed at which aerodynamic forces from the velocity head of the air flow reach the maximum permissible values for the design of the launch vehicle, a further increase in the speed of the launch vehicle is carried out by adjusting the thrust of the marching rocket engine of the side rocket blocks in within 0.3 ... 1.0 of the nominal thrust from the condition of not exceeding the maximum permissible pressure head, maintaining the ratio
where V i is the current speed of the launch vehicle;
k is a dynamic coefficient equal to 0.95 ... 1.05;
V 1 - the speed of the launch vehicle at which the maximum permissible pressure head is reached;
ρ l is the density of the standard atmosphere at which the maximum permissible pressure head is reached;
ρ i is the current density of the standard atmosphere at flight altitude.
Priority Applications (12)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2000102687/28A RU2161108C1 (en) | 2000-02-07 | 2000-02-07 | Method for orbit injection of payload by multifunctional launch vehicle of combination arrangement with cruise liquid- propellant rocket engine installations (lrei), multifunctional launch vehicle with cruise lpei and method for its development |
DE60038199T DE60038199T2 (en) | 2000-02-07 | 2000-10-13 | A method for improving multifunctional combined launch vehicles with liquid missile engine systems |
EP06014048A EP1837277B1 (en) | 2000-02-07 | 2000-10-13 | Multifunctional launch vehicle of combined scheme with cruise liquid rocket engine systems (LRESs) |
JP2001556741A JP2003521423A (en) | 2000-02-07 | 2000-10-13 | Method of orbiting a payload by a combined-type multifunctional launch vehicle having a cruise liquid rocket engine system (LRES), a combined-function multifunctional launch vehicle having a cruise LRES, and a method for improving the same |
DE60042987T DE60042987D1 (en) | 2000-02-07 | 2000-10-13 | Multifunctional combined launcher with liquid missile propulsion systems |
DE60030264T DE60030264T2 (en) | 2000-02-07 | 2000-10-13 | METHOD FOR BRINGING A USE LOAD INTO ORBIT BY MEANS OF A HYBRID MULTIFUNCTIONAL LOADER KIT EQUIPPED WITH A LIQUID FUEL GRAPHIC DRIVE SYSTEM |
EP06007044A EP1710157B1 (en) | 2000-02-07 | 2000-10-13 | Method for refining multifunctional launch vehicles of combined scheme with cruise liquid rocket engine systems (LRESs) |
PCT/RU2000/000406 WO2001056880A1 (en) | 2000-02-07 | 2000-10-13 | Method for placing a payload into orbit by means of a hybrid multifunction booster rocket equipped with a liquid-fuel rocket propulsion system (lrps), hybrid multifunction booster rocket with cruising lrps and development test therefor |
EP00970360A EP1167188B1 (en) | 2000-02-07 | 2000-10-13 | Method for placing a payload into orbit by means of a hybrid multifunction booster rocket equipped with a liquid-fuel rocket propulsion system (lres) |
US09/972,006 US6581881B2 (en) | 2000-02-07 | 2001-10-09 | Method for placing payload in orbit by multifunctional launch vehicle of combined scheme with cruise liquid rocket engine system (lres), multifunctional launch vehicle of combined scheme with cruise lres and method for refining it |
US10/336,810 US6769651B2 (en) | 2000-02-07 | 2003-01-06 | Method for placing payload in orbit by multifunctional launch vehicle of combined scheme with cruise liquid rocket engine system (lres), multifunctional launch vehicle of combined scheme with cruise lres and method for refining it |
US10/336,813 US6712319B2 (en) | 2000-02-07 | 2003-01-06 | Method for placing payload in orbit by multifunctional launch vehicle of combined scheme with cruise liquid rocket engine system (lres), multifunctional launch vehicle of combined scheme with cruise lres and method of refining it |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2000102687/28A RU2161108C1 (en) | 2000-02-07 | 2000-02-07 | Method for orbit injection of payload by multifunctional launch vehicle of combination arrangement with cruise liquid- propellant rocket engine installations (lrei), multifunctional launch vehicle with cruise lpei and method for its development |
Publications (2)
Publication Number | Publication Date |
---|---|
RU2161108C1 RU2161108C1 (en) | 2000-12-27 |
RU2000102687A true RU2000102687A (en) | 2001-11-27 |
Family
ID=20230175
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
RU2000102687/28A RU2161108C1 (en) | 2000-02-07 | 2000-02-07 | Method for orbit injection of payload by multifunctional launch vehicle of combination arrangement with cruise liquid- propellant rocket engine installations (lrei), multifunctional launch vehicle with cruise lpei and method for its development |
Country Status (6)
Country | Link |
---|---|
US (3) | US6581881B2 (en) |
EP (3) | EP1710157B1 (en) |
