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WO2016159806A1 - Soft landing system for a reusable rocket stage - Google Patents

Soft landing system for a reusable rocket stage Download PDF

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Publication number
WO2016159806A1
WO2016159806A1 PCT/RU2015/000185 RU2015000185W WO2016159806A1 WO 2016159806 A1 WO2016159806 A1 WO 2016159806A1 RU 2015000185 W RU2015000185 W RU 2015000185W WO 2016159806 A1 WO2016159806 A1 WO 2016159806A1
Authority
WO
WIPO (PCT)
Prior art keywords
platform
stage
engines
landing
rocket
Prior art date
Legal status (The legal status 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 status listed.)
Ceased
Application number
PCT/RU2015/000185
Other languages
French (fr)
Russian (ru)
Inventor
Сергей Петрович ЖДАНЮК
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to PCT/RU2015/000185 priority Critical patent/WO2016159806A1/en
Priority to RU2017132110A priority patent/RU2017132110A/en
Publication of WO2016159806A1 publication Critical patent/WO2016159806A1/en
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • 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
    • B64G1/62—Systems for re-entry into the earth's atmosphere; Retarding or landing devices
    • B64G1/625—Landing devices; Undercarriages
    • 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

Definitions

  • the invention relates to space technology.
  • the soft landing system of a reusable rocket stage contains rocket engines and a soft platform for the implementation of the landing itself.
  • a known landing system is the landing system of the first stage of the Falcon rocket, which is carried out by means of mechanical supports on an autonomous floating platform.
  • Landing steps using mechanical supports on a rigid surface has several drawbacks. Namely: the possibility of tilting the launch vehicle stage under odd conditions of its landing in part of the landing speed, its vertical and horizontal components, surface irregularities (recesses and projections), as well as random gusts wind A lot of effort is expended to keep the platform itself in an equilibrium position, to obtain the most even surface.
  • the presence of mechanisms on the step in the form of supports increases the weight of the step, which leads to an increase in fuel consumption.
  • the aim of the invention is to eliminate these disadvantages.
  • the platform consists of a soft cushioning material.
  • a soft cushioning material For example, polystyrene foam (foam).
  • the foam blocks are stacked in rows, laid with a synthetic mesh. Several layers are stacked on top of each other and make up the platform.
  • the number of foam layers, as well as the dimensions of the platform itself are determined and depend on the weight of the landing stage and the accuracy of the landing.
  • the engines In order for the platform not to burn from the flames of the working engines, the engines must be turned off at a certain optimal distance from the platform.
  • the height at which the stage motors are turned off should be as low as possible, but nonetheless one at which the flame from the engines would not fall on the platform.
  • the platform can be located both on land and at sea.

Landscapes

  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Astronomy & Astrophysics (AREA)
  • General Physics & Mathematics (AREA)
  • Vibration Dampers (AREA)
  • Toys (AREA)

Abstract

The invention relates to rocket and space technology. A reusable rocket stage, after separating from a carrier rocket, uses engines as a means of braking, and descends to a landing point, where a platform is located. Hovering at a height of approximately 15-20 meters above the platform, the engines turn off and the stage free-falls onto the platform. The integrity of the descending stage is maintained by virtue of shock-absorbing characteristics of the platform, which dampens the momentum of the fall. The present landing method makes it possible to avoid a series of negative factors which are inevitable in traditional vertical landing, such as the effects of weather and the malfunctioning of the stage engines, and also eliminates the need for any mechanisms in the form of supports, thus decreasing the weight of the carrier rocket.

