WO2001056880A1 - Procede de mise en orbite de charge utile par une fusee de lancement polyvalente a schema combine muni de systemes de moteurs-fusees a propergol liquide (mfpl), fusee de lancement polyvalente a schema combine et procede de mise au point correspondant - Google Patents
Procede de mise en orbite de charge utile par une fusee de lancement polyvalente a schema combine muni de systemes de moteurs-fusees a propergol liquide (mfpl), fusee de lancement polyvalente a schema combine et procede de mise au point correspondant Download PDFInfo
- Publication number
- WO2001056880A1 WO2001056880A1 PCT/RU2000/000406 RU0000406W WO0156880A1 WO 2001056880 A1 WO2001056880 A1 WO 2001056880A1 RU 0000406 W RU0000406 W RU 0000406W WO 0156880 A1 WO0156880 A1 WO 0156880A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- zhρdu
- ρaκeτnyχ
- blοκοv
- tsenτρalnοgο
- blοκa
- Prior art date
Links
- 238000000034 method Methods 0.000 title claims abstract description 22
- 239000000446 fuel Substances 0.000 title abstract description 14
- 238000011981 development test Methods 0.000 title abstract 2
- 230000001133 acceleration Effects 0.000 claims description 5
- 238000004519 manufacturing process Methods 0.000 claims description 5
- 239000000725 suspension Substances 0.000 claims description 4
- 238000009825 accumulation Methods 0.000 claims description 3
- 230000033228 biological regulation Effects 0.000 claims description 3
- 238000000926 separation method Methods 0.000 claims description 3
- 230000003442 weekly effect Effects 0.000 claims description 3
- 235000015842 Hesperis Nutrition 0.000 abstract description 4
- 235000012633 Iberis amara Nutrition 0.000 abstract description 4
- 238000005516 engineering process Methods 0.000 abstract description 3
- 238000012360 testing method Methods 0.000 abstract description 3
- 239000000969 carrier Substances 0.000 description 7
- 238000012545 processing Methods 0.000 description 6
- 239000007788 liquid Substances 0.000 description 4
- 238000007599 discharging Methods 0.000 description 3
- 239000002828 fuel tank Substances 0.000 description 3
- 238000002347 injection Methods 0.000 description 3
- 239000007924 injection Substances 0.000 description 3
- 239000002253 acid Substances 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 239000007800 oxidant agent Substances 0.000 description 2
- 238000005192 partition Methods 0.000 description 2
- 239000003380 propellant Substances 0.000 description 2
- 239000004449 solid propellant Substances 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 244000208874 Althaea officinalis Species 0.000 description 1
- 235000006576 Althaea officinalis Nutrition 0.000 description 1
- 239000004215 Carbon black (E152) Substances 0.000 description 1
- 241000208202 Linaceae Species 0.000 description 1
- 235000004431 Linum usitatissimum Nutrition 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 238000009395 breeding Methods 0.000 description 1
- 230000001488 breeding effect Effects 0.000 description 1
- JLQUFIHWVLZVTJ-UHFFFAOYSA-N carbosulfan Chemical compound CCCCN(CCCC)SN(C)C(=O)OC1=CC=CC2=C1OC(C)(C)C2 JLQUFIHWVLZVTJ-UHFFFAOYSA-N 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
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- 230000000694 effects Effects 0.000 description 1
- VJYFKVYYMZPMAB-UHFFFAOYSA-N ethoprophos Chemical compound CCCSP(=O)(OCC)SCCC VJYFKVYYMZPMAB-UHFFFAOYSA-N 0.000 description 1
- 239000010437 gem Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 229930195733 hydrocarbon Natural products 0.000 description 1
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- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 1
- 229910052721 tungsten Inorganic materials 0.000 description 1
- 239000010937 tungsten Substances 0.000 description 1
- 230000003612 virological effect Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/74—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant
- F02K9/76—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant with another rocket-engine plant; Multistage rocket-engine plants
- F02K9/766—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant with another rocket-engine plant; Multistage rocket-engine plants with liquid propellant
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/002—Launch systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/242—Orbits and trajectories
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/401—Liquid propellant rocket engines
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/403—Solid propellant rocket engines
- B64G1/404—Hybrid rocket engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/20—Actively adjusting tip-clearance
- F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/242—Orbits and trajectories
- B64G1/2427—Transfer orbits
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/402—Propellant tanks; Feeding propellants
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/641—Interstage or payload connectors
Definitions
- the invention is not available in the field of missile and physical equipment and may be subject to a disruption to the system. Suitable for discharging on a clean surface of a well-designed and non-removable spacecraft, as well as other devices for various purposes.
