Tab 04 SOW.pdf

Requirements Document for Mach 6 Nozzle Redesign

Performance Period:

The work will be performed over a four-month period (note that some deliverables can and should be provided earlier, see the deliverables section below).

Scope:

Performer will leverage the work performed on the original NASA funded eƯort to design a modified Liner 2 model. An additional analysis eƯort will be quoted as an option if NASA chooses to fund it.

Objectives:

Modify the existing Mach 6 nozzle design to include “shelf” features on the blade inserts that will resist inward motion observed in the original design.

Supply preliminary drawings one month from award that can be used for fabrication quoting purposes

Supply final released drawings of the modified parts two months from award Evaluate the mechanical performance of the design using loads pulled from the CDR eƯort of the original nozzle design.

Requirements:

1. Create the new models – Design: Design and model the Mach 6 nozzle components to add a shelf feature that will prevent the inward motion of the blade inserts. The following parts may be impacted by the design change: MSX-57909, MSX-57931, MSX-57935, MSX-57939, MSX-57933, MSX-57930. Perform hand calculations evaluating the strength of the new ledge feature.

2. Create the new drawings – Design: After models are created, drawings will be created or revised detailing the changes. Preliminary versions will be supplied to NASA to assist in quoting the fabrication eƯort. All eƯorts will be made to reuse existing parts to minimize the turn-around time for making the new design. Revised drawings shall not change the original design’s part number, only add an additional dash number to the drawing. This SOW covers the following parts as follows:

a. MSX-57909, Inner Case Assembly, Liner Two: New Drawing.

b. MSX-57931, Liner Two Inner Case Weldment: Revised drawing to add a new configuration

c. MSX-57933, Liner Two Inner Case: New Drawing

d. MSX-57935, Liner Two Insert: New Drawing

e. MSX-57939 (if needed), Throat Retaining Ring: New drawing may be required if reuse of existing part isn’t feasible.

f. MSX-57930, Assembly, Liner Two: Revised drawing to include alternate liner.

3. Classical Calculations of the Design- Analysis: Classical calculations (non-FEA) of the new design will be performed to compare the modified blade inserts strength against the strength of the blades analyzed in the first modification eƯort performed in early 2026. This eƯort evaluates the absolute strength of the blade to resist inward motion at an assumed temperature. It does not consider any thermal deformations due to operation.

Deliverables:

3D models in step file format will be supplied to NASA

Preliminary drawings of the preliminary design in .pdf format Final released drawings of the final design in .pdf format (modified drawings as described in

Requirements Task 2) Classical calculations from Requirements Task 3 in pdf format Optional Task (if funded): Analysis results from Requirements Task 4 in pdf PowerPoint presentation format

Government Furnished Information:

Geometric data of the existing mating interfaces as requested by performer

Reviews:

An informal (tabletop-level) review will be held at the 1 month from award point