Description

СИСТЕМА МЯГКОЙ ПОСАДКИ МНОГОРАЗОВОЙ РАКЕТНОЙ СТУПЕНИ  SOFT LANDING SYSTEM FOR REUSABLE MISSILES

Изобретение относится к космической технике .Система мягкой посадки многоразовой ракетной ступени содержит в себе ракетные двигатели и мягкую платформу для осуществления самой посадки .Нет ни парашютной системы ни каких бы то ни было механических опор как на самой ступени , так и на платформе .И это принципиальное отличие данной системы от других. Торможением двигателей достигается зависание ступени в The invention relates to space technology. The soft landing system of a reusable rocket stage contains rocket engines and a soft platform for the implementation of the landing itself. There is no parachute system, no mechanical supports of any kind, either at the stage itself or on the platform. And this is fundamental difference of this system from others. Deceleration of the engine is achieved by hanging the stage in

определенной точке на определенной высоте над платформой .После этого двигатели выключаются и ступень спокойно падает на платформу a certain point at a certain height above the platform. After that, the engines are turned off and the stage quietly falls on the platform

.Целостность и сохранность ступени достигается мягкостью самой .Integrity and safety of the stage is achieved by the softness itself.

платформы .Т.е. платформа амортизирует и тем самым гасит импульс падения. Выключение двигателей над платформой обусловлено platforms .Te the platform absorbs and thereby dampens the momentum of the fall. Shutdown engines above the platform due to

необходимостью предохранить платформу от попадания огня от работающих двигателей . the need to protect the platform from fire from operating engines.

Известна система посадки -это система посадки первой ступени ракеты «Falcon», которая осуществляется при помощи механических опор на автономную плавучую платформу . A known landing system is the landing system of the first stage of the Falcon rocket, which is carried out by means of mechanical supports on an autonomous floating platform.

(http://rbcdaily.ru/industry/562949993665236). А так же другие системы посадки , см.патент РФ 2497715 и патент US8678321 В2.  (http://rbcdaily.ru/industry/562949993665236). As well as other landing systems, see RF patent 2497715 and patent US8678321 B2.

Посадка ступени с помощью механических опор на жесткую поверхность имеет ряд недостатков .А именно : возможность опрокидывания ступени ракеты-носителя при нерасчетных условиях ее посадки в части скорости посадки, ее вертикальной и горизонтальной составляющих, неровностей поверхности (углублений и выступов), а также случайных порывов ветра. Затрачивается масса усилий для удержания самой платформы в равновесном положении , для получения максимально ровной поверхности .Наличие на ступени механизмов в виде опор - увеличивает вес ступени , что ведет к увеличению расхода топлива . Landing steps using mechanical supports on a rigid surface has several drawbacks. Namely: the possibility of tilting the launch vehicle stage under odd conditions of its landing in part of the landing speed, its vertical and horizontal components, surface irregularities (recesses and projections), as well as random gusts wind A lot of effort is expended to keep the platform itself in an equilibrium position, to obtain the most even surface. The presence of mechanisms on the step in the form of supports increases the weight of the step, which leads to an increase in fuel consumption.

Целью изобретения является устранение указанных недостатков. The aim of the invention is to eliminate these disadvantages.

Указанная цель достигается конструкцией платформы и способом This goal is achieved by the design of the platform and the way

приземления .Платформа состоит из мягкого амортизирующего материала .Например из пенополистирола (пенопласта)Блоки пенопласта укладываются рядами , прокладываются синтетической сеткой .Несколько слоев уложенных друг на друга и составляют платформу . Landings. The platform consists of a soft cushioning material. For example, polystyrene foam (foam). The foam blocks are stacked in rows, laid with a synthetic mesh. Several layers are stacked on top of each other and make up the platform.

ЗАМЕНЯЮ ИЙ ЛИСТ ПРАВИЛО 26 Количество слоев пенопласта ,а так же размеры самой платформы определяются и зависят от массы приземляемой ступени и точности приземления . Что бы платформа не сгорела от пламени работающих двигателей , двигатели должны быть выключены на некотором юптимальном расстоянии от платформы. Высота на которой отключаются двигатели ступени должна быть как можно ниже , но тем не менее такая, при которой пламя от двигателей не попадало бы на платформу .После чего происходит свободное падение ступени на платформу. Платформа может располагаться как на суше так и на море . REPLACE THE SHEET RULE 26 The number of foam layers, as well as the dimensions of the platform itself are determined and depend on the weight of the landing stage and the accuracy of the landing. In order for the platform not to burn from the flames of the working engines, the engines must be turned off at a certain optimal distance from the platform. The height at which the stage motors are turned off should be as low as possible, but nonetheless one at which the flame from the engines would not fall on the platform. The platform can be located both on land and at sea.

