FR2605051A1 - Semicircular rocket propulsion unit - Google Patents

Semicircular rocket propulsion unit Download PDF

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Publication number
FR2605051A1
FR2605051A1 FR8614171A FR8614171A FR2605051A1 FR 2605051 A1 FR2605051 A1 FR 2605051A1 FR 8614171 A FR8614171 A FR 8614171A FR 8614171 A FR8614171 A FR 8614171A FR 2605051 A1 FR2605051 A1 FR 2605051A1
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FR
France
Prior art keywords
cylindrical body
solid fuel
space
combustion
semicircular
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Granted
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FR8614171A
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French (fr)
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FR2605051B1 (en
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Individual
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Individual
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Publication date
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Priority to FR8614171A priority Critical patent/FR2605051B1/en
Publication of FR2605051A1 publication Critical patent/FR2605051A1/en
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Publication of FR2605051B1 publication Critical patent/FR2605051B1/en
Expired legal-status Critical Current

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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
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/30—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants with the propulsion gases exhausting through a plurality of nozzles
    • 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
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/10—Shape or structure of solid propellant charges

Abstract

Device for propelling space launchers. The invention relates to a device making it possible to propel space launchers without the risk of imbalance. It is made up by a fuel chamber formed by a cylindrical body 1, by two closure capsules 2 and 3 including nozzles 4 and 5 for ejecting the combustion gases, the nozzles being directed parallel to one another, by solid fuel 6 provided at its middle with a combustion chamber 7. The device according to the invention is particularly intended for propulsion in the space field.

Description

La présente invention concerne un dispositif à combustibles solides pour permettre la propulsion des fusées ou des lanceurs de satellites ou de véhicules spatiaux. The present invention relates to a solid fuel device for propelling rockets or launchers from satellites or space vehicles.

La propulsion des fusées ou des lanceurs s'effectue parfois à l'aide d'un groupe propulseur composé de deux propulseurs-fusée à combustibles solides, indépendants l'un de 1' autre.  The propulsion of rockets or launchers is sometimes carried out using a propulsion unit composed of two solid fuel rocket propellers, independent of one another.

La régularité de combustion n'est jamais identique d'un propulseur à l'autre, provoquant ainsi deux différentes pressions internes de gaz de combustion qui se traduisent par deux vitesses et deux poussées différentes des gaz éjectés. The regularity of combustion is never identical from one propellant to another, thus causing two different internal pressures of combustion gases which result in two different speeds and two thrusts of the ejected gases.

Ce qui risque de provoquer un déséquilibre de propulsion et de faire basculer la fusée ou le lanceur au décollage ou de le dévier de sa trajectoire en vol. Le dispositif selon l'invention permet de remédier à cet inconvénient.This could cause a propulsion imbalance and cause the rocket or launcher to tip over or take it off its flight path. The device according to the invention overcomes this drawback.

I1 comporte en effet une chambre à combustibles solides formée par un corps cylindrique sur lequel est fixée à chacune de ses deux extrémités, une capsule de fermeture. Sur chacune des deux capsules de fermeture est disposée une tuyère pour permettre l'éjection des gaz de combustion. Les deux tuyères d'éjection sont orientées parallèlement l'une par rapport à l'autre à ce que les gaz de combustion ainsi éjectés fournissent une poussée dans une seule et même direction, ce qui amène à concevoir une forme semi circulaire du corps cylindrique. Le combustible solide est installé à l'intérieur du corps cylindrique formant la chambre à combustibles. Le combustible solide est pourvu d'un espace en son milieu et qui constitue ainsi la chambre à combustion. I1 in fact comprises a solid fuel chamber formed by a cylindrical body on which is fixed at each of its two ends, a closure capsule. On each of the two closure capsules is arranged a nozzle to allow the ejection of the combustion gases. The two ejection nozzles are oriented parallel to each other so that the combustion gases thus ejected provide thrust in one and the same direction, which leads to the conception of a semi-circular shape of the cylindrical body. The solid fuel is installed inside the cylindrical body forming the fuel chamber. The solid fuel is provided with a space in the middle and which thus constitutes the combustion chamber.

