WO2015075503A1 - Tuyère en plastique de propulsion pour roquettes - Google Patents

Tuyère en plastique de propulsion pour roquettes Download PDF

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Publication number
WO2015075503A1
WO2015075503A1 PCT/IB2013/060312 IB2013060312W WO2015075503A1 WO 2015075503 A1 WO2015075503 A1 WO 2015075503A1 IB 2013060312 W IB2013060312 W IB 2013060312W WO 2015075503 A1 WO2015075503 A1 WO 2015075503A1
Authority
WO
WIPO (PCT)
Prior art keywords
rocket
nozzle
plastic
allows
rockets
Prior art date
Application number
PCT/IB2013/060312
Other languages
English (en)
Spanish (es)
Inventor
Jorge Felipe GONZÁLEZ PELÁEZ
Original Assignee
Thor International Sas
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 Thor International Sas filed Critical Thor International Sas
Priority to PCT/IB2013/060312 priority Critical patent/WO2015075503A1/fr
Publication of WO2015075503A1 publication Critical patent/WO2015075503A1/fr

Links

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
    • F02K9/97—Rocket nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/614—Fibres or filaments

Definitions

  • the present invention relates to a plastic propulsion nozzle for use in rockets, which is characterized in that it is manufactured in a plastic material with fiberglass injection that has characteristic properties that allow the entire ignition and firing process of the rocket is carried out successfully without presenting the problem that the nozzle can melt or be damaged by the heat of the launch, where the nozzle made of plastic material has the advantages of weight reduction that allows the rocket greater autonomy of flight and a more reliable flight because it displaces the center of pressure of the rocket improving its aerodynamics, which also allows to increase the payload of the rocket, that is, the warhead without sacrificing flight distance.
  • the nozzle of the present invention reduces the production costs of the rocket, since when manufacturing it in plastic, the manufacturing process goes from being intensive in chip removal machinery (lathes and milling machines) to being manufactured in plastic injectors thus allowing a more agile, massive and therefore economic process.
  • the rocket nozzles currently used are manufactured in a series of materials that have a desired and adequate resistance to allow the rocket to be launched and the ignition process can be carried out, avoiding to the maximum the possibility of a problem or damage caused in the rocket due to the high temperature that is handled in said launch, which makes it necessary to have a material highly resistant to heat and that allows the transport of the load that is in the head of the rocket.
  • the conventional material most used in rocket nozzles existing in the state of the art is steel, which has a very good resistance to high temperatures, but which presents the problem of being expensive and requiring a series of processes and machinery for metal handling, where the processes are long and complex and the machinery has very high costs.
  • the invention described in said United States patent document has the disadvantage that the material of the nozzle disclosed therein is simply a plastic without any type of reinforcement or coating that allows to increase the resistance to the high temperatures handled at release. of rockets, which is unwanted and restricts the application and use of the rocket used by the nozzle.
  • the nozzle described in this document has a main disadvantage, since a type of plastic is mentioned for the vanes inside the nozzle, where this plastic melts instantaneously and allows propulsion, but not which is not suitable for the manufacture of the total nozzle and does not withstand high temperatures, since its intended use is to serve as a propulsion material, so it is not suitable for the external manufacture of nozzles and rockets.
  • JP 8177632 discloses a nozzle for a solid rocket engine, where the nozzle is provided with at least one body member formed with a part in T of said body and each nozzle member is formed respectively with a C-shaped cylinder up and a D-shaped diffusion cylinder down.
  • the nozzle member is formed which is manufactured from a fiber-reinforced plastic material that uses a phenol resin in a base material to use carbon fiber in a reinforcing material.
  • the invention described herein is suitable for the manufacture of nozzles from a plastic material mixed with a fiber
  • the nozzle described therein has the disadvantage that its costs are very high considering the fact that the preferred fiber It is carbon fiber that, although it has excellent resistance, hardness and workability properties, its cost is very high and therefore, it cannot be easily manufactured in the industry and requires special machinery for handling.
  • European patent document EP 1378652 is related to a multilayer composite material for combustion chambers or rocket nozzles comprising an inner layer consisting of fiber reinforced ceramics whose matrix contains carbon phases or silicone carbide phases .
  • the outer layer of the material consists of a plastic material reinforced with carbon fibers.
  • Figure 1 corresponds to a front plan view of the plastic nozzle of the present invention.
  • Figure 2 corresponds to a top view of the plastic nozzle of Figure 1.
  • Figure 3 corresponds to the cross-section of the nozzle of Figure 1 through the line A-A '.
  • the present invention corresponds to a propulsion nozzle for use in rockets made of a high strength and low cost material, wherein said nozzle comprises:
  • the plastic nozzle of the present invention is characterized in that all of it is manufactured from a plastic material, such as Acrylonitrile Butadiene Styrene (ABS) with fiberglass injection, which allows a reduction in rocket weight and that allows it to have a greater Flight autonomy and a more reliable flight, since it displaces the center of pressure of the rocket improving its aerodynamics.
  • ABS Acrylonitrile Butadiene Styrene
  • the reduction in weight of the rocket due to the material of the nozzle also allows to increase the payload of the rocket, that is, the warhead without sacrificing flight distance.
  • ABS plastic material with fiberglass injection of the nozzle of the present invention allows a reduction in the costs associated with the manufacture of rockets, even when manufacturing the rocket in plastic, the manufacturing process goes from being intensive in chip removal machinery, such as lathes, milling machines and the like, to be manufactured in conventional plastic injectors that are used in other types of industries, which leads to a more agile, massive and mainly economic process, every time that the raw material (ABS plastic and fiberglass) are material commonly used in multiple applications, which are easy to obtain and have a very adequate price, which allows very good quality rockets to be manufactured at a reduced price.