- THE PREVIOUS VIRAL DEVELOPMENT OF THE TECHNOLOGY MODERN DEVELOPMENT OF THE SPACE TECHNOLOGY requires the creation of carrier carriers. a variety of supplies and equipment for various purposes and masses on the underground devices with a height of 180 ... 34000 km. Due to the variety of tasks, there is a need for the availability of many functional carriers. It is possible to carry out these tasks in a basic or other basic task. In the best way they satisfy this requirement of the booster-carriers of the combined circuit with a variable lower stage. Due to the fact that the prop- The advantages of a mixed carrier in the highest degree are found when one of the most advantageous units is at a low cost. Combined circuitry carriers also make it possible to optimize the launch of a space device for an ambient earth.
- the carrier-"5-carrier has a lower popular package missile units, including a central propellant missile unit with a light rail and two lateral missile units with a solid propellant solid propellant engine ( ⁇ ⁇ ). Two variants of the central unit and small variants of the larger ones are acceptable for the use of multiple units.
- the accelerated rocket unit and the main unit with the useful load are connected to the central missile unit for the tandem circuit.
- ne ⁇ b ⁇ dim ⁇ is ⁇ l- z ⁇ va ⁇ d ⁇ ug ⁇ y central block with a different railroad thirst.
- ⁇ i5 is ⁇ lz ⁇ vanii ⁇ i ⁇ ichn ⁇ y ⁇ ns ⁇ u ⁇ tsii ⁇ a ⁇ e ⁇ y-n ⁇ si ⁇ elya ⁇ mbini ⁇ vann ⁇ y s ⁇ emy unchanged tsen ⁇ aln ⁇ g ⁇ ⁇ a ⁇ e ⁇ n ⁇ g ⁇ bl ⁇ a m ⁇ zhn ⁇ 1.5 ⁇ aza izmenya ⁇ weight vyv ⁇ dim ⁇ y ⁇ lezn ⁇ y nag ⁇ uz ⁇ i, ch ⁇ yavlyae ⁇ sya ⁇ a ⁇ a ⁇ e ⁇ nym dia ⁇ az ⁇ n ⁇ m mass change ⁇ lezn ⁇ y nag ⁇ uz ⁇ i for s ⁇ v ⁇ emenn ⁇ y ⁇ a ⁇ e ⁇ y-n ⁇ si ⁇ elya ⁇ mbini ⁇ vann ⁇ y s ⁇ emy.
- the host carrier needs a separate process 0 for the central and external partitions of all the options, and it is not necessary Because in the case of a carrier, various types of launcher are used; Otherwise, the operation of the carrier rocket is possible only after 5 processing operations as a minimum of a one-time central and two-sided service.
- Susches ⁇ vennym ned ⁇ s ⁇ a ⁇ m vse ⁇ ⁇ a ⁇ e ⁇ -n ⁇ si ⁇ eley ⁇ mbini ⁇ - vann ⁇ y s ⁇ emy is ⁇ lzuyuschi ⁇ b ⁇ vye ⁇ a ⁇ e ⁇ nye bl ⁇ i with ⁇ D ⁇ , yavlyae ⁇ sya ⁇ vyshenn ⁇ e e ⁇ l ⁇ giches ⁇ e zag ⁇ yaznenie a ⁇ m ⁇ s ⁇ e ⁇ y s ⁇ edineniyami ⁇ l ⁇ a, ⁇ ye s ⁇ de ⁇ zha ⁇ sya in b ⁇ lyni ⁇ ⁇ liches ⁇ va ⁇ in ⁇ du ⁇ a ⁇ sg ⁇ aniya ⁇ vo ⁇ d ⁇ g ⁇ ⁇ liva.
