GB2560543A

GB2560543A - Pentad powered hybrid delivery system

Info

Publication number: GB2560543A
Application number: GB1704091.6A
Authority: GB
Inventors: Briggs Simon
Original assignee: Individual
Current assignee: Individual
Priority date: 2017-03-15
Filing date: 2017-03-15
Publication date: 2018-09-19
Also published as: GB201704091D0

Abstract

An on-board electric power supply and recharging system for electric rotorcraft. The system has two modular lithium based battery packs (MLBBP) a, a hydrogen fuel cell and hydrogen fuel tank b to support power delivery/supply to the battery packs when under heavy load, such as during take-off, landing, emergency manoeuvres, etc., multiple external air vents c, utilising the Venturi effect and Bernoulli principle to provide air flow to associated turbines d, the turbines then turning permanent magnet generators (PMG) that recharge the battery packs. When the battery pack powering the rotorcraft is drained below a set threshold, the supply is switched to the next battery pack, and the first battery pack enters a recharge cycle.

Description

(54) Title of the Invention: Pentad powered hybrid delivery system

Abstract Title: Electric rotorcraft with Venturi effect air vents providing air flow to turbines that turn generators to recharge the batteries while in flight (57) An on-board electric power supply and recharging system for electric rotorcraft. The system has two modular lithium based battery packs (MLBBP) a, a hydrogen fuel cell and hydrogen fuel tank b to support power delivery/supply to the battery packs when under heavy load, such as during take-off, landing, emergency manoeuvres, etc., multiple external air vents c, utilising the Venturi effect and Bernoulli principle to provide air flow to associated turbines d, the turbines then turning permanent magnet generators (PMG) that recharge the battery packs. When the battery pack powering the rotorcraft is drained below a set threshold, the supply is switched to the next battery pack, and the first battery pack enters a recharge cycle.

Figure 2.

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/2

Figure 1

Aircraft initiates ‘POWER SUPPLY CYCLE’

Via Modular Lithium Based Battery Packs (MLBBP) during Start-up procedure and begins operations.

Heavy load on the MLBBP.

Continue MLBBP supply.

Yes

Hydrogen Fuel System supports operations. EG: Take-off, Landing, evasive and/or emergency manoeuvres.

Depletion of MLBBP.

No

Yes

Power transfer to next MLBBP, which continues the ‘POWER SUPPLY CYCLE’.

Yes

Power transfer to next MLBBP, which continues the ‘POWER SUPPLY

CYCLE’.

Aircraft initiates ‘POWER REGENRATION CYCLE’

Automatic opening of air/wind/fluid flow vents, using a combination of Venturi Effect and Bernoulli Principle, air/wind/fluid flow then provides power that operates Hybrid Turbines (HT).

At the optimal RPM output, HT’s supply input power to multiple Permanent Magnet Generators (PMG’s).

PMG’s output, with efficiency variance of between 88-92% will recharge the drained MLBBP within 28 mins, allowing sufficient time for its next turn in the ‘POWER SUPPLY CYCLE’.

Once the MLBBP is recharged the air/wind/fluid vents will automatically close, forcing the shutdown of the HT’S and PMG’s, until required for the next MLBBP’s ‘POWER REGENERATION CYCLE’.

2/2

Figure 2.

DESCRIPTION

Pentad Powered Hybrid Delivery System

This invention is the process for a rotorcrafts Electric Power Supply and Delivery System, which includes an on-board Electric Power Regeneration Process enabling Electric Powered Flight, this system has been named the ‘Pentad Powered Hybrid Delivery System’. (PPHDS).

This invention relates to a unique and innovative process that will provide an electric flight capability to a rotorcraft, with power delivery mechanisms allowing for zero carbon/green-house-gas emission flight, this process also includes said rotorcrafts capability for an unlimited flight performance.

