AU2020281116B2 - Motor and Fuel-Powered Hybrid System for a Rocket Thruster - Google Patents
Motor and Fuel-Powered Hybrid System for a Rocket Thruster Download PDFInfo
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- AU2020281116B2 AU2020281116B2 AU2020281116A AU2020281116A AU2020281116B2 AU 2020281116 B2 AU2020281116 B2 AU 2020281116B2 AU 2020281116 A AU2020281116 A AU 2020281116A AU 2020281116 A AU2020281116 A AU 2020281116A AU 2020281116 B2 AU2020281116 B2 AU 2020281116B2
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- compressor
- rocket
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Abstract
OF THE DISCLOSURE
A motor and fuel-powered hybrid system of a rocket thruster is disclosed,
which mainly provides power through an electric motor and a fluid fuel injector. In
particular, at the beginning stage of the rocket lift-off, the motor drives the
compressor to provide power to send the rocket into air. When the speed and height
of the rocket gradually increase, the fuel is ignited to give power to keep propelling
the rocket, thereby reducing the fluid fuel that needs to be carried on the rocket,
increasing the rocket's loading space and enhancing the carrying capacity.
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Description
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Editorial Note
2020281116
Description pages start pages 1A -1,
should be pages 1-lA.
P/00/011 Regulation 3.2 AUSTRALIA
Patents Act 1990
Invention Title: Motor and Fuel-Powered Hybrid System for a Rocket Thruster
Name of Applicant: Taiwan Innovative Space, Inc.
Address for Service: A.P.T. Patent and Trade Mark Attorneys PO Box 833, Blackwood, SA 5051
The following statement is a full description of this invention, including the best method of performing it known to me/us:
la
Field of the Invention
The present invention relates to a rocket, and more particularly
to a motor and fuel-powered hybrid system for a rocket thruster.
Related Prior Art
At present, the most common rocket thrusters are mainly solid
rocket thrusters, liquid rocket thrusters or hybrid rocket thrusters, and
because hybrid rocket thrusters have the characteristics of being able to
control thrust, relatively low cost, and have higher safety, the number of
hybrid rocket thrusters is the largest compared to others.
It is worth mentioning that although hybrid rockets are easier to
control their thrust than pure liquid or solid rockets, they still have many
inconveniences in use. For example: the use of the mixing of fluid fuel
and solid fuel as propulsion fuel from the beginning of lift-off results in
the need to reserve a lot of fluid fuel for rocket lift-off on the rocket.
Relatively, it is necessary to calculate the possible offset of the rocket
after the fluid fuel is reduced, and then adjust the thrust of the rocket
thruster according to the calculation results.
The most important thing to note is that since the fluid fuel
required for the rocket to lift off from the ground to space must be
prepared on the rocket body, in order to prepare enough fluid fuel for lift-off, a lot of space on the rocket body is used to store fluid fuel, resulting in a small amount of equipment that can be installed in the rocket, and thus the weight ratio of the objects that the rocket can carry is extremely low.
In view of this, it is indeed necessary to provide a technical
means to solve the problem of extremely low weight ratio of objects that
the rocket can carry.
One objective of the present invention is to solve the problem of
extremely low weight ratio of objects that the rocket can carry.
To achieve the above objective, a motor and fuel-powered
hybrid system for a rocket thruster provided by the invention comprises:
a casing including a first tank, a second tank, and a third tank
that are connected in sequence, the first tank including an air inlet and a
first space communicating with each other, the second tank including a
second space communicating with the first space, and the third tank
including a third space communicating with the second space;
an electric motor disposed in the first tank, and including a
central processing system, and a compressor that is power connected to
the central processing system;
a fluid fuel injector disposed on the casing, controllingly
connected to the central processing system, and including an injection
head extending into the second tank, and the injection head being arranged toward the third tank to spray fluid fuel; and an igniter disposed in the third tank and controllingly connected to the central processing system, and being used for igniting fluid fuel; by such arrangements, there are a first stage, a second stage and a third stage, in the first stage, the central processing system drives the compressor to operate, and the compressor provides kinetic energy, the rocket enters the second stage when raised to a certain height, in the second stage, the central processing system controls the compressor to gradually reduce load, in the third stage, the central processing system drives the fluid fuel injector to inject fluid fuel toward the third tank provide kinetic energy, and in the first, second and third stages, the amounts of fluid fuel that the fluid fuel injector controls the central processing system to inject are the same.
