TERMIUM Plus^®

Record 1,  Textual support,  English

Record number: 1, Textual support number: 1 CONT

A rocket belt creates thrust by using pressurized nitrogen to push hydrogen peroxide into a chamber where thin silver plates break it down into heat, oxygen and water. The water is so hot it turns to steam and goes shooting out the belt's nozzles at supersonic speed giving thrust.  2, record 1, English, - rocket%20belt

Record 1,  Textual support,  French

Record number: 1, Textual support number: 1 DEF

Appareil à réaction très léger se fixant sur le corps du pilote pour lui permettre des évolutions dans l'atmosphère.  2, record 1, French, - ceinture%2Dfus%C3%A9e

Record 1,  Textual support,  Spanish

Record 2,  Textual support,  English

Record number: 2, Textual support number: 1 OBS

With respect to turbojet engine type certification, the approved jet thrust that is developed statically under standard sea level conditions, without fluid injection and without the burning of fuel in a separate combustion chamber, within the engine operating limitations established under Chapter 533 of the Airworthiness Manual, and limited in use to periods of not over 5 minutes for take-off operation or periods of not more than 10 minutes of one-engine-inoperative climb.  3, record 2, English, - rated%20take%2Doff%20thrust

Record 2,  Textual support,  French

Record number: 2, Textual support number: 1 OBS

En ce qui concerne la certification de type des turboréacteurs, poussée de jet approuvée, développée statiquement, dans les conditions standards au niveau de la mer, sans injection de fluide et sans combustion de carburant dans une chambre de combustion séparée, dans les limites d'utilisation du moteur établies au chapitre 533 du Manuel de navigabilité, et limitée à des durées d'utilisation ne dépassant pas 5 minutes pour les opérations de décollage ou 10 minutes en cas de montée avec un moteur arrêté.  2, record 2, French, - pouss%C3%A9e%20nominale%20au%20d%C3%A9collage

Record 2,  Textual support,  Spanish

Record number: 2, Textual support number: 1 DEF

Respecto a la certificación tipo del motor a turbina, [...] empuje aprobado y desarrollado estáticamente bajo condiciones estándar al nivel del mar, sin inyección de fluido y sin su combustión en una cámara de combustión separada, dentro de las limitaciones de operación del motor, establecida bajo la FAR [Federal Aviation Regulations] 33, y limitado su uso a períodos no mayores de 5 minutos para la operación de despegue.  1, record 2, Spanish, - empuje%20de%20despegue%20nominal

Record 3,  Textual support,  English

Record number: 3, Textual support number: 1 CONT

Swivelling nozzle for a rocket engine. The nozzle comprises a moving diverging portion and a static portion secured to the rear end wall of the combustion chamber of the engine. A cardan mount jointed link device connects the moving diverging portion of the nozzle to the static portion, the moving diverging portion and the static portion being in mutual contact via respective spherical surfaces, and an actuator device acts on the moving diverging portion of the nozzle so as to be able to vary the direction of the thrust vector of the engine by modifying the orientation of the nozzle with sliding of the spherical surfaces one on the other. Resilient return means are interposed between the moving diverging portion of the nozzle and the static portion and act on the moving diverging portion in order to urge it towards the static portion so as to keep the spherical surfaces in mutual contact for any desired orientation of the nozzle.  2, record 3, English, - swivelling%20nozzle

Record 3,  Textual support,  French

Record number: 3, Textual support number: 1 DEF

Tuyère articulée autour d'un ou deux axes et permettant d'orienter l'axe de poussée.  2, record 3, French, - tuy%C3%A8re%20orientable

Record 3,  Textual support,  Spanish

Record 4,  Textual support,  English

Record number: 4, Textual support number: 1 CONT

Rated intermediate contingency thrust with respect to supersonic transport turbojet engines means the approved jet thrust developed statically in a standard atmosphere at sea level, with burning of fuel in a separate combustion chamber, for use during engine-out operation within the engine operating limitations established under the applicable sections of FAR(Federal Administration Regulations) Part 33 and these Special Conditions and limited in use to periods of not over 15 minutes.  1, record 4, English, - intermediate%20contingency%20thrust

