PATENT CLAIM ANALYSIS

Application Number: 16101000
Application Type: Utility
Filing Date: 2018-08
Publication Date: 2019-02
Patent Classification: ["060", "258000"]

Abstract:
Provided herein are various improvements to rocket engine components and rocket engine operational techniques. In one example, a rocket engine propellant injection apparatus is provided that includes a manifold formed into a single body by an additive manufacturing process and comprising a fuel cavity and an oxidizer cavity. The manifold also includes one or more propellant feed stubs, the one or more propellant feed stubs protruding from the manifold and formed into the single body of the manifold by the additive manufacturing process, with at least a first stub configured to carry fuel to the fuel cavity and at least a second stub configured to carry oxidizer to the oxidizer cavity. The manifold also includes a plurality of injection features formed by apertures in a face of the manifold, ones of the plurality of injection features configured to inject the fuel and the oxidizer for combustion.

Claim (Index 16):
A method comprising:\n forming an injector assembly for a rocket engine into a body by an additive manufacturing process, wherein the body of the injector assembly comprises a fuel cavity and an oxidizer cavity that forms a generally toroidal shape around the fuel cavity; forming at least a first feed stub into a first face of the body and tapering outwards from a central position on the first face of the body by the additive manufacturing process to provide a first channel to carry fuel to the fuel cavity; forming at least a second feed stub into the first face of the body and tapering outwards from a position offset from the central position on the first face of the body by the additive manufacturing process to provide a second channel to carry oxidizer to the oxidizer cavity; forming propellant injection features into the body by the additive manufacturing process in a second face of the injector assembly opposite the first face of the injector assembly; and attaching a first compression fitting to the first feed stub and a second compression fitting to the second feed stub in a metal-to-metal seal, the first and second compression fittings each mechanically swaged or flared to couple to associated propellant lines.

Metadata:
- Claim Count in Document: 7.0
- Percentile: 96.0
- Lexical Diversity: 2.33333
- Patent Class: 60.0
- Transitional Phrase Type: open
- Component Type: 1
- Foreign Priority: False
- Related Applications: ['15285324', '11479082', '14229823', '11805016', '11787585']

Analysis Scores:
- 35 USC 101 Eligibility (BERT): 0.7258598255959268
- 35 USC 102 Novelty (BERT): 0.5755252858715044
- Combined Prediction Score: 0.7108263716234845
- Mean Citation Score: 292.4756260000001
- Max Citation Score: 478.2507
- Similarity Product: 455.4284553749621

Labels:
- Claim Label 101: 1
- Claim Label 102: 1
- Claim Label 103: 1
- Claim Label 112: 1
- Combined Label: 1
- Label 101 Adjusted: 0

Dataset: test