Attachment A-22 RWO 2.docx

REPRESENTATIVE WORK ORDER (RWO) 2

SWO INFORMATION

WORK DESCRIPTION

Work Description:

Pursuant to the Provisions of the above Subcontract, the Subcontractor is authorized to proceed with the work as follows:

Statement of Work: See below for SOW.

* Please fill out this section only if you chose “Level of Effort” under Effort Type.

FINANCIAL SUMMARY

SIGNATURE BLOCKS

Introduction An interplanetary orbiter and large-scale probe is being proposed. Need to estimate the structure required to support the spacecraft and perform proof-of-concept preliminary sizing. The spacecraft has a cylindrical bus with propellant tanks mounted on the inside. There is a solar panel mounted on the side of the cylinder and a high gain antenna also mounted on the side of the cylinder. Radiators, boxes and instruments fill out the rest of the cylinder. On top is a massive probe for planetary exploration.

Analysis Overview The task is to create a finite element model of the structure and perform initial sizing for the structural components. The structural components include the cylindrical bus, solar array attachments, antenna support structure, engine support structure and the probe attachment structure. Assume the main cylindrical bus is a graphite honeycomb construction. The probe is not to be sized in this study.

Perform the following Tasks

1. Perform first pass structural sizing and stress analysis.

1.1. Create a finite element model for the spacecraft. The model should accurately represent the load paths and pass basic model checks to ensure numeric well conditioning. If the finite element analysis is performed using a solver other than Nastran the contractor is responsible for ensuring the other solver results are within 2% of the Nastran results.

1.2. Perform static stress analysis for the primary structural components using the acceleration loading in the table below. For secondary structure use the MAC curve shown below.

1.3. Perform modal analysis to ensure the spacecraft can meet the following stiffness requirements:

1.4. Prepare a high-level summary to present to JPL.

2. Propose design changes to JPL to optimize the design. Assume ½ day remote meeting to review results and provide recommendations.

3. Perform second pass structural sizing and stress analysis. This should be done using the configuration agreed upon with JPL in Task 2. Prepare a high-level summary to present to JPL.

4. Propose design changes to JPL to optimize the design. Assume ½ day remote meeting to review results and provide recommendations.

5. Perform third pass structural sizing and stress analysis. This should be done using the configuration agreed upon with JPL in Task 4. Prepare a high-level summary to present to JPL.

6. Prepare a final report of all the analysis performed on this contract. This should include the three iterations and the rationale to for proposing the changes/updates for each configuration.

Deliverables The following are the deliverables from this contract:

1. A Nastran bulk data format finite element model of the final iteration of the spacecraft from Task 5.

2. A final stress report from Task 6 that address the following …

· Finite element model: assumptions, checkout results, constraint.

· Loading: types of loading used in the analysis.

· Piece Part Analysis; margin summaries of the piece parts.

· Assembly analysis: margin summaries of the bolted/boned joint analysis.

Provided Information As part of this statement of work, JPL will provide the following items:

1. CAD model of Spacecraft.

2. Mass list of major components.

JPL 7478 Rev 05/22 image1.png image2.png image3.png image4.png