Record 4,  Textual support,  French

Record 4,  Textual support,  Spanish

Record 5,  Textual support,  English

Record number: 5, Textual support number: 1 CONT

... in the case of liquid propellant rocket motors, the liquid combustibles are contained in tanks and fed into the thrust chamber through an injector head by a propellant supply system.  1, record 5, English, - feed

Record 5,  Textual support,  French

Record number: 5, Textual support number: 1 CONT

Par exemple la navette US (Shuttle) emporte dans son réservoir central, 100 t d'hydrogène et 600 t d'oxygène, pour alimenter ses moteurs cryotechniques.  1, record 5, French, - alimenter

Record 5,  Textual support,  Spanish

Record 6,  Textual support,  English

Record number: 6, Textual support number: 1 CONT

The turbopump engine... comprises... the thrust chamber and turbopump. The latter comprises a... turbine,... the two propellant pumps and a water pump. The propellant [passes] through the turbine.  1, record 6, English, - turbopump%20engine

Record 6,  Textual support,  French

Record number: 6, Textual support number: 1 CONT

Dans les fusées à turbopompes, les liquides sont extraits des réservoirs au moyen de pompes [...] mues par une turbine, elles-mêmes actionnées par des gaz chauds et sous pression engendrés par un générateur de gaz.  1, record 6, French, - fus%C3%A9e%20%C3%A0%20turbopompes

Record 6,  Textual support,  Spanish

Record 7,  Textual support,  English

Record number: 7, Textual support number: 1 OBS

In a gas generator cycle engine, the turbine flow is in parallel with the thrust chamber and is not used to develop thrust.  2, record 7, English, - gas%20generator%20cycle%20engine

Record 7,  Textual support,  French

Record 7,  Textual support,  Spanish

Record 8,  Textual support,  English

Record number: 8, Textual support number: 1 CONT

Systems Analysis of a Future Semi-Reusable Launcher, Based on a High Thrust Bleed Cycle Rocket Engine. In this paper a high thrust, cryogenic bleed cycle engine, to be used for propulsion of future reusable booster stages(liquid fly back boosters), of an expendable heavy lift launcher, is analyzed. The system configuration remains unchanged, in terms of total available fuel and the number of engines, hereas the variation of the engine parameters result in a change of total system mass and payload capacity. Different arrangements of bleed cycles are being analyzed, and compared with each other. The paper describes a simplified heat transfer model, used in the analysis of the suggested cycles. The thrust chamber design is discussed and a preliminary design of the booster vehicle, including a trajectory analysis, is presented.  3, record 8, English, - semi%2Dreusable%20launcher

Record 8,  Textual support,  French

Record number: 8, Textual support number: 1 CONT

Cinq navettes furent construites [...] pour remplacer Challenger [...] Au départ ce devait être un lanceur récupérable. Mais les coûts exorbitants obligèrent les responsables à le transformer en un lanceur semi-récupérable. Le gros réservoir est devenu un élément ordinaire. Seuls l'orbiteur et les propulseurs auxiliaires sont récupérés.  1, record 8, French, - lanceur%20semi%2Dr%C3%A9cup%C3%A9rable

Record 8,  Textual support,  Spanish

Record 9,  Textual support,  English

Record number: 9, Textual support number: 1 CONT

When it is completed, the K-1 will be the first commercially available, fully reusable launch vehicle to provide low-cost access to space for low earth-orbiting satellites. The K-1 is powered by modified Russian rocket engines, provided by Aerojet, that burn LOX(liquid oxygen) and kerosene. Thrust is produced when the appropriate mixture of LOX and kerosene is pumped into the combustion chamber and ignited.  6, record 9, English, - K%2D1%20reusable%20launch%20vehicle

