Add to ORKGA baseline for a space shuttle configuration utilizing four parallel-burn 120-in. diameter SRMS is presented. Topics discussed include parachute system sequence, recovery system development profile, parachute container, and segment and closure recovery operations. A cost analysis for recovery of the SRM stage is presented. It is concluded that from the standpoint of minimum cost and development, parachutes are the best means of achieving SRM recovery. Major SRM components can be reused safely
The study of solid rocket motors for a space shuttle booster was directed toward definition of a par...
The technical requirements for the solid propellant rocket engine to be used with the space shuttle ...
The cost data for solid propellant rocket engines for use with the space shuttle are presented. The ...
The baseline for a space shuttle configuration utilizing two parallel-burn, 156-in.-diameter SRMs wi...
Preliminary parametric studies were performed to establish size, weight and packaging arrangements f...
Recovery and reuse of the Space Shuttle solid rocket boosters was baselined to support the primary g...
The design of the space shuttle solid rocket booster (SRB) subsystems for reuse posed some unique an...
The Solid Rocket Booster (SRB) element integrates all the subsystems needed for ascent flight, entry...
An analysis of the water entry loads imposed on the reusable solid propellant rocket engine of the s...
An analysis and design effort was conducted as part of the study of solid rocket motor for a space s...
The cancellation of the Advanced Solid Rocket Booster Project and the earth-to-orbit payload require...
The factors affecting the choice of the 156 inch diameter, parallel burn, solid propellant rocket en...
Two Solid Rocket Boosters provide the primary first stage thrust for the Space Shuttle. These Booste...
Additional technical data have been prepared to supplement the data supplied in the SRM shuttle boos...
Flexseal assemblies, TVC actuators, hydraulic supply system, TVC electronic control unit, flight ins...
The study of solid rocket motors for a space shuttle booster was directed toward definition of a par...
The technical requirements for the solid propellant rocket engine to be used with the space shuttle ...
The cost data for solid propellant rocket engines for use with the space shuttle are presented. The ...
The baseline for a space shuttle configuration utilizing two parallel-burn, 156-in.-diameter SRMs wi...
Preliminary parametric studies were performed to establish size, weight and packaging arrangements f...
Recovery and reuse of the Space Shuttle solid rocket boosters was baselined to support the primary g...
The design of the space shuttle solid rocket booster (SRB) subsystems for reuse posed some unique an...
The Solid Rocket Booster (SRB) element integrates all the subsystems needed for ascent flight, entry...
An analysis of the water entry loads imposed on the reusable solid propellant rocket engine of the s...
An analysis and design effort was conducted as part of the study of solid rocket motor for a space s...
The cancellation of the Advanced Solid Rocket Booster Project and the earth-to-orbit payload require...
The factors affecting the choice of the 156 inch diameter, parallel burn, solid propellant rocket en...
Two Solid Rocket Boosters provide the primary first stage thrust for the Space Shuttle. These Booste...
Additional technical data have been prepared to supplement the data supplied in the SRM shuttle boos...
Flexseal assemblies, TVC actuators, hydraulic supply system, TVC electronic control unit, flight ins...
The study of solid rocket motors for a space shuttle booster was directed toward definition of a par...
The technical requirements for the solid propellant rocket engine to be used with the space shuttle ...
The cost data for solid propellant rocket engines for use with the space shuttle are presented. The ...