ЗАМЕНЯЮЩИЙ ЛИСТ (ПРАВИЛО 26) SUBSTITUTE SHEET (RULE 26)

Claims

ФОРМУЛА ИЗ ОБРЕТЕНИЯ  CLAIM Система мягкой посадки многоразовой ракетн ой ступ ени , которая содержит ракетные двигатели , «мягкую» The system of soft landing reusable rocket th stage, which contains rocket engines, "soft" амортизирующую платформу и способ приземления , заключающийся в падении ступени на платф орму с выключенными двигателями с н еб ольшой высоты . shock-absorbing platform and landing method, which consists in dropping a step onto the platform with the engines off from a high altitude. ЗАМЕНЯЮЩИЙ ЛИСТ (ПРАВИЛО 26) SUBSTITUTE SHEET (RULE 26)
PCT/RU2015/000185 2015-03-27 2015-03-27 Soft landing system for a reusable rocket stage Ceased WO2016159806A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
PCT/RU2015/000185 WO2016159806A1 (en) 2015-03-27 2015-03-27 Soft landing system for a reusable rocket stage
RU2017132110A RU2017132110A (en) 2015-03-27 2015-03-27 Soft landing system reusable rocket stage

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/RU2015/000185 WO2016159806A1 (en) 2015-03-27 2015-03-27 Soft landing system for a reusable rocket stage

Publications (1)

Publication Number Publication Date
WO2016159806A1 true WO2016159806A1 (en) 2016-10-06

Family

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Family Applications (1)

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PCT/RU2015/000185 Ceased WO2016159806A1 (en) 2015-03-27 2015-03-27 Soft landing system for a reusable rocket stage

Country Status (2)

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RU (1) RU2017132110A (en)
WO (1) WO2016159806A1 (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2740525C1 (en) * 2020-05-22 2021-01-15 Акционерное общество "Центральный научно-исследовательский институт машиностроения" (АО "ЦНИИмаш") Device for landing of return stage of carrier rocket
CN113739648A (en) * 2021-08-17 2021-12-03 航天科工火箭技术有限公司 Reusable technology demonstration verification rocket landing detection method, system and equipment
RU2781713C1 (en) * 2022-02-25 2022-10-17 Владимир Федорович Петрищев Landing device for launch return stage and method for its landing

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5667167A (en) * 1994-09-02 1997-09-16 Kistler Aerospace Corporation Methods and apparatus for reusable launch platform and reusable spacecraft
RU2131383C1 (en) * 1998-02-16 1999-06-10 Акционерное общество открытого типа "Ракетно-космическая корпорация "Энергия" им.С.П.Королева" Take-off and landing spacecraft
RU2215673C2 (en) * 2001-10-03 2003-11-10 Шуликов Константин Владимирович Aerospace launching complex mars
US8047472B1 (en) * 2006-06-06 2011-11-01 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Ram booster

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5667167A (en) * 1994-09-02 1997-09-16 Kistler Aerospace Corporation Methods and apparatus for reusable launch platform and reusable spacecraft
RU2131383C1 (en) * 1998-02-16 1999-06-10 Акционерное общество открытого типа "Ракетно-космическая корпорация "Энергия" им.С.П.Королева" Take-off and landing spacecraft
RU2215673C2 (en) * 2001-10-03 2003-11-10 Шуликов Константин Владимирович Aerospace launching complex mars
US8047472B1 (en) * 2006-06-06 2011-11-01 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Ram booster

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2740525C1 (en) * 2020-05-22 2021-01-15 Акционерное общество "Центральный научно-исследовательский институт машиностроения" (АО "ЦНИИмаш") Device for landing of return stage of carrier rocket
CN113739648A (en) * 2021-08-17 2021-12-03 航天科工火箭技术有限公司 Reusable technology demonstration verification rocket landing detection method, system and equipment
RU2781713C1 (en) * 2022-02-25 2022-10-17 Владимир Федорович Петрищев Landing device for launch return stage and method for its landing

Also Published As

Publication number Publication date
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