Record number: 9, Textual support number: 2 CONT

The K-1 will be able to deliver approximately 3,200 kg (7,000 lbm) of pressurized cargo to the ISS and return approximately 900 kg (2,000 lbm) of recoverable downmass. The K-1 cargo module can accommodate a volume of 30 m³ (1,000 ft³) equivalent to five International Standard Payload Racks. The K-1 is also capable of providing up to 40km (25 nmi) reboost and attitude control for ISS, an important feature for maintaining the ISS orbit, and conducting on-orbit technology demonstration as precursor risk reduction missions.  4, record 9, English, - K%2D1%20reusable%20launch%20vehicle

Record number: 9, Textual support number: 1 PHR

K-1 is equipped with an active dispenser.  7, record 9, English, - K%2D1%20reusable%20launch%20vehicle

Record number: 9, Textual support number: 2 PHR

K1 fully reusable, two-stage.  7, record 9, English, - K%2D1%20reusable%20launch%20vehicle

Record 9,  Textual support,  French

Record number: 9, Textual support number: 1 CONT

Le premier vaisseau spatial entièrement réutilisable sera l'engin K-1 de la Société Kistler Aerospace. Il devrait voler à la fin de 1999. Cette fusée à deux étages utilise des moteurs russes qui fonctionnent au kérosène et à l'oxygène liquide. Les étages séparés retourneront sur Terre par parachute.  2, record 9, French, - lanceur%20r%C3%A9cup%C3%A9rable%20K%2D1

Record 9,  Textual support,  Spanish

Record 10,  Textual support,  English

Record number: 10, Textual support number: 1 CONT

A rocket engine is a device in which propellants are burned in a combustion chamber and the resulting high pressure gases are expanded through a specially shaped nozzle to produce thrust. The function of the nozzle is to convert the chemical-thermal energy generated in the combustion chamber into kinetic energy. The nozzle converts the slow moving, high pressure, high temperature gas in the combustion chamber into high velocity gas of lower pressure and temperature. Gas velocities from 2 to 4. 5 kilometers per second can be obtained in rocket nozzles. The nozzles which perform this feat are called DeLaval nozzles(after the inventor) and consist of a convergent and divergent section. The minimum flow area between the convergent and divergent section is called the nozzle throat. The flow area at the end of the divergent section is called the nozzle exit area.  6, record 10, English, - divergent%20exit%20cone

Record 10,  Textual support,  French

Record number: 10, Textual support number: 1 DEF

Partie d'une tuyère de section croissante, en aval du col, où se produit la détente du gaz.  2, record 10, French, - divergent

Record number: 10, Textual support number: 1 OBS

Dans le divergent d'une tuyère à blocage sonique, la vitesse du gaz croît au-delà de la vitesse du son au col.  2, record 10, French, - divergent

Record number: 10, Textual support number: 1 PHR

Partie supérieure du divergent.  3, record 10, French, - divergent

Record 10,  Textual support,  Spanish

Record 11,  Textual support,  English

Record number: 11, Textual support number: 1 DEF

A very solid overdesigned thrust chamber used to test new propellants or new injector concepts.  2, record 11, English, - boiler%20plate%20motor

Record 11,  Textual support,  French

Record number: 11, Textual support number: 1 OBS

Sert à mesurer l'impulsion spécifique.  1, record 11, French, - moteur%20en%20%C2%ABboiler%20plate%C2%BB

Record 11,  Textual support,  Spanish

Record 12,  Textual support,  English

Record number: 12, Textual support number: 1 CONT

Analyses of launch-vehicle data obtained during the flight revealed that launch-vehicle propellant depletion occurred before the velocity cut-off system was armed and before the thrust chamber abort switch was disarmed. This combination of events resulted in an abort signal being transmitted to the spacecraft from the launch vehicle.  3, record 12, English, - velocity%20cut%2Doff%20system