In another solution, a motor and fuel-powered hybrid system for
a rocket thruster provided by the invention comprises:
a casing including a first tank, a second tank, and a third tank
that are connected in sequence, the first tank including an air inlet and a
first space communicating with each other, the second tank including a
second space communicating with the first space, and the third tank
including a third space communicating with the second space;
an electric motor disposed in the first tank, and including a
central processing system, and a compressor that is power connected to
the central processing system; a fluid fuel injector disposed on the casing, controllingly connected to the central processing system, and including an injection head extending into the second tank, and the injection head being arranged toward the third tank to spray fluid fuel; and an igniter disposed in the third tank and controllingly connected to the central processing system, and being used for igniting fluid fuel.
In a proffered embodiment, a nozzle is connected to the third
tank, and the nozzle includes a passage penetrating and communicating
with the third space.
In a proffered embodiment, the central processing system
includes a processing unit, a power supply, and an electric motor, the
processing unit is controllingly connected to the power supply, the
power supply is electrically connected to the electric motor, and the
electric motor is power connected to the compressor.
In a proffered embodiment, the power supply takes the form of
lithium ion batteries or hydrogen fuel cells.
In a proffered embodiment, the compressor is selected from a
group consisting of an axial compressor, a centrifugal air compressor, and
a combination of the axial compressor and the centrifugal air
compressor.
In a proffered embodiment, an interior of the fluid fuel injector
is used for storage of hydrocarbon fuel.
In a proffered embodiment, the igniter is an autotransformer.
In a proffered embodiment, a mixing enhancer is disposed in the
second tank, and located between the nozzle and the third space of the
third tank .
Since the first stage of rocket lift-off is mainly achieved by the
compressor, and the compressor is driven by the power supply in the
central processing system, the weight of the power supply is much
smaller than that of the fluid fuel, and in the second stage the load of the
compressor is gradually reduced, the central processing system controls
the compressor to gradually reduce the load, so that the rocket can also
increase the speed to super high speed. In the third stage, the central
processing system 21 drives the fluid fuel injector 30 to inject fluid fuel
toward the third tank 13, and the fluid fuel injector 30 provides kinetic
energy. It is worth mentioning that in the first, second and third stages,
the amounts of fluid fuel that the central processing system 21 controls
the fluid fuel injector 30 to inject are the same,_so that the rocket can be
loaded with more equipment, and the rocket's load ratio is greatly
increased.
These together with other objects of the invention, along with
the various features of novelty which characterize the invention, are
pointed out with particularity in the claims annexed to and forming a
part of this disclosure. For a better understanding of the invention, its
operating advantages and the specific objects attained by its uses, reference should be had to the accompanying drawings and descriptive matter in which there are illustrated preferred embodiments of the invention.
Fig. 1 is a schematic diagram of the structure of the present
invention in a preferred embodiment;
Fig. 2 is a graph of the injection conditions of the electric motor
and the fluid fuel injector of the present invention in comparison with
conventional hybrid rockets.
The present invention will be clearer from the following
description when viewed together with the accompanying drawings,
which show, for purpose of illustrations only, the preferred embodiment
in accordance with the present invention.
Referring to Fig. 1, the present invention is a motor and
fuel-powered hybrid system for rocket thruster, which essentially
comprises: a casing 10, the electric motor 20, a fluid fuel injector 30 and
an igniter 40.
The casing 10 includes a first tank 11, a second tank 12, and a
third tank 13 that are connected in sequence. The first tank 11 includes
an air inlet 111 and a first space 112 communicating with each other, the
second tank 12 includes a second space 121 communicating with the
first space 112, and the third tank 13 includes a third space 131 communicating with the second space 121. In this embodiment, the invention further includes a nozzle 14 connected to the third tank 13, and the nozzle 14 includes a passage 141 penetrating and communicating with the third space 131.
The electric motor 20 is disposed in the first tank 11, and
includes a central processing system 21, and a compressor 22 that is
power connected to the central processing system 21. In this
embodiment, the central processing system 21 includes a processing unit
211 (Central Processing Unit/CPU), a power supply 212, and an electric
motor 213. The processing unit 211 is controllingly connected to the
power supply 212 to control the amount of power supplied from the
power supply 212 to the electric motor 213. The power supply 212 is
electrically connected to the electric motor 213, and can take the form of
lithium ion batteries or hydrogen fuel cells to provide the electric motor
213 energy. The electric motor 213 is power connected to the
compressor 22 to drive the compressor 22 to operate, and the
compressor 22 can be an axial compressor 22, a centrifugal air
compressor 22 or a combination of the two.