- the main engines of the accelerated unit include after the completion of the operation of the central unit of the missile.
- a complete package is a uniform one for all missile units, which significantly reduces the cost of loading useful load on the site. However, it is not in full use of the energy features of the lower charge unit of the portable devices, since there is no charge for the
- the carrier contains the lower part package of the multi-engine flash units, including the central and integrated side panels and the optional parts for it.
- the carrier is equipped with a fuel injection system between the side and central missile units. It is proposed that the components of the carrier and the method of discharging useful load on the ground are described in the patent.
- the lower part package of the missile units includes the central and integrated to it four-sided missile units.
- the central unit and the tandem unit are reserved for the transitional unit, the dispersed missile unit and the main unit with a useful
- the carrier is equipped with a system for storing lateral missile units in the central unit.
- Lateral missile units are equipped with main processors.
- the centric missile unit has larger dimensions and weight compared to the side missile units and carries more fuel, which makes it longer.
- V is the current velocity of the carrier rocket
- k - dynamic coefficient equal 0.95 ... 1.05
- V / - the speed of the carrier rocket, and if it is quickly reached, the vehicle is immediately available for fast delivery; r ⁇ - accessibility of a standard engine, but quick access to the weekly 15 acceptable speed; ⁇ , - the current density of the standard aircraft at a height of flight.
- the multiplexer has a commercially-available combi circuit with a ready-to-install receiver, which is not removable.
- ZhDU including the central and integrated lateral missile units and tandem attached to the central unit of the transitional unit
- the carrier can be equipped with two side rocket launchers
- the essence of the invention is included in that, having formatted in the processor-carrier of the combined circuit of the lower part of the package in the same package thirteen
- n ⁇ si ⁇ elya s ⁇ s ⁇ n ⁇ g ⁇ na ⁇ a further increase its s ⁇ s ⁇ i ⁇ susches ⁇ vlyayu ⁇ ⁇ eguli ⁇ vaniem ⁇ yagi ma ⁇ shevy ⁇ ZH ⁇ DU b ⁇ vy ⁇ ⁇ a ⁇ e ⁇ ny ⁇ bl ⁇ v in ⁇ edela ⁇ 0.3 ... 1, 0 ⁇ n ⁇ minaln ⁇ y ⁇ yagi of usl ⁇ viya not ⁇ evysheniya ⁇ edeln ⁇ d ⁇ us ⁇ im ⁇ g ⁇ s ⁇ s ⁇ n ⁇ g ⁇ na ⁇ a, vyde ⁇ zhivaya zayavlenn ⁇ e s ⁇ n ⁇ shenie (1).
- Optimal for the operation of a carrier rocket of a combined circuit is not an increase in the air when it is running on an air from a direct air ... 1700000.
- FIG. 1 The general view of the proposed heavy carrier is shown.
- the heavy-duty carrier contains the lower part package 1 of the inclusive units, including the integral 2 and the integral part of the three-port power adapter.
- Missile units that have identical fuel tanks 4 and 5.
- Fuel tank 4; each missile unit 2 and 3 has a capacity of 46 m 3 and can accommodate 36.5 tons.
- the fuel tank 5 of each missile unit 2 and 3 has a volume of 90 m and accommodates up to 96 tons of liquid acid.
- Central missile unit 2
- the side rocket units 3 are equipped with an adjustable weighted rail 7.
- Central and lateral missile units are equipped
- the front WAIT 6 central unit is redundant in the dual suspension 8 with two intermittent two-way air vents. Downloading areas divide the central block 2 on the four vertical sectors. Lateral missiles 3 are mounted on the central
- Headed railways 7 lateral rocket units are stored in the data card
- the download speed of the railroad is waiting for 7 lateral missile units in parallel with the corresponding downloads of the railroad is waiting for 6 central shopping carts.
