3 NASA HAS IDENTIFIED THE NEED FOR RISK REDUCTION WITH RESPECT TO THE FIRST STAGE OF A TWO STAGE MAV, WHICH WILL BE CAPABLE OF INJECTING AN ORBITING SAMPLE INTO MARS ORBIT. THE FIRST STAGE HAS BEEN CHOSEN BECAUSE MANY CHALLENGES LIE IN ITS DESIGN. BOTH STAGES ARE ASSUMED TO BE SOLID ROCKET MOTORS WITH A PROPELLANT CAPABLE OF LOW TEMPERATURE STORAGE AND OPERATION. THE FIRST STAGE IS THE LARGER OF THE TWO MOTORS, MAKING GRAIN STRESSES MORE PRONOUNCED. IT ALSO UTILIZED THRUST VECTOR CONTROL (TVC), REQUIRING S TVC SYSTEM TO BE ADAPTED FOR THIS APPLICATION. THE SECOND STAGE GUIDANCE IS STILL BEING TRADED BETWEEN SPINNING AND TVC. THERE IS A STRONG DESIRE TO USE LOW COST, HIGH HERITAGE COMPONENTS WHERE POSSIBLE. THE MAV MUST SURVIVE EARTH LAUNCH, CRUISE TRANSIT, ENTRY DESCENT AND LANDING AS WELL AS MARS SURFACE ENVIRONMENTS. SEE THE ATTACHED ENVIRONMENTAL REQUIREMENTS DOCUMENT (ERD) FOR DETAILED ENVIRONMENTAL SPECIFICATIONS. GENERAL: THE STRAWMAN MAV DESIGN ASSUMES THAT IT WILL BE LOWERED TO THE SURFACE OF MARS ON A HERITAGE, SKY-CRANE LANDER. PROPELLANT MASS IS BASED ON A METASTUDY OF ~20 YEARS OF SOLID PROPELLANT MAV DESIGNS. THE CURRENT MAXIMUM OUTER DIAMETER (NOT INCLUDING RCS OR CONNECTION ADAPTERS) IS ASSUMED TO BE 15 INCHES AND THE MAXIMUM STAGE 1 MOTOR LENGTH IS 0.9M. REDUCTIONS IN ENVELOPE ARE DESIRABLE AS THESE ARE PRELIMINARY ESTIMATES OF THE GEOMETRY. ALL MASSES HAVE ASSUMED A CURRENT BEST ESTIMATE PLUS 43% MARGIN. WHILE THIS CONTINGENCY MAY SEEM HIGH FOR A SOLID ROCKET MOTOR, IT IS EXPECTED THAT THE SYSTEM DESIGN WILL REQUIRE ANY ADDITIONAL MARGIN PROVIDED BY THE PROPULSION SYSTEM. IT IS ASSUMED THAT ANY RESIDUAL MARGIN WILL BE COMPENSATED FOR BY OFFLOADING PROPELLANT ( Other Administrative Action ($3k) 6/3/14 2 NASA HAS IDENTIFIED THE NEED FOR RISK REDUCTION WITH RESPECT TO THE FIRST STAGE OF A TWO STAGE MAV, WHICH WILL BE CAPABLE OF INJECTING AN ORBITING SAMPLE INTO MARS ORBIT. THE FIRST STAGE HAS BEEN CHOSEN BECAUSE MANY CHALLENGES LIE IN ITS DESIGN. BOTH STAGES ARE ASSUMED TO BE SOLID ROCKET MOTORS WITH A PROPELLANT CAPABLE OF LOW TEMPERATURE STORAGE AND OPERATION. THE FIRST STAGE IS THE LARGER OF THE TWO MOTORS, MAKING GRAIN STRESSES MORE PRONOUNCED. IT ALSO UTILIZED THRUST VECTOR CONTROL (TVC), REQUIRING S TVC SYSTEM TO BE ADAPTED FOR THIS APPLICATION. THE SECOND STAGE