The fluid fuel injector 30 is disposed on the casing 10,
controllingly connected to the central processing system 21, and includes
an injection head 31 extending into the second tank 12, and the injection
head 31 is arranged toward the third tank 13 to spray fluid fuel. The third
tank 13_contains compressed air obtained from the environment to provide thrust together with fluid fuel. In this embodiment, the interior of the fluid fuel injector 30 is used for storage of hydrocarbon fuel.
Hydrocarbon fuel is a bio-fluid fuel that can replace petrochemical diesel
and is a substitute for petroleum energy. Hydrocarbon fuel is a fluid fuel
that can be produced through a lipid exchange reaction using various
lipid compounds (rapeseed oil, cottonseed oil...etc. various vegetable oils)
and methanol as raw materials, under the action of a catalyst.
The igniter 40 is disposed in the third tank 13 and controllingly
connected to the central processing system 21, and is used for igniting
fluid fuel. In this embodiment, the igniter 40 is an autotransformer, and
the central processing system 21 controls the increase or decrease of its
voltage, so that the igniter 40 can generate a spark at a specific time
point and ignite the fluid fuel in the third tank 13.
Thereby, there are a first stage, a second stage and a third stage.
In the first stage, the central processing system 21 drives the compressor
22 to operate, and the compressor 22 provides kinetic energy. After the
rocket is raised to a certain height, it enters the second stage. In the
second stage, the central processing system 21 controls the compressor
22 to gradually reduce the load, and in the third stage, the central
processing system 21 drives the fluid fuel injector 30 to inject fluid fuel
toward the third tank 13, and the fluid fuel injector 30 provides kinetic
energy. It is worth mentioning that in the first, second and third stages,
the amounts of fluid fuel that the fluid fuel injector 30 eont the central processing system 21 controls the fluid fuel injector 30 to inject are the same.
Among them, there is a mixing enhancer 50 disposed in the
second tank 12, and the mixing enhancer 50 is located between the
nozzle 14 and the third space 131 of the third tank 13. When the nozzle
14 injects fluid fuel toward the third tank 13, the fluid fuel will first pass
through the mixing enhancer 50 and then enter the third space 131 of
the third tank 13.
The above is the structural configuration and connection
relationship of the present invention in a preferred embodiment. The use
of the present invention and the effects it can produce are as follows:
Referring to Figs. 1 and 2, the electric motor and the fuel power
mixing system of a rocket thruster of the present invention mainly has
three stages in use. In the first stage, the central processing system 21
first controls the compressor 22 to start, and then controls the fluid fuel
injector 30 to inject a small amount of hydrocarbon fuel, so that air
enters the first space 112 from the air inlet 111 and passes through the
compressor 22. When the air passes through the compressor 22, it
becomes high pressure and sequentially passes through the second
space 121, the third space 131 and the passage 141, thereby allowing
the rocket to be propelled into the air mainly by the compressor 22.
After the rocket lifted off through the compressor 22, the
central processing system 21 controls the compressor 22 to reduce the load, and controls the fluid fuel injector 30 to continuously inject a small amount of hydrocarbon fuel. In the second stage, the power generated by igniting the hydrocarbon fuel is combined with the power generated by the compressor 22 to keep propelling the rocket. Therefore, in the second stage, the combination of the power generated by the ignition of the hydrocarbon fuel and the power generated by the compressor 22 is sed continues to propel the rocket.
In the third stage, as the power of the power supply 212 is
gradually exhausted, the central processing system 21 controls the
compressor 22 to reduce the load, the fluid fuel injector 30 injects
hydrocarbon fuel toward the third tank 13, and the powergenerated by
ignition and combustion of the hydrocarbon fuel is used to propel the
rocket.
Since the first stage of rocket lift-off is mainly achieved by the
compressor 22, and the compressor 22 is driven by the power supply 212
in the central processing system 21, the weight of the compressor 22 is
much smaller than that of the fluid fuel, and in the second stage the load
of the compressor 22 is gradually reduced, so that the rocket can also
increase the speed to super high speed. In the third stage, the central
processing system 21 controls the reduction of the load of the
compressor 22, and mainly uses fluid fuel to provide kinetic energy,
therefore, the volume of fluid fuel that needs to be stored on the rocket
is greatly reduced, so that the rocket can be loaded with more equipment, and the rocket's load ratio is greatly increased.