- the data for the suspensions 8 and 9 are shown in Fig. 4
- the unit is tandemly connected to the interconnect compartment 13, the multiple accessory unit 14 and the main unit 15;
- the proposed invention makes use of the standardized
- the method of discharging the load to the ground will be 26 ... 28 t with a heavy load.
- the sequence of loading a useful load using a carrier circuit of the combined circuit shown in Fig. 7 includes the following:
- the lower part package of 1 missile unit is connected by connecting to the central part of the unit 2 18
- the central missile unit also connects the tandem circuitry to an unloadable solid-state unit 14 with a light-weight solid load (light)
- ⁇ i ⁇ ichny g ⁇ a ⁇ i ⁇ changes ⁇ yagi ⁇ (ma ⁇ shev ⁇ y ZH ⁇ DU tsen ⁇ aln ⁇ g ⁇ ⁇ a ⁇ e ⁇ n ⁇ g ⁇ bl ⁇ a ⁇ azan on ⁇ ig.8 on ⁇ y ⁇ a ⁇ zhe ⁇ iveden ⁇ 5 change ⁇ d ⁇ ln ⁇ g ⁇ us ⁇ eniya ⁇ ⁇ - ⁇ a ⁇ e ⁇ y n ⁇ si ⁇ elya.
- ⁇ i ⁇ ichny g ⁇ a ⁇ i ⁇ changes ⁇ yagi ⁇ (ma ⁇ shevy ⁇ ZH ⁇ DU 7 b ⁇ vy ⁇ ⁇ a ⁇ e ⁇ ny ⁇ bl ⁇ v ⁇ i d ⁇ s ⁇ izhenii 0 ⁇ edeln ⁇ d ⁇ us ⁇ im ⁇ y value ⁇ d ⁇ ln ⁇ g ⁇ us ⁇ eniya ⁇ ⁇ ⁇ azan on ⁇ ig.9.
- the processing of the host carrier is carried out as follows. ⁇ ybi ⁇ ayu ⁇ gaba ⁇ i ⁇ n ⁇ -mass ⁇ vye ⁇ a ⁇ a ⁇ e ⁇ is ⁇ i ⁇ i tsen ⁇ aln ⁇ g ⁇ , and b ⁇ vy ⁇ ⁇ azg ⁇ nny ⁇ ⁇ a ⁇ e ⁇ ny ⁇ bl ⁇ v and ⁇ yag ⁇ vye ⁇ a ⁇ a ⁇ e ⁇ is ⁇ i ⁇ i i ⁇ ma ⁇ shevy ⁇ ZH ⁇ DU, ⁇ i e ⁇ m for tsen ⁇ aln ⁇ g ⁇ and b ⁇ vy ⁇ ⁇ a ⁇ e ⁇ ny ⁇ bl ⁇ v zadayu ⁇ ⁇ dina ⁇ vye gaba ⁇ i ⁇ n ⁇ -mass ⁇ vye ⁇ a ⁇ a ⁇ e ⁇ is ⁇ i ⁇ i and ⁇ yagu ma ⁇ shevy ⁇ ZH ⁇ DU, ⁇ bes ⁇ echivayuschie is ⁇ lz ⁇ vanie
- the central flash unit is tested as part of the tandem carrier circuit and starts to use it in the tungsten carrier circuit for easy access This allows you to quickly collect statistical data to ensure the reliability of production.
