US20210147093A1 - Parallel hybrid-electric aircraft engine - Google Patents
Parallel hybrid-electric aircraft engine Download PDFInfo
- Publication number
- US20210147093A1 US20210147093A1 US17/140,616 US202117140616A US2021147093A1 US 20210147093 A1 US20210147093 A1 US 20210147093A1 US 202117140616 A US202117140616 A US 202117140616A US 2021147093 A1 US2021147093 A1 US 2021147093A1
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- US
- United States
- Prior art keywords
- rotary shaft
- aircraft
- power
- electrical
- engine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
Links
- 238000002485 combustion reaction Methods 0.000 claims abstract description 10
- 238000000034 method Methods 0.000 claims 6
- 230000005611 electricity Effects 0.000 claims 1
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000009194 climbing Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D35/00—Transmitting power from power plant to propellers or rotors; Arrangements of transmissions
- B64D35/08—Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the transmission being driven by a plurality of power plants
-
- B64D27/026—
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D35/00—Transmitting power from power plant to propellers or rotors; Arrangements of transmissions
- B64D35/02—Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the type of power plant
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D2221/00—Electric power distribution systems onboard aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D31/00—Power plant control; Arrangement thereof
- B64D31/02—Initiating means
- B64D31/06—Initiating means actuated automatically
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- the present invention relates to hybrid power plants and, more particularly, to a parallel hybrid-electric powerplant aircraft engine.
- Aircraft go through phases of flight, commonly, takeoff, climb, cruise, descent and landing.
- takeoff and climb portion of the flight the aircraft engine is required to generate enough horsepower to accelerate and lift the aircraft to altitude.
- the physics of the problem is that power is needed to accelerate the mass of the aircraft and then once free from the runway additional power is needed to lift the aircraft against the force or gravity. Once at a given altitude and no longer climbing or accelerating the engine need only overcome the drag on the aircraft. This disproportionate power requirement means the aircraft needs to have a large powerplant that can perform the functions of accelerate and climb but then reduce power to that required to maintain level flight.
- the amount of power delivered by the typical engine is proportional to its weight. Therefore, an engine capable of getting an aircraft to it cruise altitude would be heavier than an engine used to maintain level flight. The additional weight of the powerful engine, then must be carried by the aircraft even though it's not yielding power from the additional weight.
- Serial Hybrid-Electric Aircraft engines which are a generator to provide power via wires to an electric motor turning a propeller.
- Serial Hybrid-Electric Aircraft engines can fail if the generator fails and battery power is lost. Serial Hybrid-Electric Aircraft engines can fail if the circuit between the generator and the propeller motor breaks. Serial Hybrid-Electric Aircraft engines can fail if the motor fails. Serial Hybrid-Electric Aircraft engines can fail if the engine on the generator fails.would be advantageous to provide an aircraft powerplant that can accelerate an aircraft to takeoff speed.
- a parallel hybrid-electric aircraft engine that provides power for takeoff and climb by combining the output power of an electric motor with that an internal combustion engine and then converting the electric motor to a generator once the additional power of the electric motor is no longer needed.
- FIG. 1 is a front perspective view of a parallel hybrid-electric aircraft engine
- FIG. 2 is a lower perspective view of a parallel hybrid-electric aircraft engine
- FIG. 3 is a left view of a parallel hybrid-electric aircraft engine
- FIG. 4 is a front view of a parallel hybrid-electric aircraft engine
- FIG. 5 is a top view of a parallel hybrid-electric aircraft engine
- FIG. 6 is a bottom view of a parallel hybrid-electric aircraft engine.
- FIG. 1 is a perspective view of a hybrid-electric aircraft engine consisting of an internal combustion engine 10 , sprag clutch 30 , flexible belt 40 , electric motor 50 and propeller 20 .
- FIG. 2 is a lower perspective view of parallel hybrid electric engine showing the internal combustion engine 10 , sprag clutch 30 , flexible belt 40 , electric motor 50 and propeller 20 .
- FIG. 3 is a left side view of a parallel hybrid-electric aircraft engine showing an internal combustion engine 10 , flexible belt 40 , electric motor 50 and propeller 20 .
- FIG. 4 is a front view of a parallel hybrid-electric aircraft engine showing an internal combustion engine 10 , sprag clutch 30 , flexible belt 40 , electric motor 50 , engine output shaft 60 and propeller 20 .
- FIG. 1 is a perspective view of a hybrid-electric aircraft engine consisting of an internal combustion engine 10 , sprag clutch 30 , flexible belt 40 , electric motor 50 and propeller 20 .
