PATENT CLAIM ANALYSIS

Application Number: 16005345
Application Type: Utility
Filing Date: 2018-06
Publication Date: 2019-05
Patent Classification: ["244", "006000"]

Abstract:
This disclosure is generally directed to a High Speed vertical takeoff and landing (VTOL) aircraft that includes fixed wing flight capabilities. The High Speed VTOL aircraft may include at least two thrust producing rotors located equidistant from a longitudinal axis of the aircraft on a main wing, and at least two thrust producing rotors located equidistant from a longitudinal axis of the aircraft on a vertical wing. The rotors may be driven by electric motors. However, other power sources may be used such as combustion or hybrid engines. By adjusting the speed and/or the pitch of the rotors, the aircraft can transition from a vertical flight configuration to a horizontal flight configuration and back.

Claim (Index 20):
A system for maneuvering a vertical takeoff and landing (VTOL) aircraft comprising:\n a first propulsion system coupled to a first wing at a first distance from a longitudinal axis, the first propulsion system comprising a first engine and a first rotor; a second propulsion system coupled to the first wing at the first distance from the longitudinal axis, the second propulsion system comprising a second engine and a second rotor; a third propulsion system coupled to a second wing at a second distance from the longitudinal axis the third propulsion system comprising a third engine and a third rotor; a fourth propulsion system coupled to the second wing at the second distance from the longitudinal axis, the fourth propulsion system comprising a fourth engine and a fourth rotor; a control management system coupled to the first, second, third, and fourth propulsion systems causing the aircraft to:\n spin the first, second, third, and fourth rotors at a hover rate or a hover pitch, the hover rate or hover pitch being sufficient to provide thrust to overcome the weight of the aircraft; \n spin the first and second rotors at different rates or pitches than the third and fourth rotors while in a hover, wherein the spinning the first and second rotors at different rates or different pitches from the third and fourth rotors produces a roll motion of the aircraft; \n spin the third and fourth rotors at different rates or different pitches than the first and second rotors while in the hover, wherein the spinning the first and second rotors at different rates or different pitches from the first and second rotors produces a pitch motion of the aircraft; \n spin the first and second rotors at different rates or different pitches than the third and fourth rotors while in a forward flight regime, wherein the spinning the first and second rotors at different rates or different pitches from the third and fourth rotors produces a yaw motion of the aircraft; and \n spin the third and fourth rotors at different rates or different pitches than the first and second rotors while in the forward flight regime, wherein the spinning the first and second rotors at different rates or different pitches from the first and second rotors produces a pitch motion of the aircraft.

Metadata:
- Claim Count in Document: 50.0
- Percentile: 94.0
- Lexical Diversity: 1.7971
- Patent Class: 244.0
- Transitional Phrase Type: open
- Component Type: 1
- Foreign Priority: False
- Related Applications: ['14554892', '13708612', '14738675', '14559529', '15093845']

Analysis Scores:
- 35 USC 101 Eligibility (BERT): 0.8694075149944349
- 35 USC 102 Novelty (BERT): 0.5615201562382687
- Combined Prediction Score: 0.8386187791188183
- Mean Citation Score: 347.205998
- Max Citation Score: 476.07635
- Similarity Product: 400.8470680146128

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

Dataset: test