PATENT CLAIM ANALYSIS

Application Number: 16177313
Application Type: Utility
Filing Date: 2018-10
Publication Date: 2019-03
Patent Classification: ["290", "00100R"]

Abstract:
In an embodiment, an integrated ground support system for an aircraft is described herein, the system including a frame on which the system is arranged as a singular assembly. An engine, drive train, alternator, bleed air unit, one or more electrical components, and air cycle machine are mounted on the frame. The engine operates at a first operational state associated with a first rotational speed that is independent of a frequency associated with electrical power, if only the electrical power is to be used by the aircraft, and the engine operates at a second operational state associated with a second rotational speed, different from the first rotational speed, that is a function of a pressure associated with bleed air or the conditioned air, if the electrical power and one of the bleed air or the conditioned air are to be used simultaneously by the aircraft.

Claim (Index 1):
An integrated ground support system for an aircraft, the system comprising:\n a frame on which the system is arranged as a singular assembly; an engine mounted on the frame and configured to power the system; a drive train, an alternator, and a bleed air unit mounted on the frame, the drive train disposed between and interconnected to the engine and each of the alternator and the bleed air unit; one or more electrical components mounted on the frame and electrically connected to the alternator, wherein the one or more electrical components is configured to produce electrical power for use by the aircraft; and an air cycle machine mounted on the frame and connected to the bleed air unit, wherein the bleed air unit is configured to produce bleed air for use by the aircraft and the air cycle machine is configured to produce conditioned air for use by the aircraft, wherein the engine operates at a first operational state associated with a first rotational speed that is independent of a frequency associated with the electrical power, if only the electrical power is to be used by the aircraft, and the engine operates at a second operational state associated with a second rotational speed, different from the first rotational speed, that is a function of a pressure associated with the bleed air or the conditioned air, if the electrical power and one of the bleed air or the conditioned air are to be used simultaneously by the aircraft.

Metadata:
- Claim Count in Document: 37.0
- Percentile: 97.0
- Lexical Diversity: 2.28571
- Patent Class: 290.0
- Transitional Phrase Type: open
- Component Type: 1
- Foreign Priority: False
- Related Applications: ['11693532', '10927993', '15244557', '11681686', '11944199']

Analysis Scores:
- 35 USC 101 Eligibility (BERT): 0.6173730405994782
- 35 USC 102 Novelty (BERT): 0.4780212119125612
- Combined Prediction Score: 0.6034378577307865
- Mean Citation Score: 211.96727
- Max Citation Score: 223.29752
- Similarity Product: 183.60862374423027

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