- FIG. 2 is a lower perspective view of parallel
- FIG. 5 is a top view of a parallel hybrid-electric aircraft engine showing an internal combustion engine 10 , flexible belt 40 , electric motor 50 and propeller 20 .
- FIG. 6 is a bottom view of a parallel hybrid-electric aircraft engine showing an internal combustion engine 10 , flexible belt 40 , electric motor 50 and propeller 20 .
Abstract
A parallel hybrid-electric aircraft engine that provides power for takeoff and climb by combining the output power of an electric motor with that an internal combustion engine and then converting the electric motor to a generator once the additional power of the electric motor is no longer needed.
Description
- The present application is a continuation-in-part application of U.S. provisional patent application Ser. No. 62/375,171, filed Aug. 15, 2016, for PARALLEL HYBRID-ELECTRIC AIRCRAFT ENGINE, by Marinus Bernard Bosma, included by reference herein and for which benefit of the priority date is hereby claimed.
- The present invention relates to hybrid power plants and, more particularly, to a parallel hybrid-electric powerplant aircraft engine.
- Aircraft go through phases of flight, commonly, takeoff, climb, cruise, descent and landing. For the takeoff and climb portion of the flight the aircraft engine is required to generate enough horsepower to accelerate and lift the aircraft to altitude. The physics of the problem is that power is needed to accelerate the mass of the aircraft and then once free from the runway additional power is needed to lift the aircraft against the force or gravity. Once at a given altitude and no longer climbing or accelerating the engine need only overcome the drag on the aircraft. This disproportionate power requirement means the aircraft needs to have a large powerplant that can perform the functions of accelerate and climb but then reduce power to that required to maintain level flight.
- The amount of power delivered by the typical engine is proportional to its weight. Therefore, an engine capable of getting an aircraft to it cruise altitude would be heavier than an engine used to maintain level flight. The additional weight of the powerful engine, then must be carried by the aircraft even though it's not yielding power from the additional weight.
- An engine that can be both lightweight and powerful would allow this.
- Serial Hybrid-Electric Aircraft engines which are a generator to provide power via wires to an electric motor turning a propeller.
- Serial Hybrid-Electric Aircraft engines can fail if the generator fails and battery power is lost. Serial Hybrid-Electric Aircraft engines can fail if the circuit between the generator and the propeller motor breaks. Serial Hybrid-Electric Aircraft engines can fail if the motor fails. Serial Hybrid-Electric Aircraft engines can fail if the engine on the generator fails.would be advantageous to provide an aircraft powerplant that can accelerate an aircraft to takeoff speed.
- It would also be advantageous to provide an aircraft powerplant that can provide excess horsepower for climb.
- It would further be advantageous to provide aircraft powerplant that throttle back to that power necessary for cruise flight.
- It would further be advantageous to provide aircraft powerplant that has good fuel economy by operating at maximum efficiency power settings.
- It would further be advantageous to provide aircraft powerplant that uses two different sources of power as a backup if one or the other fails.
- In accordance with the present invention, there is provided a parallel hybrid-electric aircraft engine that provides power for takeoff and climb by combining the output power of an electric motor with that an internal combustion engine and then converting the electric motor to a generator once the additional power of the electric motor is no longer needed.
- A complete understanding of the present invention may be obtained by reference to the accompanying drawings, when considered in conjunction with the subsequent, detailed description, in which:
-
FIG. 1 is a front perspective view of a parallel hybrid-electric aircraft engine; -
FIG. 2 is a lower perspective view of a parallel hybrid-electric aircraft engine; -
FIG. 3 is a left view of a parallel hybrid-electric aircraft engine; -
FIG. 4 is a front view of a parallel hybrid-electric aircraft engine; -
FIG. 5 is a top view of a parallel hybrid-electric aircraft engine; and -
FIG. 6 is a bottom view of a parallel hybrid-electric aircraft engine. - For purposes of clarity and brevity, like elements and components will bear the same designations and numbering throughout the Figures.
-
FIG. 1 is a perspective view of a hybrid-electric aircraft engine consisting of aninternal combustion engine 10,sprag clutch 30,flexible belt 40,electric motor 50 andpropeller 20.FIG. 2 is a lower perspective view of parallel hybrid electric engine showing theinternal combustion engine 10,sprag clutch 30,flexible belt 40,electric motor 50 andpropeller 20.FIG. 3 is a left side view of a parallel hybrid-electric aircraft engine showing aninternal combustion engine 10,flexible belt 40,electric motor 50 andpropeller 20.FIG. 4 is a front view of a parallel hybrid-electric aircraft engine showing aninternal combustion engine 10,sprag clutch 30,flexible belt 40,electric motor 50,engine output shaft 60 andpropeller 20.FIG. 5 is a top view of a parallel hybrid-electric aircraft engine showing aninternal combustion engine 10,flexible belt 40,electric motor 50 andpropeller 20.FIG. 6 is a bottom view of a parallel hybrid-electric aircraft engine showing aninternal combustion engine 10,flexible belt 40,electric motor 50 andpropeller 20. - Since other modifications and changes varied to fit particular operating requirements and environments will be apparent to those skilled in the art, the invention is not considered limited to the example chosen for purposes of disclosure, and covers all changes and modifications which do not constitute departures from the true spirit and scope of this invention.