Since the birth of powered flight, fossil fuels have been the common denominator that provides the aviation industry with its platform to deliver powered flight. My system is a process utilising five (5) power mechanisms that will challenge the industries conventional thinking. With these five (5) mechanisms arranged in a specific configuration, not only will my innovative processes deliver a sustainable electric flight alternative to the internal combustion or turbine engine alternative, offering a zero carbon/green-house-gas emission option rather than the decades old, post WW2 technologies available in the market today. In addition, the processes also combine the capability of delivering an unlimited flight capability. The performance and expectations are deliverable via the use of the afore mentioned five (5) mechanisms, which are existing technologies already successful in industrial applications outside of the aviation industry for many years and openly available in the marketplace.

PPHDS delivers electric power to a rotorcraft to support all its systems, via five (5) on-board mechanisms that enable and allow the possibility of sustainable electric powered flight, whilst also providing an on-board power regeneration process to enable an unlimited flight capability. Initially the process of power regeneration is made possible by utilising the Venturi Effect in combination with the Bernoulli Principles to begin this regeneration process.

The power supply/delivery mechanisms are arranged in a specific configuration, figure 2 and may also be substituted for mechanisms of alternate weight and/or power outputs, as such providing weight saving and performance enhancements, however, the processes remain as stated within my claims and in keeping within the same process parameters and mechanism configuration.

The invention will now be described solely by way of example and with reference to the accompanying drawings, in which:

Figure 1 (Page 6) shows a flowchart describing the invention processes, outlining the order in which the five (5) mechanisms provide an electric power supply/delivery to a rotorcraft, as such this process provides said rotorcraft with a zero carbon/greenhouse-gas emission electric flight capability. In combination with the afore-mentioned electric power supply and delivery innovation, the invention also provides an onboard power regeneration process to support an unlimited flight capability.

Figure 2 (Page 7) shows an embodiment of my process with the afore-mentioned five (5) mechanisms, configured to provide the process that is the foundation my claims. Outlined in figure 2:

(a) identifies electric power supply/delivery using multiple Modular Lithium Based Battery Packs (MLBBP’s) as the main power supply/delivery source.

(b) identifies the Hydrogen Fuel Cell and Hydrogen Fuel Tank (HFC/HFT) that will support the electric power delivery/supply of the MLBBP’s during periods of high load, such as: Take-off; landing; emergency and/or evasive manoeuvres.

(c) identifies the multiple air/wind/fluid flow/force vents which utilise the Venturi Effect, in combination with the Bernoulli Principle to supply the input power source for the multiple Hybrid Turbine’s (HT) and the next mechanism in the process.

(d) identifies the multiple HT’s that through their operation will develop the operational RPM through their connection to the Permanent Magnet Generators which provide the output and subsequently the input power necessary to operate the next mechanism in the process.

(e) identifies the Permanent Magnet Generators (PMG’s) that will operate within a variance of eighty-eight (88) percent to ninety-two (92) percent efficiency, providing the necessary output power supply/delivery source, to deliver an electrical input power that will recharge the drained MLBBP. Once the PMG’s have performed they’re tasking, the vents allowing air/wind/fluid flow/force that began the power regeneration process will automatically close, until the next MLBBP in the aircrafts electrical supply/delivery process necessitates the vents re-opening and the power regeneration process re-starting. This process will continue until the rotorcraft has reached its destination.

Claims

1. A power delivery and power re-generation process comprising of five power supply/delivery mechanisms that when combined in a unique configuration will create an innovative process delivering the benefits of zero carbon/green-house-gas emission electric powered flight, combined with the benefit of an unlimited flight capability. When these five power delivery mechanisms are combined in the manner outlined within my abstract and diagrams/schematic, it is then that they will deliver the processes that provides a rotorcraft with the benefits of this invention.

