PATENT CLAIM ANALYSIS

Application Number: 16127640
Application Type: Utility
Filing Date: 2018-09
Publication Date: 2019-01
Patent Classification: ["244", "00700R"]

Abstract:
Systems, methods, and devices provide a vehicle, such as an aircraft, with rotors configured to function as a tri-copter for vertical takeoff and landing (“VTOL”) and a fixed-wing vehicle for forward flight. One rotor may be mounted at a front of the vehicle fuselage on a hinged structure controlled by an actuator to tilt from horizontal to vertical positions. Two additional rotors may be mounted on the horizontal surface of the vehicle tail structure with rotor axes oriented vertically to the fuselage. For forward flight of the vehicle, the front rotor may be rotated down such that the front rotor axis may be oriented horizontally along the fuselage and the front rotor may act as a propeller. For vertical flight, the front rotor may be rotated up such that the front rotor axis may be oriented vertically to the fuselage, while the tail rotors may be activated.

Claim (Index 19):
A tri-rotor vehicle, comprising:\n a wing having no rotors coupled thereto; a tail comprising two horizontal tail sections; a fuselage; two tail rotors coupled to the tail, wherein the two horizontal tail sections extend horizontally relative to the fuselage and from opposite sides of the fuselage, wherein each of the two tail rotors has a single corresponding respective horizontal tail section, and wherein each of the two tail rotors is coupled only to its own respective one of the two horizontal tail sections; and a front rotor coupled to a front hinged portion of the fuselage controlled by an actuator, wherein the front rotor is configured to tilt through a range of motion by control of the actuator and wherein the vehicle is configured to transition between a wing born flight phase and a VTOL flight phase by the front rotor tilting through the range of motion; and a front rotor motor configured to drive the front rotor and two tail rotor motors, each tail rotor motor configured to drive a respective one of the tail rotors, wherein the front rotor motor is selected from the group consisting of a fuel burning engine and an electric motor and each of the two tail rotor motors is selected from the group consisting of a fuel burning engine and an electric motor, wherein:\n the two tail rotors are coupled to the tail such that rotor axes of each of the two tail rotors are configured to orient vertically relative to the fuselage during the VTOL flight phase and horizontally during the wing born flight phase; and \n the front rotor and two tail rotors are cyclic and collective controlled rotors.

Metadata:
- Claim Count in Document: 1.0
- Percentile: 97.0
- Lexical Diversity: 2.32857
- Patent Class: 244.0
- Transitional Phrase Type: open
- Component Type: 1
- Foreign Priority: False
- Related Applications: ['15080167', '15332391', '14121001', '15494780', '13708612']

Analysis Scores:
- 35 USC 101 Eligibility (BERT): 0.8814351742599834
- 35 USC 102 Novelty (BERT): 0.6742385710296871
- Combined Prediction Score: 0.8607155139369538
- Mean Citation Score: 479.86585
- Max Citation Score: 700.92676
- Similarity Product: 688.4125980566023

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

Dataset: test