RU95115377A - Launch vehicle - Google Patents

Launch vehicle

Info

Publication number
RU95115377A
RU95115377A RU95115377/11A RU95115377A RU95115377A RU 95115377 A RU95115377 A RU 95115377A RU 95115377/11 A RU95115377/11 A RU 95115377/11A RU 95115377 A RU95115377 A RU 95115377A RU 95115377 A RU95115377 A RU 95115377A
Authority
RU
Russia
Prior art keywords
launch vehicle
rocket
lines
oxidizer
case
Prior art date
Application number
RU95115377/11A
Other languages
Russian (ru)
Other versions
RU2090461C1 (en
Inventor
А.К. Недайвода
В.К. Карраск
А.П. Пеструхин
Г.Д. Дермичев
Original Assignee
Конструкторское бюро "Салют" филиал Государственного космического научно-производственного центра им.М.В.Хруничева
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Конструкторское бюро "Салют" филиал Государственного космического научно-производственного центра им.М.В.Хруничева filed Critical Конструкторское бюро "Салют" филиал Государственного космического научно-производственного центра им.М.В.Хруничева
Priority to RU95115377/11A priority Critical patent/RU2090461C1/en
Publication of RU95115377A publication Critical patent/RU95115377A/en
Application granted granted Critical
Publication of RU2090461C1 publication Critical patent/RU2090461C1/en

Links

Classifications

    • 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
    • B64G5/00—Ground equipment for vehicles, e.g. starting towers, fuelling arrangements
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Astronomy & Astrophysics (AREA)
  • General Physics & Mathematics (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)
  • Loading And Unloading Of Fuel Tanks Or Ships (AREA)

Abstract

FIELD: rocketry; construction of pneumohydraulic and electric service lines of multi-stage launch vehicle and their connection with ground service lines. SUBSTANCE: oxidizer filling and draining pipes lines 13 and fuel filling and draining pipe lines 18, as well as plug connectors 24 for connection of launch vehicle with ground complex are mounted in separate detachable module located in parallel with axis of case of launch vehicle and connected with case by means of detachable load-bearing unit provided with pushers. Module case is divided by partition into two hermetic chambers: oxidizer chamber 10 and fuel chamber 11. Electric lines 22 and rocket holding engines are mounted on the outside of module case. EFFECT: increased weight of payload due to reduced weight of structural members of storages.

Claims (1)

Изобретение относится к ракетной технике, а более конкретно к конструкции пневмогидравлических и электрических коммуникаций многоступенчатого ракетоносителя и их связей с заправочно-дренажными и электрокоммуникациями наземного комплекса. Целью изобретения является увеличение выводимого веса полезной нагрузки за счет уменьшения конструктивного веса ступеней ракетоносителя. Для этого заправочно-дренажные трубопроводы окислителя 13 и заправочно-дренажные трубопроводы горючего 18, а также штепсельные разъемы 24 для связи ракетоносителя с наземным комплексом смонтированы в отдельном расположенном параллельно оси корпуса ракетоносителя 1 отделяемом модуле, связанном с корпусом ракетоносителя разъемными силовыми узлами с толкателями. Корпус модуля разделен перегородкой на две герметичные полости - полость окислителя 10 и полость горючего 11. Снаружи корпуса модуля размещены электрокоммуникации 22 и ракетные двигатели увода.The invention relates to rocket technology, and more specifically to the design of pneumohydraulic and electrical communications of a multi-stage carrier rocket and their connections with refueling and drainage and electrical communications of the ground complex. The aim of the invention is to increase the output payload weight by reducing the structural weight of the stages of the launch vehicle. For this, the oxidizer refueling and drainage pipelines 13 and the fuel 18 refueling and drainage pipelines, as well as the plug connectors 24 for connecting the rocket launcher to the ground complex, are mounted in a separate detachable module located parallel to the axis of the rocket launcher 1 and connected to the rocket launcher by detachable power units with pushers. The module case is divided by a partition into two airtight cavities - the oxidizer cavity 10 and the fuel cavity 11. Outside of the module case there are electrical communications 22 and rocket propulsion engines.
RU95115377/11A 1995-08-31 1995-08-31 Launch vehicle RU2090461C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU95115377/11A RU2090461C1 (en) 1995-08-31 1995-08-31 Launch vehicle

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU95115377/11A RU2090461C1 (en) 1995-08-31 1995-08-31 Launch vehicle

Publications (2)

Publication Number Publication Date
RU95115377A true RU95115377A (en) 1996-12-10
RU2090461C1 RU2090461C1 (en) 1997-09-20

Family

ID=20171748

Family Applications (1)

Application Number Title Priority Date Filing Date
RU95115377/11A RU2090461C1 (en) 1995-08-31 1995-08-31 Launch vehicle

Country Status (1)

Country Link
RU (1) RU2090461C1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111301716A (en) * 2020-03-23 2020-06-19 北京中科宇航技术有限公司 Power supply and distribution system of multistage carrier rocket

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2446081C1 (en) * 2010-08-06 2012-03-27 Открытое Акционерное Общество "Государственный Ракетный Центр Имени Академика В.П. Макеева" Method rocket launching
CN106314829B (en) * 2015-06-19 2018-11-02 北京强度环境研究所 Simulation core grade and assembly manipulation platform for the experiment of large-scale boost motor
CN113916053A (en) * 2021-10-28 2022-01-11 航天科工火箭技术有限公司 Adaptive design of no-service tower and swing rod of low-temperature rocket power system

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111301716A (en) * 2020-03-23 2020-06-19 北京中科宇航技术有限公司 Power supply and distribution system of multistage carrier rocket
CN111301716B (en) * 2020-03-23 2021-09-14 北京中科宇航技术有限公司 Power supply and distribution system of multistage carrier rocket

Also Published As

Publication number Publication date
RU2090461C1 (en) 1997-09-20

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Legal Events

Date Code Title Description
MM4A The patent is invalid due to non-payment of fees

Effective date: 20050901