# US 12,761,239 B2 · Aircraft laser system with a corrective optical device

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- Number: US 12,761,239 B2
- Document ID: US12761239B2
- Status: Granted
- Kind: B2
- Application number: 18/061,419
- Filed: 2022-12-02
- Published: 2024-06-06
- Granted: 2026-10-13
- Earliest claimed: 2022-12-02
- Assignees: The Boeing Company
- Applicants: The Boeing Company
- Inventors: Nathan D. Hiller; Robert M. Dowgwillo; Ishaan Bakhle
- Web page: https://patentgrep.com/patent/US12761239B2

## CPC

- G01P 5/26: by measuring the direct influence of the streaming fluid on the properties of a detecting optical wave
- B64D 47/02: Arrangements or adaptations of signal or lighting devices
- G01S 7/481: Constructional features, e.g. arrangements of optical elements
- G01S 7/4814: {of transmitters alone}
- G01S 7/497: Means for monitoring or calibrating
- G02B 27/0068: {having means for controlling the degree of correction, e.g. using phase modulators, movable elements (controlling the phase of light using moving or deformable elements G02B26/06)}
- G01P: MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT (measuring or recording blood flow A61B5/02, A61B8/06; monitoring speed or deceleration of electrically-propelled vehicles B60L3/00; vehicle lighting systems adapted to indicate speed B60Q1/54; determining position or course in navigation, measuring ground distance in geodesy or surveying G01C; combined measuring devices for measuring two or more variables of movement G01C23/00; measuring velocity of sound G01H; measuring velocity of light G01J7/00; measuring direction or velocity of solid objects by reception or emission of radiowaves or other waves and based on propagation effects, e.g. Doppler effect, propagation time, direction of propagation, G01S; measuring speed of nuclear radiation G01T; measuring acceleration of gravity G01V; {measuring or recording the speed of trains B61L23/00; speed indicators incorporated in motor vehicles B60K35/00; measuring frequency or phase G01R; traffic control G08G})
- B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- G01S: RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G02B: OPTICAL ELEMENTS, SYSTEMS OR APPARATUS

## Abstract

A laser sensor system comprising a laser beam generator, a corrective optical device, an interference system, a detection system, and an analyzer. The laser beam generator is configured to emit a laser beam on a path from an aircraft. The corrective optical device is positioned in the path of the laser beam. The corrective optical device reduces distortion from the laser beam from passing through a turbulent air. The interference system is configured to interfere a backscatter light with a reference light to form an interfered light having a power in response to receiving the backscatter light. The detection system is configured to measure a set of characteristics for the interfered light. The analyzer is configured to determine a set of parameters for the aircraft using the set of characteristics.

## Claims

### Claim 1

A laser sensor system comprising:
a laser beam generator configured to emit a laser beam on a path from an aircraft;
a corrective optical lens positioned in the path of the laser beam, wherein the corrective lens includes multiple sections having varying thicknesses relative to optical path differences through the sections, wherein the corrective optical lens reduces distortion from the laser beam from passing through a turbulent air;
an interference system configured to interfere a backscatter light with a reference light to form an interfered light having a power in response to receiving the backscatter light;
a detection system configured to measure a set of characteristics for the interfered light; and
an analyzer configured to determine a set of parameters for the aircraft using the set of characteristics.

### Claim 2 (depends on 1)

The laser sensor system of claim 1, wherein the corrective lens is comprised of a transparent material.

### Claim 3 (depends on 1)

The laser sensor system of claim 1, wherein the corrective lens is comprised of:
a material that changes an optical path length of the laser beam based on a thickness of the material; and
the sections in the corrective lens in which the material has thicknesses selected to compensate for changes in the optical path length of the laser beam in response to the laser beam passing through the turbulent air and the sections.

### Claim 4 (depends on 3)

The laser sensor system of claim 3, wherein the thicknesses for the sections are based on an optical path length change caused by the turbulent air at the sections.

### Claim 5 (depends on 4)

The laser sensor system of claim 4, wherein a selected thickness for a selected section is greater than a base thickness such that the optical path length is increased for the laser beam passing through the selected section as compared using the base thickness.

### Claim 6 (depends on 4)

The laser sensor system of claim 4, wherein a selected thickness for a selected section is less than a base thickness such that the optical path length is decreased for the laser beam passing through the selected section as compared using the base thickness.

### Claim 7 (depends on 1)

The laser sensor system of claim 1, wherein the set of characteristics is selected from at least one of a beat frequency, a power, polarization, or wavelength, or an intensity.

### Claim 8 (depends on 1)

The laser sensor system of claim 1, wherein the set of parameters is selected from at least one of a speed, an angle of sideslip, an angle of attack, or an aerodynamic efficiency.

### Claim 9

A method for determining a set of parameters for an aircraft, the method comprising:
emitting a laser beam on a path;
directing the laser beam through a corrective optical lens positioned in the path of the laser beam, wherein the corrective optical lens includes multiple sections having varying thickness relative to optical path differences through the sections,
wherein the corrective optical lens reduces distortion from the laser beam from passing through turbulent air;
interfering a backscatter light with a reference light to form an interfered light in response to receiving the backscatter light;
measuring a set of characteristics for the interfered light; and
determining the set of parameters for the aircraft using the set of characteristics.

### Claim 10 (depends on 9)

The method of claim 9, wherein the corrective optical lens reduces changes in an optical path length for portions of the laser beam caused by the laser beam passing through the turbulent air.

### Claim 11 (depends on 9)

The method of claim 9, wherein the set of characteristics is selected from at least one of a beat frequency, a power, polarization, or wavelength, or an intensity.

### Claim 12 (depends on 9)

The method of claim 9, wherein the set of parameters is selected from at least one of a speed, an angle of sideslip, an angle of attack, or an aerodynamic efficiency.

### Claim 13 (depends on 9)

The method of claim 9, wherein the corrective lens is comprised of a transparent material.

### Claim 14 (depends on 9)

The method of claim 9, wherein the corrective lens is comprised of:
a material that changes an optical path length of the laser beam based on a thickness of the material; and
the sections in the corrective lens in which the material has thicknesses selected to compensate for changes in the optical path length of the laser beam in response to the laser beam passing through the turbulent air and the sections.

### Claim 15 (depends on 14)

The method of claim 14, wherein the thicknesses for the sections are based on an optical path length change caused by the turbulent air at the sections.

### Claim 16 (depends on 14)

The method of claim 14, wherein a selected thickness for a selected section is greater than a base thickness such that the optical path length is increased for the laser beam passing through the selected section as compared using the base thickness.

### Claim 17 (depends on 14)

The method of claim 14, wherein a selected thickness for a selected section is less than a base thickness such that the optical path length is decreased for the laser beam passing through the selected section as compared using the base thickness.