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1. WO1996004168 - TWO STAGE LAUNCH VEHICLE AND LAUNCH TRAJECTORY METHOD

Publication Number WO/1996/004168
Publication Date 15.02.1996
International Application No. PCT/US1995/009368
International Filing Date 25.07.1995
Chapter 2 Demand Filed 21.02.1996
IPC
B64G 1/00 2006.01
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
GCOSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
1Cosmonautic vehicles
B64G 1/14 2006.01
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
GCOSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
1Cosmonautic vehicles
14Space shuttles
B64G 1/40 2006.01
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
GCOSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
1Cosmonautic vehicles
22Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
40Arrangements or adaptations of propulsion systems
F02K 9/76 2006.01
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
KJET-PROPULSION PLANTS
9Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
74combined with another jet-propulsion plant
76with another rocket-engine plant; Multistage rocket-engine plants
CPC
B64G 1/002
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
GCOSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
1Cosmonautic vehicles
002Launch systems
B64G 1/14
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
GCOSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
1Cosmonautic vehicles
14Space shuttles
B64G 1/401
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
GCOSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
1Cosmonautic vehicles
22Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
40Arrangements or adaptations of propulsion systems
401Liquid propellant rocket engines
B64G 1/402
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
GCOSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
1Cosmonautic vehicles
22Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
40Arrangements or adaptations of propulsion systems
402Propellant tanks; Feeding propellants
B64G 1/403
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
GCOSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
1Cosmonautic vehicles
22Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
40Arrangements or adaptations of propulsion systems
403Solid propellant rocket engines
F02K 9/766
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
KJET-PROPULSION PLANTS
9Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
74combined with another jet-propulsion plant
76with another rocket-engine plant; Multistage rocket-engine plants
766with liquid propellant
Applicants
  • STIENNON, Patrick, J., G. [US/US]; US
Inventors
  • STIENNON, Patrick, J., G.; US
Agents
  • ROMARY, John, M. ; Finnegan, Henderson, Farabow, Garrett & Dunner 1300 I Street, N.W. Washington, DC 20005-3315, US
Priority Data
08/283,73901.08.1994US
Publication Language English (EN)
Filing Language English (EN)
Designated States
Title
(EN) TWO STAGE LAUNCH VEHICLE AND LAUNCH TRAJECTORY METHOD
(FR) VEHICULE DE LANCEMENT A DEUX ETAGES ET PROCEDE RELATIF A LA TRAJECTOIRE DE LANCEMENT
Abstract
(EN)
A method of launching a two stage vehicle (20) and a trajectory for use with a two stage vehicle (20) which allows recovery of both stages at the launch site. This is accomplished by launching the first stage (24) completely vertically so that on burnout the first stage (24) is positioned directly above the recovery site. In order to get maximum benefit from launching the stage vertically gravitational losses are minimized by a first stage thrust to weight ratio of 1.6. The high thrust to weight ratio results in burnout at approximately 100,000 feet altitude within the atmosphere. Therefore the vehicle employs engines (27) which produce at altitude approximately 15 percent of the sea level thrust of the first stage and consume the last 5 percent of propellant over a time period of 40 seconds. Staging is accomplished at 200,000 feet altitude. The second stage (24) employs uprated RL-10 engines (25) and has a thrust to weight ratio of 1.45 and can achieve orbit with a velocity change of approximately 24,500 feet per second. The first stage (22) employs air breathing vertical lift engines (27) for recovery. The second stage (24) utilizes a parawing (55).
(FR)
Procédé de lancement d'un véhicule à deux étages (20) et trajectoire à utiliser avec un véhicule à deux étages (20). Ledit procédé permet de récupérer les deux étages sur le site de lancement. On y parvient en lançant le premier étage (24) de manière complètement verticale, si bien qu'à l'épuisement du carburant, le premier étage (24) est placé directement au-dessus du site de récupération. Afin d'obtenir les avantages maximaux du lancement vertical de l'étage, les pertes gravitationnelles sont minimisées par un rapport poussée/poids de premier étage de 1,6. Le rapport poussée/poids élevé entraîne un épuisement du carburant à environ 100.000 pieds d'altitude dans l'atmosphère. Par conséquent, ledit véhicule est doté de moteurs (27) qui produisent en altitude environ 15 pour cent de la poussée du premier étage au niveau de la mer et consomment les 5 pour cent restants de propulseur sur une période de 40 secondes. La séparation des étages est effectuée à 200.000 pieds d'altitude. Le second étage (24) emploie des moteurs perfectionnés RL-10 (25) et possède un rapport poussée/poids de 1,45. Il peut atteindre l'orbite avec une variation de vitesse d'environ 24.500 pieds par seconde. Pour la récupération, le premier étage (22) emploie des moteurs E (27) poussée verticale aérobies. Le second étage (24) utilise un paraplaneur (55).
Also published as
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