GUIDANCE IS STILL BEING TRADED BETWEEN SPINNING AND TVC. THERE IS A STRONG DESIRE TO USE LOW COST, HIGH HERITAGE COMPONENTS WHERE POSSIBLE. THE MAV MUST SURVIVE EARTH LAUNCH, CRUISE TRANSIT, ENTRY DESCENT AND LANDING AS WELL AS MARS SURFACE ENVIRONMENTS. SEE THE ATTACHED ENVIRONMENTAL REQUIREMENTS DOCUMENT (ERD) FOR DETAILED ENVIRONMENTAL SPECIFICATIONS. GENERAL: THE STRAWMAN MAV DESIGN ASSUMES THAT IT WILL BE LOWERED TO THE SURFACE OF MARS ON A HERITAGE, SKY-CRANE LANDER. PROPELLANT MASS IS BASED ON A METASTUDY OF ~20 YEARS OF SOLID PROPELLANT MAV DESIGNS. THE CURRENT MAXIMUM OUTER DIAMETER (NOT INCLUDING RCS OR CONNECTION ADAPTERS) IS ASSUMED TO BE 15 INCHES AND THE MAXIMUM STAGE 1 MOTOR LENGTH IS 0.9M. REDUCTIONS IN ENVELOPE ARE DESIRABLE AS THESE ARE PRELIMINARY ESTIMATES OF THE GEOMETRY. ALL MASSES HAVE ASSUMED A CURRENT BEST ESTIMATE PLUS 43% MARGIN. WHILE THIS CONTINGENCY MAY SEEM HIGH FOR A SOLID ROCKET MOTOR, IT IS EXPECTED THAT THE SYSTEM DESIGN WILL REQUIRE ANY ADDITIONAL MARGIN PROVIDED BY THE PROPULSION SYSTEM. IT IS ASSUMED THAT ANY RESIDUAL MARGIN WILL BE COMPENSATED FOR BY OFFLOADING PROPELLANT ( Other Administrative Action $0 6/3/14 1 NASA HAS IDENTIFIED THE NEED FOR RISK REDUCTION WITH RESPECT TO THE FIRST STAGE OF A TWO STAGE MAV, WHICH WILL BE CAPABLE OF INJECTING AN ORBITING SAMPLE INTO MARS ORBIT. THE FIRST STAGE HAS BEEN CHOSEN BECAUSE MANY CHALLENGES LIE IN ITS DESIGN. BOTH STAGES ARE ASSUMED TO BE SOLID ROCKET MOTORS WITH A PROPELLANT CAPABLE OF LOW TEMPERATURE STORAGE AND OPERATION. THE FIRST STAGE IS THE LARGER OF THE TWO MOTORS, MAKING GRAIN STRESSES MORE PRONOUNCED. IT ALSO UTILIZED THRUST VECTOR CONTROL (TVC), REQUIRING S TVC SYSTEM TO BE ADAPTED FOR THIS APPLICATION. THE SECOND STAGE GUIDANCE IS STILL BEING TRADED BETWEEN SPINNING AND TVC. THERE IS A STRONG DESIRE TO USE LOW COST, HIGH HERITAGE COMPONENTS WHERE POSSIBLE. THE MAV MUST SURVIVE EARTH LAUNCH, CRUISE TRANSIT, ENTRY DESCENT AND LANDING AS WELL AS MARS SURFACE ENVIRONMENTS. SEE THE ATTACHED ENVIRONMENTAL REQUIREMENTS DOCUMENT (ERD) FOR DETAILED ENVIRONMENTAL SPECIFICATIONS. GENERAL: THE STRAWMAN MAV DESIGN ASSUMES THAT IT WILL BE LOWERED TO THE SURFACE OF MARS ON A HERITAGE, SKY-CRANE LANDER. PROPELLANT MASS IS BASED ON A METASTUDY OF ~20 YEARS OF SOLID PROPELLANT MAV DESIGNS. THE CURRENT MAXIMUM