2. The power delivery and power re-generation process as mentioned in Claim 1. above is further outlined with the following description:

The concept describes new processes for electric power supply/delivery and electric power re-generation enabling electric powered flight, using technology which I have named the Pentad Powered Hybrid Delivery System (PPHDS). This process utilises five power supply/delivery mechanisms that allows for zero carbon/greenhouse-gas : emission electric powered flight, in combination with a performance capability offering an unlimited flight capability. In achieving this level of innovation, the concept uses five (5) mechanisms as outlined below, enabling the successful implementation our electric power supply/delivery and electric regeneration processes, as follows:

(1) Multiple Modular Lithium Based Battery Packs. (MLBBP’s) (2) Hydrogen Fuel Cell and Hydrogen Tank Systems. (HFC & HTS) (3) Multiple external vents channelling external Air/Wind/Fluid Flow/Force, whilst utilising the combination of the Venturi Effect and the Bernoulli Principle to manipulate said power source.

(4) Multiple Hybrid Turbines. (HT’s) (5) Multiple Permanent Magnet Generators. (PMG’s)

With all these mechanisms being commercially widely available and already proven effective outside of the aviation industry, used within both the automotive and renewable energy industries, it is my claim that when combined and utilised in a innovative configuration, that the PPHDS will prove to be a revolutionary step forward for sustainable electric powered flight, combined with an unlimited electric flight capability.

3. The mechanism (1) Modular Lithium Based Battery Pack (MLBBP) outlined in Claim 2. wherein is a battery capable of delivering electrical energy to power a rotorcraft during flight operations. This first mechanism will deliver its energy output until drained to a specific but safe level of electrical energy remaining within its cells, however, prior to going off-line the next MLBBP will continue with its electrical output as the previous MLBBP did, then the drained MLBBP begins its recharge cycle (see Claim 5). The discharge and recharge cycle of all on-board MLBBP’s will continue until the rotorcraft has reached its destination.

4. The mechanism (2) Hydrogen Fuel Cell and Hydrogen Fuel Tank Systems (HFC & HFTS) outlined in Claim 2. wherein is a power delivery system to be used to support the MLBBP’s when under heavy load, with such circumstances being take-off, landing and at such times that requires emergency manoeuvres to be performed.

The HFC & HFTS is constantly monitoring power usage levels and in such circumstance as outline previously, will provide the appropriate electrical output to reduce excessive loading on the MLBBP’s, therefore lengthening the energy output capability of any given MLBBP supplying power to the rotorcrafts systems.

5. The mechanism (3) Air/Wind/Fluid Flow/Force Vents as outlined in Claim 2. Is the first stage in the system’s electrical power regeneration process. During an aircraft’s operations, MLBBP’s will require power regeneration, a process that will be initiated once a depleted MLBBP is off-line and disengaged from its electric power supply/delivery tasking. As the first MLBBP reaches a predetermined specific, (but safe) power level, the system converts to the next assigned MLBBP automatically (as outlined in point 3), at which point, the power re-generation process begins via the automatic opening of multiple external Air/Wind/Fluid Flow/Force Vents, allowing for Air/Wind/Fluid Flow/Force to be diverted and manipulated using the Venturi Effect and Bernoulli Principles to start the process that will regenerate any of the drained MLBBP’s. This resulting energy output is utilised to power the next mechanism in the processes.

6. The mechanism (4) Hybrid Turbine (HT) outlined in Claim 2. wherein is a bladeless centripetal flow turbine, powered by Air/Wind/Fluid Flow/Force during flight operations. As the Air/Wind/Fluid Flow/Force passes through the hybrid turbines, the output power that results from this will rotate a shaft at a given revolution per minute, providing the necessary input power supply/delivery to the final mechanism in the power regeneration process.

7. The mechanism (5) Permanent Magnet Generator’s (PMG’s) outlined in Claim 2. wherein is a magnetic generator/alternator which is tethered to a HT (as outlined in point 6) with the HT acting as its input power supply, enough to turn the tethered shaft that powers the PMG’s rota allowing for a low RPM range, RPM that will ensure that the PMG’s output electrical charge subsequently and sufficiently, recharges the appropriate MLBBP. Once the MLBBP is fully re-charged the external vents will close.

8. The PPHDS operation cycle will start automatically for each of the MLBBP’s as and when needed, allowing for an unlimited flight capability or until the rotorcraft’s flight destination is reached.