Record 12,  Textual support,  French

Record 12,  Textual support,  Spanish

Record 13,  Textual support,  English

Record number: 13, Textual support number: 1 CONT

Pre-Burner Cycle Cryogenic Engine. Also known as the staged-combustion and topping cycle engine, this class of rocket engine features a turbopump drive in which some(or all) of the propellants undergo combustion at conditions considerably above thrust chamber combustion pressure(and at acceptable turbine inlet temperature conditions). The propellants pass through the turbine driving the pumps and are then injected into the thrust chamber where maximum cycle temperatures are achieved.  2, record 13, English, - topping%20cycle%20engine

Record 13,  Textual support,  French

Record 13,  Textual support,  Spanish

Record 14,  Textual support,  English

Record number: 14, Textual support number: 1 CONT

The Lance engine is actually two concentric engines with the thrust chamber of the boost motor surrounding the sustainer motor.  2, record 14, English, - sustainer%20motor

Record number: 14, Textual support number: 1 OBS

These motors are on the Lance tactical missile.  3, record 14, English, - sustainer%20motor

Record 14,  Textual support,  French

Record number: 14, Textual support number: 1 CONT

Le moteur du Lance comporte en fait deux moteurs concentriques, la chambre de poussée du moteur de démarrage et d'accélération entourant le moteur de croisière.  2, record 14, French, - moteur%20de%20croisi%C3%A8re

Record number: 14, Textual support number: 1 OBS

Ces moteurs sont ceux du missile tactique Lance.  3, record 14, French, - moteur%20de%20croisi%C3%A8re

Record 14,  Textual support,  Spanish

Record 15,  Textual support,  English

Record number: 15, Textual support number: 1 CONT

Directional control is the guidance mode used during missile boost engine operation. It is a gyroscope-controlled method of keeping the missile on its aimed course. During this phase, the missile attitude is maintained by a thrust vector control(TVC) system, which consists of four simple on-off valves spaced at 90 degree intervals around the nozzle of the booster thrust chamber.  1, record 15, English, - thrust%20vector%20control%20system

Record number: 15, Textual support number: 1 OBS

These devices are on the Lance tactical missile.  2, record 15, English, - thrust%20vector%20control%20system

Record 15,  Textual support,  French

Record number: 15, Textual support number: 1 CONT

Le contrôle de direction est le mode de guidage utilisé pendant le fonctionnement du moteur de démarrage du missile. Il s'agit, par contrôle gyroscopique, de maintenir le missile sur sa trajectoire de visée. Au cours de cette phase, l'attitude du missile est conservée par le système de contrôle du vecteur de poussée (TVC) qui consiste en quatre clapets espacés à des intervalles de 90 degrés sur le pourtour de la tuyère de la chambre de poussée du moteur de démarrage.  1, record 15, French, - syst%C3%A8me%20de%20contr%C3%B4le%20du%20vecteur%20de%20pouss%C3%A9e

Record number: 15, Textual support number: 1 OBS

Ces dispositifs se trouvent sur le missile tactique Lance.  2, record 15, French, - syst%C3%A8me%20de%20contr%C3%B4le%20du%20vecteur%20de%20pouss%C3%A9e

Record 15,  Textual support,  Spanish

Record 16,  Textual support,  English

Record number: 16, Textual support number: 1 CONT

The ejector lift principle, as developed by de Havilland Canada and used by General Dynamics in the E-7 design, also ducts forwards but to a specially-designed chamber where ambient air is entrained by the fan stream and a thrust-augmentation effect is obtained. The main engine nozzle swivels for lift thrust and, in forward flight, the fan stream has its own separate exhaust with afterburner.  1, record 16, English, - ejector%20lift%20principle