JP (1) | JP2003521423A (en) |
DE (3) | DE60038199T2 (en) |
RU (1) | RU2161108C1 (en) |
WO (1) | WO2001056880A1 (en) |
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WO2003004356A2 (en) * | 2001-07-06 | 2003-01-16 | Team Encounter, Llc | Space craft and methods for space travel |
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US7036773B2 (en) * | 2003-08-28 | 2006-05-02 | Ecliptic Enterprises Corporation | Compact external launcher for small space payloads |
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US20080264372A1 (en) * | 2007-03-19 | 2008-10-30 | Sisk David B | Two-stage ignition system |
RU2459971C1 (en) * | 2011-03-23 | 2012-08-27 | Николай Борисович Болотин | Carrier rocket, liquid-propellant rocket engine and roll nozzle block |
RU2464526C1 (en) * | 2011-03-30 | 2012-10-20 | Федеральное государственное унитарное предприятие Государственный космический научно-производственный центр имени М.В. Хруничева | Method of minimising estrangement zone for multistage carrier rocket jettisonable parts |
RU2464207C1 (en) * | 2011-05-13 | 2012-10-20 | Николай Борисович Болотин | Interplanetary rocket |
RU2456215C1 (en) * | 2011-05-25 | 2012-07-20 | Николай Борисович Болотин | Spaceship |
RU2478533C1 (en) * | 2011-08-04 | 2013-04-10 | Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева" | Spaceship head |
RU2481247C1 (en) * | 2011-12-27 | 2013-05-10 | Федеральное государственное унитарное предприятие "Государственный космический научно-производственный центр имени М.В. Хруничева" | Method of placing cluster space rocket in orbit at flight leg before separation of side blocks |
FR2998269B1 (en) * | 2012-11-20 | 2015-01-02 | Centre Nat Detudes Spatiales Cnes | CONNECTING DEVICE BETWEEN A FIRST FLOOR AND A SECOND FLOOR OF A COMPOSITE BELOW A LAUNCHER; LAUNCHER, LAUNCHING METHOD, AND ASSOCIATED ASSEMBLY METHODS |
RU2532445C1 (en) * | 2013-03-13 | 2014-11-10 | ФГУП "Государственный космический научно-производственный центр имени М.В. Хруничева" (ФГУП "ГКНПЦ имени М.В. Хруничева") | Multistage carrier rocket configuration |
WO2017018903A1 (en) * | 2015-07-28 | 2017-02-02 | Общество С Ограниченной Ответственностью "Космокурс" Ооо "Космокурс" | Method for placing a payload into orbit using a carrier rocket |
RU2595092C1 (en) * | 2015-07-28 | 2016-08-20 | Общество с ограниченной ответственностью "КосмоКурс" (ООО "КосмоКурс") | Method for payload orbital injection by carrier rocket |
US10023329B1 (en) * | 2017-03-04 | 2018-07-17 | Othniel Mbamalu | Space vehicle system |
CN107643105B (en) * | 2017-10-30 | 2024-04-02 | 程鹏 | Weather modification rocket launcher detector |
RU2703763C1 (en) * | 2018-09-05 | 2019-10-22 | Акционерное общество "Корпорация "Московский институт теплотехники" (АО "Корпорация "МИТ") | Method of payload delivery to circumterrestrial orbits by means of space launching vehicle |
RU2750343C1 (en) * | 2020-02-28 | 2021-06-28 | Публичное акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева" | Configuration of multi-stage modular launcher rocket |
RU2752727C1 (en) * | 2020-10-08 | 2021-07-30 | Акционерное общество "Государственный научный центр Российской Федерации "Исследовательский центр имени М.В. Келдыша" | Method for operation of propulsion system of first stage of super-heavy launch vehicle to ensure flight safety |
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CN114783673B (en) * | 2022-04-20 | 2023-09-19 | 天津航天长征火箭制造有限公司 | Passive decompression method for carrier rocket cable waterproof layer |
CN115127826B (en) * | 2022-08-30 | 2023-03-03 | 北京星河动力装备科技有限公司 | High-altitude flight test run system of aircraft and engine |
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-
2000
- 2000-02-07 RU RU2000102687/28A patent/RU2161108C1/en not_active IP Right Cessation
- 2000-10-13 EP EP06007044A patent/EP1710157B1/en not_active Expired - Lifetime
- 2000-10-13 DE DE60038199T patent/DE60038199T2/en not_active Expired - Lifetime
- 2000-10-13 JP JP2001556741A patent/JP2003521423A/en active Pending
- 2000-10-13 DE DE60030264T patent/DE60030264T2/en not_active Expired - Lifetime
- 2000-10-13 DE DE60042987T patent/DE60042987D1/en not_active Expired - Lifetime
- 2000-10-13 EP EP06014048A patent/EP1837277B1/en not_active Expired - Lifetime
- 2000-10-13 WO PCT/RU2000/000406 patent/WO2001056880A1/en active IP Right Grant
- 2000-10-13 EP EP00970360A patent/EP1167188B1/en not_active Expired - Lifetime
-
2001
- 2001-10-09 US US09/972,006 patent/US6581881B2/en not_active Expired - Lifetime
-
2003
- 2003-01-06 US US10/336,813 patent/US6712319B2/en not_active Expired - Fee Related
- 2003-01-06 US US10/336,810 patent/US6769651B2/en not_active Expired - Fee Related
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