- n ⁇ si ⁇ ele ⁇ andemn ⁇ y s ⁇ emy ⁇ a ⁇ e ⁇ ny bl ⁇ is ⁇ lzuyu ⁇ ⁇ i ⁇ mi ⁇ vanii nizhneg ⁇ ⁇ libl ⁇ chn ⁇ g ⁇ ⁇ a ⁇ e ⁇ a ⁇ a ⁇ e ⁇ ny ⁇ bl ⁇ v ⁇ a ⁇ e ⁇ y-n ⁇ si ⁇ elya ⁇ mbini ⁇ van- n ⁇ y s ⁇ emy, va ⁇ ian ⁇ y ⁇ y ⁇ ⁇ azany on ⁇ ig.1 and 5, with ⁇ vedeniem lo ⁇ n ⁇ - ⁇ ns ⁇ u ⁇ s ⁇ i ⁇ is ⁇ y ⁇ any enlarged v ⁇ emenem ⁇ ab ⁇ y ma ⁇ shev ⁇ y ZH ⁇ DU tsen ⁇ aln ⁇ g ⁇ ⁇ a ⁇ e ⁇ n ⁇ g ⁇ bl ⁇ a ⁇ n ⁇ si ⁇ eln ⁇ ma ⁇ shevy ⁇ ZH ⁇ DU b ⁇ vy ⁇ missile units.
Description
Claims
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2001556741A JP2003521423A (ja) | 2000-02-07 | 2000-10-13 | 巡航液体ロケットエンジンシステム(lres)を有する結合式構造の多機能打ち上げロケットによりペイロードを軌道に乗せる方法と、巡航lresを有する結合式構造の多機能打ち上げロケットと、これを改善する方法 |
DE60030264T DE60030264T2 (de) | 2000-02-07 | 2000-10-13 | Verfahren um eine nutzlast in orbit zu bringen mittels einer hybriden multifunktionellen mit einem flüssigbrennstoffraketenantriebssystem ausgerüsteten trägerrakete |
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 (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2000102687/28A RU2161108C1 (ru) | 2000-02-07 | 2000-02-07 | Способ выведения на орбиту полезной нагрузки многофункциональной ракетой-носителем комбинированной схемы с маршевыми жидкостными ракетными двигательными установками (жрду), многофункциональная ракета-носитель комбинированной схемы с маршевыми жрду и способ ее отработки |
RU2000102687 | 2000-02-07 |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US09/972,006 Continuation 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 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2001056880A1 true WO2001056880A1 (fr) | 2001-08-09 |
Family
ID=20230175
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/RU2000/000406 WO2001056880A1 (fr) | 2000-02-07 | 2000-10-13 | Procede de mise en orbite de charge utile par une fusee de lancement polyvalente a schema combine muni de systemes de moteurs-fusees a propergol liquide (mfpl), fusee de lancement polyvalente a schema combine et procede de mise au point correspondant |
Country Status (6)
Country | Link |
---|---|
US (3) | US6581881B2 (ru) |
EP (3) | EP1167188B1 (ru) |
JP (1) | JP2003521423A (ru) |
DE (3) | DE60042987D1 (ru) |
RU (1) | RU2161108C1 (ru) |
WO (1) | WO2001056880A1 (ru) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6581881B2 (en) | 2000-02-07 | 2003-06-24 | Gosudarstvenny Kosmichesky Nauchno-Proizvodstvenny Tsentr Im. M. V. | 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 |
Families Citing this family (25)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2003004356A2 (en) * | 2001-07-06 | 2003-01-16 | Team Encounter, Llc | Space craft and methods for space travel |
US20030052232A1 (en) * | 2001-09-17 | 2003-03-20 | Hall Allison Earl | Space transportation system |
US7036773B2 (en) * | 2003-08-28 | 2006-05-02 | Ecliptic Enterprises Corporation | Compact external launcher for small space payloads |
US7669406B2 (en) * | 2006-02-03 | 2010-03-02 | General Electric Company | Compact, low pressure-drop shock-driven combustor and rocket booster, pulse detonation based supersonic propulsion system employing the same |
US20080264372A1 (en) * | 2007-03-19 | 2008-10-30 | Sisk David B | Two-stage ignition system |
RU2459971C1 (ru) * | 2011-03-23 | 2012-08-27 | Николай Борисович Болотин | Ракета-носитель, жидкостный ракетный двигатель и блок сопел крена |