Record 16,  Textual support,  French

Record 16,  Textual support,  Spanish

Record 17,  Textual support,  English

Record number: 17, Textual support number: 1 CONT

Directional control is the guidance mode used during missile boost engine operation. It is a gyroscope-controlled method of keeping the missile on its aimed course. During this phase, the missile attitude is maintained by a thrust vector control(TVC) system, which consists of four simple on-off valves spaced at 90 degree intervals around the nozzle of the booster thrust chamber.  1, record 17, English, - directional%20control

Record number: 17, Textual support number: 1 OBS

These devices are on the Lance tactical missile.  2, record 17, English, - directional%20control

Record 17,  Textual support,  French

Record number: 17, Textual support number: 1 CONT

Le contrôle de direction est le mode de guidage utilisé pendant le fonctionnement du moteur de démarrage du missile. Il s'agit, par contrôle gyroscopique, de maintenir le missile sur sa trajectoire de visée. Au cours de cette phase, l'attitude du missile est conservée par le système de contrôle du vecteur de poussée (TVC) qui consiste en quatre clapets espacés à des intervalles de 90 degrés sur le pourtour de la tuyère de la chambre de poussée du moteur de démarrage.  1, record 17, French, - contr%C3%B4le%20de%20direction

Record number: 17, Textual support number: 1 OBS

Ces dispositifs se trouvent sur le missile tactique Lance.  2, record 17, French, - contr%C3%B4le%20de%20direction

Record 17,  Textual support,  Spanish

Record 18,  Textual support,  English

Record number: 18, Textual support number: 1 CONT

The TRI60 demonstrated start-up and acceleration to cruise thrust in less than five seconds entirely by means of the windmilling effect created by ram pressure. At launch, the only engine-starting actions required are the opening of the fuel cock and the firing of two pyrotechnic igniters in the combustion chamber.  1, record 18, English, - pyrotechnic%20igniter

Record 18,  Textual support,  French

Record number: 18, Textual support number: 1 CONT

Saab-Scania (...) participait à ces essais (...) qui ont démontré l'aptitude du turboréacteur à atteindre le régime de croisière en moins de 5 secondes sous le seul effet de l'autorotation créée par la pression dynamique, les actions requises au moment du lancement se limitant à l'ouverture de la vanne de carburant et au déclenchement des deux allumeurs pyrotechniques de la chambre de combustion.  1, record 18, French, - allumeur%20pyrotechnique

Record 18,  Textual support,  Spanish

Record 19,  Textual support,  English

Record number: 19, Textual support number: 1 CONT

... The Hawker Project Office had produced the first drawing of a supersonic vectored thrust V/STOL aircraft... This shows the first embodiment of Bristol Siddeley... proposals for Plenum Chamber Burning in a vectored thrust engine.  1, record 19, English, - vectored%20thrust%20engine

Record 19,  Textual support,  French

Record number: 19, Textual support number: 1 CONT

Il est assez réconfortant de penser que c'est un de nos compatriotes (...) qui fut à la base des réacteurs Bristol Siddeley à orientation de poussée.  1, record 19, French, - r%C3%A9acteur%20%C3%A0%20orientation%20de%20pouss%C3%A9e

Record 19,  Textual support,  Spanish

Record 20,  Textual support,  English

Record number: 20, Textual support number: 1 CONT

P. C. B. [Plenum Chamber Burning] consists of burning fuel in the front(cold) jet streams to give thrust boost for take-off in supersonic flight and, in consequence, a better thrust/S. F. C. matching in throttle-back subsonic cruise at low altitude.  1, record 20, English, - Plenum%20Chamber%20Burning

Record 20,  Textual support,  French

Record number: 20, Textual support number: 1 DEF

Dans un réacteur double-flux, une partie de l'air, après passage dans le compresseur est utilisé pour refroidir les parties extérieures de la zone de combustion et participer à la poussée: pour augmenter celle-ci on peut injecter ou enflammer du carburant dans le canal d'éjection propre à ce flux.  2, record 20, French, - r%C3%A9chauffe%20du%20flux%20secondaire

Record 20,  Textual support,  Spanish