ANNULAR AEROSPIKE NOZZLE WITH WIDELY-SPACED THRUST CHAMBERS, ENGINE INCLUDING THE ANNULAR AEROSPIKE NOZZLE, AND VEHICLE INCLUDING THE ENGINE

An annular aerospike nozzle for a vehicle, such as an upper stage rocket, is disclosed. The annular aerospike nozzle includes a centerbody and a plurality of thrust chambers spaced around the centerbody. Each thrust chamber has a throat and a nozzle portion extending aft of the throat. The nozzle po...

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Bibliographische Detailangaben
Hauptverfasser:	FELDMAN, THOMAS, LAPSA, ANDREW, MCCULLOUGH, THOMAS RYAN, SANDER, ZACHARY
Format:	Patent
Sprache:	eng ; fre
Schlagworte:	AIRCRAFT AVIATION BLASTING COMBUSTION ENGINES COSMONAUTICS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING PERFORMING OPERATIONS TRANSPORTING VEHICLES OR EQUIPMENT THEREFOR WEAPONS
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Beschreibung
Zusammenfassung:	An annular aerospike nozzle for a vehicle, such as an upper stage rocket, is disclosed. The annular aerospike nozzle includes a centerbody and a plurality of thrust chambers spaced around the centerbody. Each thrust chamber has a throat and a nozzle portion extending aft of the throat. The nozzle portion has an exit dimension Dexit at an aft end. Each thrust chamber is spaced away from adjacent thrust chambers by a spacing distance Dspace, such that Dspace = M * Dexit, where M = 1. L'invention concerne une tuyère annulaire de type aerospike pour un véhicule, tel qu'une fusée à étage supérieur. Ladite tuyère annulaire de type aerospike comprend un corps central et une pluralité de chambres propulsives espacées autour du corps central. Chaque chambre propulsive présente un col et une partie de tuyère s'étendant vers l'arrière du col. La partie de tuyère a une dimension de sortie Dexit à une extrémité arrière. Chaque chambre propulsive est espacée des chambres propulsives adjacentes d'une distance d'espacement Dspace, de sorte que Dspace = M * Dexit, où M = 1.