RU2464526C1 (ru) * | 2011-03-30 | 2012-10-20 | Федеральное государственное унитарное предприятие Государственный космический научно-производственный центр имени М.В. Хруничева | Способ минимизации зон отчуждения для отделяемых частей многоступенчатой ракеты-носителя |
RU2464207C1 (ru) * | 2011-05-13 | 2012-10-20 | Николай Борисович Болотин | Ракета для межпланетных полетов |
RU2456215C1 (ru) * | 2011-05-25 | 2012-07-20 | Николай Борисович Болотин | Звездолет |
RU2478533C1 (ru) * | 2011-08-04 | 2013-04-10 | Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева" | Космическая головная часть |
RU2481247C1 (ru) * | 2011-12-27 | 2013-05-10 | Федеральное государственное унитарное предприятие "Государственный космический научно-производственный центр имени М.В. Хруничева" | Способ выведения на орбиту ракеты космического назначения пакетной схемы на участке полета до отделения боковых блоков |
FR2998269B1 (fr) * | 2012-11-20 | 2015-01-02 | Centre Nat Detudes Spatiales Cnes | Dispositif de liaison entre un premier etage et un deuxieme etage d'un composite inferieur d'un lanceur ; lanceur, procede de lancement et procedes d'assemblage associes |
RU2532445C1 (ru) * | 2013-03-13 | 2014-11-10 | ФГУП "Государственный космический научно-производственный центр имени М.В. Хруничева" (ФГУП "ГКНПЦ имени М.В. Хруничева") | Компоновка многоступенчатой ракеты-носителя |
RU2595092C1 (ru) * | 2015-07-28 | 2016-08-20 | Общество с ограниченной ответственностью "КосмоКурс" (ООО "КосмоКурс") | Способ выведения на орбиту полезной нагрузки ракетой-носителем |
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- 2000-10-13 JP JP2001556741A patent/JP2003521423A/ja active Pending
- 2000-10-13 DE DE60042987T patent/DE60042987D1/de not_active Expired - Lifetime
- 2000-10-13 WO PCT/RU2000/000406 patent/WO2001056880A1/ru active IP Right Grant
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Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6581881B2 (en) | 2000-02-07 | 2003-06-24 | Gosudarstvenny Kosmichesky Nauchno-Proizvodstvenny Tsentr Im. M. V. | 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 |
US6712319B2 (en) | 2000-02-07 | 2004-03-30 | Gosudarstvenny Kosmichesky Nauchno-Proizvodstvenny Tsentr Tm. M.V. Khrunicheva | 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 |
US6769651B2 (en) | 2000-02-07 | 2004-08-03 | Federalnoe Gosudarstvennoe Unitarnoe Predpriyatie Gosudarstvenny Kosmichesky Nauchno-Proizvodstvenny Tsentr Im.M.V. Krunicheva | 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 |
Also Published As
Publication number | Publication date |
---|---|
JP2003521423A (ja) | 2003-07-15 |
US6712319B2 (en) | 2004-03-30 |
EP1167188A1 (en) | 2002-01-02 |
DE60042987D1 (de) | 2009-10-29 |
US6769651B2 (en) | 2004-08-03 |
EP1837277B1 (en) | 2009-09-16 |
DE60030264T2 (de) | 2007-09-20 |
DE60038199T2 (de) | 2009-02-26 |
EP1167188A4 (en) | 2005-08-03 |
RU2161108C1 (ru) | 2000-12-27 |
EP1837277A2 (en) | 2007-09-26 |
US6581881B2 (en) | 2003-06-24 |
EP1167188B1 (en) | 2006-08-23 |
EP1837277A3 (en) | 2007-10-03 |
US20020060271A1 (en) | 2002-05-23 |
US20030102409A1 (en) | 2003-06-05 |
US20030098397A1 (en) | 2003-05-29 |
EP1710157A1 (en) | 2006-10-11 |
DE60030264D1 (de) | 2006-10-05 |
DE60038199D1 (de) | 2008-04-10 |
EP1710157B1 (en) | 2008-02-27 |
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