- Having thus described the invention, what is desired to be protected by Letters Patent is presented in the subsequently appended claims.
Claims (6)
1. A method for takeoff and climb in an aircraft comprising:
powering a first mechanical-rotary shaft using a first internal combustion engine;
powering a first electrical-rotary shaft using electrical power stored in the electricity storage device or via connection to the first mechanical-rotary shaft;
applying to the takeoff and climb a portion of a thrust generated by the first mechanical-rotor; selectively applying to the takeoff and climb, in parallel with the first mechanical rotary shaft, at least a portion of a thrust generated by the first electrical-rotary shaft.
2. The method of claim 1 , wherein the selective applying of thrust of the first electrical-rotary shaft is accomplished via a connection between the first mechanical-rotary shaft, and the first electrical-rotary shaft via a clutch and belt.
3. The method of claim 2 , wherein generation of electrical power using the first internal combustion engine is accomplished via the connection and the electrical power generated is stored in a battery.
4. The method of claim 3 , wherein the electrical power generated is used to power accessories in an aircraft.
5. The method of claim 2 comprising a further step of removing power from either the first mechanical-rotary shaft or the first electrical-rotary shaft via the clutch.
6. The method of claim 5 , wherein the clutch is a sprag clutch.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US17/140,616 US20210147093A1 (en) | 2016-08-15 | 2021-01-04 | Parallel hybrid-electric aircraft engine |
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US201662375171P | 2016-08-15 | 2016-08-15 | |
US15/677,005 US10494117B2 (en) | 2017-08-14 | 2017-08-14 | Parallel hybrid-electric aircraft engine |
US16/690,735 US10882634B2 (en) | 2016-08-15 | 2019-11-21 | Parallel hybrid-electric aircraft engine |
US17/140,616 US20210147093A1 (en) | 2016-08-15 | 2021-01-04 | Parallel hybrid-electric aircraft engine |
Related Parent Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US16/690,735 Division US10882634B2 (en) | 2016-08-15 | 2019-11-21 | Parallel hybrid-electric aircraft engine |
Publications (1)
Publication Number | Publication Date |
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US20210147093A1 true US20210147093A1 (en) | 2021-05-20 |
Family
ID=65274714
Family Applications (3)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US15/677,005 Active 2037-11-18 US10494117B2 (en) | 2016-08-15 | 2017-08-14 | Parallel hybrid-electric aircraft engine |
US16/690,735 Active US10882634B2 (en) | 2016-08-15 | 2019-11-21 | Parallel hybrid-electric aircraft engine |
US17/140,616 Abandoned US20210147093A1 (en) | 2016-08-15 | 2021-01-04 | Parallel hybrid-electric aircraft engine |
Family Applications Before (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US15/677,005 Active 2037-11-18 US10494117B2 (en) | 2016-08-15 | 2017-08-14 | Parallel hybrid-electric aircraft engine |
US16/690,735 Active US10882634B2 (en) | 2016-08-15 | 2019-11-21 | Parallel hybrid-electric aircraft engine |
Country Status (1)
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US (3) | US10494117B2 (en) |
Families Citing this family (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10494117B2 (en) * | 2017-08-14 | 2019-12-03 | Marinus Bernard Bosma | Parallel hybrid-electric aircraft engine |
US11148820B1 (en) * | 2018-02-19 | 2021-10-19 | Parallel Flight Technologies, Inc. | System defining a hybrid power unit for thrust generation in an aerial vehicle and method for controlling the same |
WO2020137105A1 (en) * | 2018-12-27 | 2020-07-02 | 本田技研工業株式会社 | Flying object |
EP3931099A4 (en) | 2019-03-01 | 2022-11-30 | Pratt & Whitney Canada Corp. | Cooling system configurations for an aircraft having hybrid-electric propulsion system |