While we have shown and described various embodiments in
accordance with the present invention, it is clear to those skilled in the
art that further embodiments may be made without departing from the
scope of the present invention.
Claims (8)
1. A motor and fuel-powered hybrid system for a rocket thruster,
comprising:
a casing (10) including a first tank (11), a second tank (12), and a
third tank (13) that are connected in sequence, the first tank (11)
including an air inlet (111) and a first space (112) communicating with
each other, the second tank (12) including a second space (121)
communicating with the first space (112), and the third tank (13)
including a third space (131) communicating with the second space (121),
the third tank (13) containing compressed air obtained from the
environment to provide thrust together with fluid fuel;
the motor and fuel-powered hybrid system for a rocket thruster is
characterized in that:
an electric motor (20) disposed in the first tank (11), and
including a central processing system (21), and a compressor (22) that is
power connected to the central processing system (21);
a fluid fuel injector (30) disposed on the casing (10),
controllingly connected to the central processing system (21), and
including an injection head (31) extending into the second tank (12), and
the injection head (31) being arranged toward the third tank (13) to spray
fluid fuel; and
an igniter (40) disposed in the third tank (13) and controllingly
connected to the central processing system (21), and being used for igniting fluid fuel; there are a first stage, a second stage and a third stage, in the first stage, the central processing system (21) drives the compressor (22) and the fluid fuel injector (30) to operate, and the compressor (22) provides kinetic energy, the rocket enters the second stage when raised to a certain height, in the second stage, the central processing system (21) controls the compressor (22) to gradually reduce load and the amount of fluid fuel that the fluid fuel injector (30) injects does not change, in the third stage, the central processing system (21) controls the compressor (22) to gradually reduce load and the amount of fluid fuel that the fluid fuel injector (30) injects does not change, the central processing system (21) drives the fluid fuel injector (30) to inject fluid fuel toward the third tank
(13) to provide kinetic energy, and in the first, second and third stages,
the amounts of fluid fuel that the central processing system (21) controls
the fluid fuel injector (30) to inject are the same.
2. motor and fuel-powered hybrid system for the rocket thruster
as claimed in claim 1 is characterized in that: further comprising a nozzle
(14) connected to the third tank (13), and the nozzle (14) includes a
passage (141) penetrating and communicating with the third space (131).
3. The motor and fuel-powered hybrid system for the rocket
thruster as claimed in claim 1 is characterized in that: wherein the central
processing system (21) includes a processing unit (211), a power supply
(212), and an electric motor (213), the processing unit (211) is controllingly connected to the power supply (212), the power supply (212) is electrically connected to the electric motor (213) of the central processing system (21), and the electric motor (213) of the central processing system (21) is power connected to the compressor (22).
4. The motor and fuel-powered hybrid system for the rocket
thruster as claimed in claim 3 is characterized in that: wherein the power
supply (212) takes the form of lithium ion batteries or hydrogen fuel
cells.
5. The motor and fuel-powered hybrid system for the rocket
thruster as claimed in claim 3 is characterized in that: wherein the
compressor (22) is selected from a group consisting of an axial
compressor (22), a centrifugal air compressor (22), and a combination of
the axial compressor (22) and the centrifugal air compressor (22).
6. The motor and fuel-powered hybrid system for the rocket
thruster as claimed in claim 1 is characterized in that: wherein an interior
of the fluid fuel injector (30) is used for storage of hydrocarbon fuel.
7. The motor and fuel-powered hybrid system for the rocket
thruster as claimed in claim 1 is characterized in that: wherein the igniter
(40) is an autotransformer.