Quand la combustion s'effectue, les gaz ne peuvent exercer qu'une seule pression interne, les gaz de combustion ainsi éjectés par chacune des deux tuyères, sont de vitesse et de poussée identiques, ce qui provoque un équilibre de propulsion, évitant au décollage le basculement de la fusée ou du lanceur et sa déviation envol.When combustion takes place, the gases can exert only one internal pressure, the combustion gases thus ejected by each of the two nozzles, are of identical speed and thrust, which causes a balance of propulsion, avoiding takeoff rocking of the rocket or launcher and its deflection takeoff.

Selon une variante, les deux extrémités du dispositif peuvent être prolongées parallèlement l'une par rapport à l'autre pour une augmentation de puissance. Alternatively, the two ends of the device can be extended parallel to one another for an increase in power.

Les dessins annexés illustrent l'invention
La figure 1 représente, de profil, le dispositif selon l'invention.The accompanying drawings illustrate the invention
Figure 1 shows, in profile, the device according to the invention.

La figure 2 représente, en coupe suivant AA, ce dispositif. Figure 2 shows, in section along AA, this device.

La figure 3 représente, vue à partir des tuyères, ce dispositif. FIG. 3 represents, seen from the nozzles, this device.

La figure 4 représente, vue à partir du corps cylindrique, ce dispositif. FIG. 4 represents, seen from the cylindrical body, this device.

La figure 5 représente, en coupe suivant BB, ce disposifit. Figure 5 shows, in section along BB, this device.

La figure 6 représente une variante de ce dispositif. Figure 6 shows a variant of this device.

Le dispositif représenté sur la figure 1 comporte le corps cylindrique (1), les deux capsules de fermeture (2) et (3), les deux tuyères d'éjection des gaz de combustion (4) et (5).  The device shown in FIG. 1 comprises the cylindrical body (1), the two closure capsules (2) and (3), the two combustion gas ejection nozzles (4) and (5).

Le dispositif représenté sur la figure 2 comporte le coprs cylindrique (1), les capsules de fermeture (2) et (3) les tuyères d'éjection des gaz de combustion (4) et (5), le combustible solide (6), la chambre à combustion (7). The device shown in FIG. 2 includes the cylindrical body (1), the closure capsules (2) and (3) the combustion gas ejection nozzles (4) and (5), the solid fuel (6), the combustion chamber (7).

Le dispositif représenté sur la figure 3 comporte le corps cylindrique (1), les deux capsules de fermeture (2) et (3) les tuyères d'éjection (4) et (5). The device shown in Figure 3 includes the cylindrical body (1), the two closure capsules (2) and (3) the ejection nozzles (4) and (5).

Le dispositif représenté sur la figure 4 comporte le corps cylindrique (1). The device shown in Figure 4 comprises the cylindrical body (1).

Le dispositif représenté sur la figure 5 comporte le corps cylindrique (1), le combustible solide (6), la chambre à combustion (7). The device shown in Figure 5 includes the cylindrical body (1), the solid fuel (6), the combustion chamber (7).

Une variante de ce dispositif représentée par la figure 6 comporte le corps cylindrique (1) dont les extrémités sont prolongées parallèlement l'une par rapport à l'autre, les
capsules de fermeture (2) et (3),les tuyères d'éjection des gaz de combustion (4) et (5), le combustible solide (6), la chambre à combustion (7).A variant of this device shown in Figure 6 comprises the cylindrical body (1) whose ends are extended parallel to each other, the
closure caps (2) and (3), the combustion gas ejection nozzles (4) and (5), the solid fuel (6), the combustion chamber (7).

Le dispositif selon l'invention est particulièrement destiné à la propulsion des lanceurs dans le domaine spatial.  The device according to the invention is particularly intended for the propulsion of launchers in the space field.

Claims (5)