US11628942B2 (en) | 2019-03-01 | 2023-04-18 | Pratt & Whitney Canada Corp. | Torque ripple control for an aircraft power train |
US11574548B2 (en) | 2019-04-25 | 2023-02-07 | Pratt & Whitney Canada Corp. | Aircraft degraded operation ceiling increase using electric power boost |
US11667391B2 (en) | 2019-08-26 | 2023-06-06 | Pratt & Whitney Canada Corp. | Dual engine hybrid-electric aircraft |
US11912422B2 (en) | 2019-08-26 | 2024-02-27 | Hamilton Sundstrand Corporation | Hybrid electric aircraft and powerplant arrangements |
US11738881B2 (en) | 2019-10-21 | 2023-08-29 | Hamilton Sundstrand Corporation | Auxiliary power unit systems |
WO2022146943A1 (en) * | 2020-12-28 | 2022-07-07 | Parallel Flight Technologies, Inc. | System defining a hybrid power unit for thrust generation in an aerial vehicle and method for controlling the same |
WO2022192698A1 (en) | 2021-03-12 | 2022-09-15 | Essex Industries, Inc., | Rocker switch |
EP4309200A1 (en) | 2021-03-15 | 2024-01-24 | Essex Industries, Inc. | Five-position switch |
US11685537B1 (en) | 2022-08-19 | 2023-06-27 | Ampaire, Inc. | Parallel hybrid propulsion system |
Citations (7)
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US20100038473A1 (en) * | 2007-01-15 | 2010-02-18 | Heinz-Dieter Schneider | Aircraft Propeller Device, Method for Driving an Aircraft Propeller, Use of a Bearing for an Aircraft Propeller Drive and Use of an Electric Machine |
US20100064689A1 (en) * | 2007-04-11 | 2010-03-18 | Flight-Design-Gmbh Flugsportgeraete | Aircraft |
US20130227950A1 (en) * | 2012-03-05 | 2013-09-05 | Embry-Riddle Aeronautical University, Inc. | Hybrid assembly for an aircraft |
US20140010652A1 (en) * | 2012-07-09 | 2014-01-09 | Mcmaster University | Hybrid powertrain system |
US20160265631A1 (en) * | 2013-05-17 | 2016-09-15 | Perkins Engine Company Limited | A propulsion system |
US20170225573A1 (en) * | 2014-09-23 | 2017-08-10 | Sikorsky Aircraft Corporation | Hybrid electric power drive system for a rotorcraft |
US10882634B2 (en) * | 2016-08-15 | 2021-01-05 | Marinus Bernard Bosma | Parallel hybrid-electric aircraft engine |
Family Cites Families (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE112010004022T5 (en) * | 2009-10-13 | 2012-12-27 | Honda Motor Co., Ltd. | hybrid vehicle |
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2017
- 2017-08-14 US US15/677,005 patent/US10494117B2/en active Active
-
2019
- 2019-11-21 US US16/690,735 patent/US10882634B2/en active Active
-
2021
- 2021-01-04 US US17/140,616 patent/US20210147093A1/en not_active Abandoned
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20100038473A1 (en) * | 2007-01-15 | 2010-02-18 | Heinz-Dieter Schneider | Aircraft Propeller Device, Method for Driving an Aircraft Propeller, Use of a Bearing for an Aircraft Propeller Drive and Use of an Electric Machine |
US20100064689A1 (en) * | 2007-04-11 | 2010-03-18 | Flight-Design-Gmbh Flugsportgeraete | Aircraft |
US20130227950A1 (en) * | 2012-03-05 | 2013-09-05 | Embry-Riddle Aeronautical University, Inc. | Hybrid assembly for an aircraft |
US20140010652A1 (en) * | 2012-07-09 | 2014-01-09 | Mcmaster University | Hybrid powertrain system |
US20160265631A1 (en) * | 2013-05-17 | 2016-09-15 | Perkins Engine Company Limited | A propulsion system |
US20170225573A1 (en) * | 2014-09-23 | 2017-08-10 | Sikorsky Aircraft Corporation | Hybrid electric power drive system for a rotorcraft |
US10882634B2 (en) * | 2016-08-15 | 2021-01-05 | Marinus Bernard Bosma | Parallel hybrid-electric aircraft engine |
Also Published As
Publication number | Publication date |
---|---|
US10494117B2 (en) | 2019-12-03 |
US10882634B2 (en) | 2021-01-05 |
US20200255160A1 (en) | 2020-08-13 |
US20190047720A1 (en) | 2019-02-14 |
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AS | Assignment |
Owner name: HYBRID AEROSPACE CORPORATION, OHIO Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:BOSMA, MARINUS BERNARD;REEL/FRAME:066810/0612 Effective date: 20240225 |