8. The motor and fuel-powered hybrid system for the rocket
thruster as claimed in claim 2 is characterized in that: further comprising
a mixing enhancer (50) disposed in the second tank (12), and located
between the nozzle (14) and the third space (131) of the third tank (13)
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| TW109129694 | 2020-08-31 | ||
| TW109129694A TWI776218B (en) | 2020-08-31 | 2020-08-31 | Motor and fuel-powered hybrid system for rocket thruster |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| AU2020281116A1 AU2020281116A1 (en) | 2022-03-17 |
| AU2020281116B2 true AU2020281116B2 (en) | 2023-03-02 |
Family
ID=80629158
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| AU2020281116A Active AU2020281116B2 (en) | 2020-08-31 | 2020-12-03 | Motor and Fuel-Powered Hybrid System for a Rocket Thruster |
Country Status (3)
| Country | Link |
|---|---|
| AU (1) | AU2020281116B2 (en) |
| NZ (1) | NZ770698A (en) |
| TW (1) | TWI776218B (en) |
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| DE4018249A1 (en) * | 1990-06-07 | 1991-12-12 | Dietmar Neuhaus | Gas turbine plant for solar dynamic energy conversion - has hermetically sealed rotating housing filled with working gas acting as rotor of electrical generator |
| US20080175703A1 (en) * | 2007-01-09 | 2008-07-24 | Sonic Blue Aerospace | Electric turbine bypass fan and compressor for hybrid propulsion |
| EP1669587B1 (en) * | 2004-11-22 | 2011-09-14 | General Electric Company | Propulsion system |
| CN103807052A (en) * | 2014-03-10 | 2014-05-21 | 邱世军 | Electric drive jet engine |
| CN107696812A (en) * | 2017-10-10 | 2018-02-16 | 中国人民解放军国防科技大学 | Oil-electricity hybrid power system and vertical take-off and landing hovercar with same |
| US10012177B2 (en) * | 2013-10-11 | 2018-07-03 | Reaction Engines Ltd | Engine comprising a rocket combustion chamber and a heat exchanger |
| US20190271263A1 (en) * | 2018-03-01 | 2019-09-05 | Subaru Corporation | Supercharging system for aircraft reciprocating engine, aircraft reciprocating engine, and aircraft |
| CN111237084A (en) * | 2020-02-17 | 2020-06-05 | 王镇辉 | Electric-driven jet aircraft engine and aircraft |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| TW201020009A (en) * | 2008-11-26 | 2010-06-01 | hui-yi Wu | Miniature jet engine |
| FR2967725B1 (en) * | 2010-11-23 | 2012-12-14 | Snecma | COMBINED TURBOREACTOR AND STATOREACTOR COMBINATION PROPELLER |
| TW201413102A (en) * | 2012-07-24 | 2014-04-01 | Lee Brent | Internal detonation engine, hybrid engines including the same, and methods of making and using the same |
| DE102015011959A1 (en) * | 2015-09-18 | 2017-03-23 | INGENIEURBüRO CAT M. ZIPPERER GMBH | Starter arrangement |
| CN108995817B (en) * | 2018-07-16 | 2020-05-15 | 中国科学院合肥物质科学研究院 | Multi-ring heat exchanger and propulsion system and method based on multi-ring heat exchanger |
-
2020
- 2020-08-31 TW TW109129694A patent/TWI776218B/en active
- 2020-12-03 NZ NZ770698A patent/NZ770698A/en unknown
- 2020-12-03 AU AU2020281116A patent/AU2020281116B2/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4018249A1 (en) * | 1990-06-07 | 1991-12-12 | Dietmar Neuhaus | Gas turbine plant for solar dynamic energy conversion - has hermetically sealed rotating housing filled with working gas acting as rotor of electrical generator |
| EP1669587B1 (en) * | 2004-11-22 | 2011-09-14 | General Electric Company | Propulsion system |
| US20080175703A1 (en) * | 2007-01-09 | 2008-07-24 | Sonic Blue Aerospace | Electric turbine bypass fan and compressor for hybrid propulsion |
| US10012177B2 (en) * | 2013-10-11 | 2018-07-03 | Reaction Engines Ltd | Engine comprising a rocket combustion chamber and a heat exchanger |
| CN103807052A (en) * | 2014-03-10 | 2014-05-21 | 邱世军 | Electric drive jet engine |
| CN107696812A (en) * | 2017-10-10 | 2018-02-16 | 中国人民解放军国防科技大学 | Oil-electricity hybrid power system and vertical take-off and landing hovercar with same |
| US20190271263A1 (en) * | 2018-03-01 | 2019-09-05 | Subaru Corporation | Supercharging system for aircraft reciprocating engine, aircraft reciprocating engine, and aircraft |
| CN111237084A (en) * | 2020-02-17 | 2020-06-05 | 王镇辉 | Electric-driven jet aircraft engine and aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| TWI776218B (en) | 2022-09-01 |
| TW202210371A (en) | 2022-03-16 |
| NZ770698A (en) | 2022-12-23 |
| AU2020281116A1 (en) | 2022-03-17 |
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