PATENT CLAIM ANALYSIS

Application Number: 16036743
Application Type: Utility
Filing Date: 2018-07
Publication Date: 2018-11
Patent Classification: ["244", "058000"]

Abstract:
An air vehicle power and thermal management system includes an aircraft controller structured to distribute power provided by a gas turbine engine between a cooling system and an electrically powered load. The controller is configured to direct the power to create a first duration cooling power to the cooling system to cool the engine fuel cooling medium over a first power time period. The controller is configured to shift the power to reduce the first duration cooling power to create a load electrical power to drive the electrically powered load over a second power time period. By operation of the controller to shift the power from the first duration cooling power to the load electrical power a second duration cooling power is provided to the cooling system to cool the electrically powered load using the engine fuel cooling medium that was cooled during the first power time period.

Claim (Index 28):
An aircraft thermal regulation system for thermally cooling an electrically driven aircraft component, comprising:\n a first thermal management device, a first electrically driven aircraft component, an aircraft power source, and an air vehicle control unit, the first thermal management device further comprising:\n a first refrigeration system powered by the aircraft power source; \n a first heat sink reservoir; \n first fluid control devices coupled between the first refrigeration system and the first heat sink reservoir; \n second fluid control devices coupled between the first heat sink reservoir and a first electrically driven aircraft component; and \n the air vehicle control unit configured to:\n direct a first heat sink fluid from the first thermal management device to the first heat sink reservoir, via control of the first fluid control devices, to cool the first heat sink reservoir; and \n direct the first heat sink fluid from the first heat sink reservoir to the first electrically driven aircraft component, via the second fluid control devices, to cool the first electrically driven aircraft component using the first heat sink reservoir.

Metadata:
- Claim Count in Document: 2.0
- Percentile: 95.0
- Lexical Diversity: 2.76364
- Patent Class: 244.0
- Transitional Phrase Type: open
- Component Type: 1
- Foreign Priority: False
- Related Applications: ['14692104', '15044523', '15433681', '15358444', '13215456']

Analysis Scores:
- 35 USC 101 Eligibility (BERT): 0.810357216608302
- 35 USC 102 Novelty (BERT): 0.481110885126742
- Combined Prediction Score: 0.777432583460146
- Mean Citation Score: 168.532492
- Max Citation Score: 246.04639
- Similarity Product: 212.7197277547097

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

Dataset: test