OUTER DIAMETER (NOT INCLUDING RCS OR CONNECTION ADAPTERS) IS ASSUMED TO BE 15 INCHES AND THE MAXIMUM STAGE 1 MOTOR LENGTH IS 0.9M. REDUCTIONS IN ENVELOPE ARE DESIRABLE AS THESE ARE PRELIMINARY ESTIMATES OF THE GEOMETRY. ALL MASSES HAVE ASSUMED A CURRENT BEST ESTIMATE PLUS 43% MARGIN. WHILE THIS CONTINGENCY MAY SEEM HIGH FOR A SOLID ROCKET MOTOR, IT IS EXPECTED THAT THE SYSTEM DESIGN WILL REQUIRE ANY ADDITIONAL MARGIN PROVIDED BY THE PROPULSION SYSTEM. IT IS ASSUMED THAT ANY RESIDUAL MARGIN WILL BE COMPENSATED FOR BY OFFLOADING PROPELLANT ( Other Administrative Action $0 2/12/14 Not listed - NASA HAS IDENTIFIED THE NEED FOR RISK REDUCTION WITH RESPECT TO THE FIRST STAGE OF A TWO STAGE MAV, WHICH WILL BE CAPABLE OF INJECTING AN ORBITING SAMPLE INTO MARS ORBIT. THE FIRST STAGE HAS BEEN CHOSEN BECAUSE MANY CHALLENGES LIE IN ITS DESIGN. BOTH STAGES ARE ASSUMED TO BE SOLID ROCKET MOTORS WITH A PROPELLANT CAPABLE OF LOW TEMPERATURE STORAGE AND OPERATION. THE FIRST STAGE IS THE LARGER OF THE TWO MOTORS, MAKING GRAIN STRESSES MORE PRONOUNCED. IT ALSO UTILIZED THRUST VECTOR CONTROL (TVC), REQUIRING S TVC SYSTEM TO BE ADAPTED FOR THIS APPLICATION. THE SECOND STAGE GUIDANCE IS STILL BEING TRADED BETWEEN SPINNING AND TVC. THERE IS A STRONG DESIRE TO USE LOW COST, HIGH HERITAGE COMPONENTS WHERE POSSIBLE. THE MAV MUST SURVIVE EARTH LAUNCH, CRUISE TRANSIT, ENTRY DESCENT AND LANDING AS WELL AS MARS SURFACE ENVIRONMENTS. SEE THE ATTACHED ENVIRONMENTAL REQUIREMENTS DOCUMENT (ERD) FOR DETAILED ENVIRONMENTAL SPECIFICATIONS. GENERAL: THE STRAWMAN MAV DESIGN ASSUMES THAT IT WILL BE LOWERED TO THE SURFACE OF MARS ON A HERITAGE, SKY-CRANE LANDER. PROPELLANT MASS IS BASED ON A METASTUDY OF ~20 YEARS OF SOLID PROPELLANT MAV DESIGNS. THE CURRENT MAXIMUM OUTER DIAMETER (NOT INCLUDING RCS OR CONNECTION ADAPTERS) IS ASSUMED TO BE 15 INCHES AND THE MAXIMUM STAGE 1 MOTOR LENGTH IS 0.9M. REDUCTIONS IN ENVELOPE ARE DESIRABLE AS THESE ARE PRELIMINARY ESTIMATES OF THE GEOMETRY. ALL MASSES HAVE ASSUMED A CURRENT BEST ESTIMATE PLUS 43% MARGIN. WHILE THIS CONTINGENCY MAY SEEM HIGH FOR A SOLID ROCKET MOTOR, IT IS EXPECTED THAT THE SYSTEM DESIGN WILL REQUIRE ANY ADDITIONAL MARGIN PROVIDED BY THE PROPULSION SYSTEM. IT IS ASSUMED THAT ANY RESIDUAL MARGIN WILL BE COMPENSATED FOR BY OFFLOADING PROPELLANT ( Not listed $704.6k 12/17/13