REVENDICATIONS 1) Dispositif à combustiblessolides pour propulser les lanceurs de satellites ou de véhicules spatiaux caractérisé en ce qu' il comporte un corps cylindrique (1) dans lequel est installé le combustible solide (6) qui est pourvu d'un espace (7) en son milieu, aux deux extrémités du corps cylindrique (1) sont fixées deux capsules de fermeture (2) et (3) sur lesquelles sont disposées deux tuyères d'éjection des gaz de combustion (4) et (5) et qui sont orientées parallèlement l'une par rapport à l'autre donnant ainsi au corps cylindrique (1) une forme semi circulaire. 1) Solid fuel device for propelling satellite or space vehicle launchers characterized in that it comprises a cylindrical body (1) in which the solid fuel (6) is installed which is provided with a space (7) in sound middle, at the two ends of the cylindrical body (1) are fixed two closure capsules (2) and (3) on which are arranged two combustion gas ejection nozzles (4) and (5) and which are oriented parallel l 'one relative to the other thus giving the cylindrical body (1) a semi circular shape. 2) Dispositif selon la revendication i caractérisé en ce que le corps cylindrique (1) constitue la chambre à combustibles. 2) Device according to claim i characterized in that the cylindrical body (1) constitutes the fuel chamber. 3) Dispositif selon la revendication 1 caractérisé en ce que l'espace aménagé au milieu du combustible solide (6) constitue la chambre à combustion (7). 3) Device according to claim 1 characterized in that the space arranged in the middle of the solid fuel (6) constitutes the combustion chamber (7). 4) Dispositif selon la revendication 1 caractérisé en ce que les deux tuyères d'éjection des gaz de combustion (4) et (5) sont orientées parallèlement l'une par rapport à l'autre. 4) Device according to claim 1 characterized in that the two combustion gas ejection nozzles (4) and (5) are oriented parallel to each other. 5) Dispositif selon la revendication 1 caractérisé en ce que les deux extrémités du corps cylindrique (1) peuvent être prolongées parallèlement l'une par rapport à l'autre (fiv.6)  5) Device according to claim 1 characterized in that the two ends of the cylindrical body (1) can be extended parallel to one another (fiv.6)
FR8614171A 1986-10-13 1986-10-13 SEMICIRCULAR ROCKET PROPELLER Expired FR2605051B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR8614171A FR2605051B1 (en) 1986-10-13 1986-10-13 SEMICIRCULAR ROCKET PROPELLER

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR8614171A FR2605051B1 (en) 1986-10-13 1986-10-13 SEMICIRCULAR ROCKET PROPELLER

Publications (2)

Publication Number Publication Date
FR2605051A1 true FR2605051A1 (en) 1988-04-15
FR2605051B1 FR2605051B1 (en) 1989-09-29

Family

ID=9339775

Family Applications (1)

Application Number Title Priority Date Filing Date
FR8614171A Expired FR2605051B1 (en) 1986-10-13 1986-10-13 SEMICIRCULAR ROCKET PROPELLER

Country Status (1)

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FR (1) FR2605051B1 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109237517A (en) * 2018-08-12 2019-01-18 梁智斌 Annular jet propeller
CN112065607A (en) * 2020-09-18 2020-12-11 侯瀚宇 Combustion chamber, engine, method and application

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2976805A (en) * 1947-02-11 1961-03-28 Africano Alfred Rocket construction
FR1336757A (en) * 1962-07-19 1963-09-06 Onera (Off Nat Aerospatiale) Improvements made to rocket motors with solid propellant charge, especially those for high performance vehicles
GB961001A (en) * 1962-03-20 1964-06-17 Snecma Improvements in propulsion units having a plurality of reaction propulsion nozzles
FR2312660A1 (en) * 1975-05-27 1976-12-24 Onera (Off Nat Aerospatiale) Solid fuel rocket engine - has spherical casing with nozzle supported by thermal insulation ring

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2976805A (en) * 1947-02-11 1961-03-28 Africano Alfred Rocket construction
GB961001A (en) * 1962-03-20 1964-06-17 Snecma Improvements in propulsion units having a plurality of reaction propulsion nozzles
FR1336757A (en) * 1962-07-19 1963-09-06 Onera (Off Nat Aerospatiale) Improvements made to rocket motors with solid propellant charge, especially those for high performance vehicles
FR2312660A1 (en) * 1975-05-27 1976-12-24 Onera (Off Nat Aerospatiale) Solid fuel rocket engine - has spherical casing with nozzle supported by thermal insulation ring

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109237517A (en) * 2018-08-12 2019-01-18 梁智斌 Annular jet propeller
CN109237517B (en) * 2018-08-12 2021-03-26 梁智斌 Annular nozzle propeller
CN112065607A (en) * 2020-09-18 2020-12-11 侯瀚宇 Combustion chamber, engine, method and application

Also Published As

Publication number Publication date
FR2605051B1 (en) 1989-09-29

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