Allred, 1995 - Google Patents
Quantitative evaluation of human-rating-The impact of solid propulsion on the reliability and safety of space launch vehiclesAllred, 1995
- Document ID
- 12639556320796214035
- Author
- Allred A
- Publication year
- Publication venue
- Space Programs and Technologies Conference
External Links
Snippet
Human-rating concerns can have a significant impact on vehicle cost and operability. If properly managed, this impact can be effectively minimized. These concerns must he addressed quantitatively beginning with the inception of a program. Assessment of …
- 239000007787 solid 0 title description 79
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/402—Propellant tanks; Feeding propellants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING ENGINES OR PUMPS
- 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
- F02K9/32—Constructional parts; Details
- F02K9/34—Casings; Combustion chambers; Liners thereof
- F02K9/343—Joints, connections, seals therefor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING ENGINES OR PUMPS
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/646—Docking or rendez-vous systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING ENGINES OR PUMPS
- 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
- F02K9/42—Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLYING SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D25/00—Emergency apparatus or devices, not otherwise provided for
- B64D25/08—Ejecting or escaping means
Similar Documents
Publication | Publication Date | Title |
---|---|---|
Palaszewski et al. | Launch vehicle performance using metallized propellants | |
US20120312927A1 (en) | Launch abort and orbital maneuver system | |
WO2014022836A2 (en) | Universal elliptical-sliced solid grain geometry and coupled grill-feedthrough featured assembly for solid rocket motor and coaxial hybrid rocket design | |
US7484692B1 (en) | Integrated abort rocket and orbital propulsion system | |
Allred | Quantitative evaluation of human-rating-The impact of solid propulsion on the reliability and safety of space launch vehicles | |
US20070012821A1 (en) | Launch vehicle crew escape system | |
Arves et al. | Development of a N2O/HTPB hybrid rocket motor | |
Allred et al. | Crew survival and intact abort using solid rocket boosters | |
Allen | Historical reliability of US launch vehicles | |
Lake et al. | A Study of the Role of Pyrotechnic Systems on the Space Shuttle Program | |
Sauvageau et al. | Launch vehicle historical reliability | |
Wiswell et al. | X-15 propulsion system | |
Baker et al. | Mars science laboratory descent-stage integrated propulsion subsystem: development and flight performance | |
Sarigul-Klijn et al. | Concept and Design Details of a Universal Gas-Gas Launch Escape System | |
US12049855B1 (en) | Method and apparatus for reducing consequences of a bulkhead failure for a liquid methane and liquid oxygen rocket | |
Vaughan | Apollo reaction control systems | |
Allred et al. | Human-rating aspects of solid propulsion | |
Go et al. | Mission Success of US Launch Vehicle Flights from a Propulsion Stage-based Perspective: 1980-2015 | |
Seeholzer | Applications catalog of pyrotechnically actuated devices/systems | |
Lo et al. | Hybrid boosters for Ariane 5 | |
Maybee et al. | A novel design warm gas pressurization system | |
Boorady et al. | Solution of the high-vacuum hard-start problem of the IRFNA-UDMH rocket for Gemini Agena. | |
CHASE | IUS flight motor designs and full-scale development program | |
CRAMER et al. | Application of the integrated modular engine (IME) to space vehicle concepts | |
Cotta et al. | Upper stage options for reusable launch vehicles |