Abstract

La présente invention concerne une tuyère de propulsion en plastique destinée à être utilisée sur des roquettes, ladite tuyère étant caractérisée en ce qu'elle est réalisée à partir d'une matière plastique à fibres de verre incorporées qui possède des propriétés caractéristiques permettant un déroulement réussi de tout le processus d'allumage et de tir de la roquette, sans présenter de problème de fusion ou d'endommagement de la tuyère sous l'effet de la chaleur du lancement, la tuyère fabriquée à partir de matière plastique présentant comme avantages une réduction de poids permettant l'augmentation de l'autonomie de vol et un vol plus fiable du fait que le centre de pression de la roquette est déplacé ce qui améliore son aérodynamique, et permet en outre d'agrandir la charge utile de la roquette, autrement dit l'ogive, sans réduire la distance de vol.
PCT/IB2013/060312 2013-11-21 2013-11-21 Tuyère en plastique de propulsion pour roquettes WO2015075503A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/IB2013/060312 WO2015075503A1 (fr) 2013-11-21 2013-11-21 Tuyère en plastique de propulsion pour roquettes

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/IB2013/060312 WO2015075503A1 (fr) 2013-11-21 2013-11-21 Tuyère en plastique de propulsion pour roquettes

Publications (1)

Publication Number Publication Date
WO2015075503A1 true WO2015075503A1 (fr) 2015-05-28

Family

ID=53179027

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/IB2013/060312 WO2015075503A1 (fr) 2013-11-21 2013-11-21 Tuyère en plastique de propulsion pour roquettes

Country Status (1)

Country Link
WO (1) WO2015075503A1 (fr)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3663496A (en) * 1964-09-14 1972-05-16 Uniroyal Inc Ablative composition comprising rubber,resin,and filler
US4232843A (en) * 1977-05-25 1980-11-11 Her Majesty The Queen In Right Of Canada, As Represented By The Minister Of National Defence Molded nozzle for rocket motor
WO2001020966A2 (fr) * 1999-09-08 2001-03-29 Alliant Techsystems Inc. Isolation ablative par resine phenolique elastomerisee pour moteurs-fusees
WO2002079307A2 (fr) * 2001-01-10 2002-10-10 Alliant Techsystems Inc. Isolation pour moteur-fusee renforcee de fibres

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3663496A (en) * 1964-09-14 1972-05-16 Uniroyal Inc Ablative composition comprising rubber,resin,and filler
US4232843A (en) * 1977-05-25 1980-11-11 Her Majesty The Queen In Right Of Canada, As Represented By The Minister Of National Defence Molded nozzle for rocket motor
WO2001020966A2 (fr) * 1999-09-08 2001-03-29 Alliant Techsystems Inc. Isolation ablative par resine phenolique elastomerisee pour moteurs-fusees
WO2002079307A2 (fr) * 2001-01-10 2002-10-10 Alliant Techsystems Inc. Isolation pour moteur-fusee renforcee de fibres

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