CN113859551A - Propulsion system for enhancing airplane power - Google Patents
Propulsion system for enhancing airplane power Download PDFInfo
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- CN113859551A CN113859551A CN202111205305.2A CN202111205305A CN113859551A CN 113859551 A CN113859551 A CN 113859551A CN 202111205305 A CN202111205305 A CN 202111205305A CN 113859551 A CN113859551 A CN 113859551A
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- 230000002708 enhancing effect Effects 0.000 title claims abstract description 11
- 238000001816 cooling Methods 0.000 claims abstract description 18
- 238000000034 method Methods 0.000 claims abstract description 6
- 239000000463 material Substances 0.000 claims abstract description 5
- 208000016261 weight loss Diseases 0.000 claims abstract description 4
- 239000013585 weight reducing agent Substances 0.000 claims abstract description 4
- 238000001514 detection method Methods 0.000 claims description 27
- 238000004088 simulation Methods 0.000 claims description 19
- 238000012360 testing method Methods 0.000 claims description 7
- 230000000007 visual effect Effects 0.000 claims description 6
- 230000002452 interceptive effect Effects 0.000 claims description 5
- 238000005259 measurement Methods 0.000 claims description 3
- 239000002245 particle Substances 0.000 claims description 2
- 230000003190 augmentative effect Effects 0.000 claims 2
- 230000002650 habitual effect Effects 0.000 claims 1
- 238000005457 optimization Methods 0.000 claims 1
- 238000010586 diagram Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 238000005461 lubrication Methods 0.000 description 1
- 230000001629 suppression Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D31/00—Power plant control systems; Arrangement of power plant control systems in aircraft
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Abstract
The invention discloses a propulsion system for enhancing the power of an airplane, which comprises a direct lifting pushing module, an indirect lifting pushing module and an airborne control module; the direct lifting pushing module and the indirect lifting pushing module are electrically connected through the airborne control module; directly lifting the power module, performing supercharging and cooling treatment on the engine on the premise of safety and stability, and performing weight reduction treatment on the material; the power module is indirectly lifted, reasonable distribution is carried out on the basis of normal airplane power, energy is reasonably utilized, and power is optimized on the premise of safety; and the airborne control module is used for detecting, controlling and recording the systems and managing and planning the systems. According to the invention, the energy distribution among the systems in the flight process of the airplane is adjusted, and under the condition of not changing the airplane, the power distribution is carried out according to a specific value in a specific environment through reasonable distribution and a reasonable driving mode, so that the overall power is improved.
Description
Technical Field
The invention relates to the technical field of airplane power, in particular to a propulsion system for enhancing airplane power.
Background
The improvement of airplane power is usually accompanied with the updating and upgrading of airplanes, and is a change in the field of engines while the airplane improves power, and the airplane power is a system necessary for the normal work of the engines in the process of ensuring safe flight of the airplanes. The composition of which depends on the type of aircraft engine used, there are mainly the following systems or devices: aircraft engines and their starting and operating systems; an aircraft fuel system; aircraft lubrication systems fire protection and suppression systems; an aircraft engine heat sink; an aircraft engine fixture; the air inlet and exhaust device is characterized in that the air inlet and exhaust device is of a structure in advance, common airplane power lifting is mainly embodied in updating of an airplane engine technology and reduction and assembly on an airplane body, however, the engine and the airplane body are replaced, huge manpower and material resources are consumed, and errors of serious energy consumption and irregular driving technology in the flying process still exist while updating and updating, so that the problem that the airplane power lifting cannot be fundamentally solved is solved, and therefore a propulsion system for enhancing the airplane power is provided.
Disclosure of Invention
The invention aims to solve the defects in the prior art and provides a propulsion system for enhancing the power of an airplane.
In order to achieve the purpose, the invention adopts the following technical scheme:
a propulsion system for enhancing power of an aircraft, comprising: the system comprises a direct lifting pushing module, an indirect lifting pushing module and an airborne control module; the direct lifting pushing module and the indirect lifting pushing module are electrically connected through the airborne control module;
directly lifting the power module, performing supercharging and cooling treatment on the engine on the premise of safety and stability, and performing weight reduction treatment on the material;
the power module is indirectly lifted, reasonable distribution is carried out on the basis of normal airplane power, energy is reasonably utilized, and power is optimized on the premise of safety;
and the airborne control module is used for detecting, controlling and recording the systems and managing and planning the systems.
Preferably, the direct lift push module includes: the power filling module and the power detection module.
Preferably, the indirect lifting pushing module includes: the driving detection module, the energy distribution module, the data recording module, the data simulation module and the power detection module.
Preferably, the driving detection module is used for detecting the driving information of the aircraft driver and detecting and recording the operation modes under different conditions;
the energy distribution module is used for performing algorithmic energy distribution on performance indexes among the systems and the result of the power actual measurement analysis through a set algorithm;
the data recording module is used for carrying out interactive recording on all subsystems of the airplane to obtain performance indexes between all the systems and power under different environments and different operations;
the data simulation module is used for carrying out digital simulation on each system and analyzing and simulating the performance indexes among the systems;
and the power detection module is used for carrying out experimental detection on each index of the data simulation and testing the influence relationship between independent operation among the systems and other systems.
Preferably, the power shim module includes: air inlet pressurization module, air inlet cooling module, air inlet pressurization module improves air inlet air flow velocity, and air inlet cooling module carries out cooling on a large scale to the high-speed air that flows of air inlet to rationally cool down the engine.
Preferably, the data simulation module performs optimal simulation test on a single system under different environments.
Preferably, the energy distribution module is used for performing energy distribution on each system and recording the habit adjustment of a driver according to the numerical value obtained by the particle swarm algorithm.
Preferably, the power detection module performs overall testing and power detection based on the data simulation module, and obtains a specific set value on the premise of safely improving power.
An indirect power-up method for a propulsion system for boosting aircraft power, comprising the steps of:
step 1, carrying out interactive recording on all subsystems of an airplane, and recording the relation between the power and the operation of the airplane;
step 2, acquiring performance indexes between each system and power under different environments and different operations;
step 3, establishing a visual digital model for the obtained information and the power performance index;
step 4, analyzing each system and performance through a visual digital model, and analyzing the operation habits and the dynamic performance of a driver;
step 5, obtaining a power optimal flight mode, and analyzing the operation habits of a driver to obtain a power optimal operation mode;
and 6, reasonably distributing and optimally distributing the systems based on the visual digital models among the systems, and reasonably arranging the operation modes.
Compared with the prior art, the invention has the beneficial effects that:
1. according to the invention, the energy distribution among the systems in the flight process of the airplane is adjusted through the indirect lifting pushing module, and under the condition that the airplane is not changed, the power distribution is carried out according to a specific value in a specific environment through reasonable distribution and a reasonable driving mode, so that the overall power is improved;
2. according to the invention, the direct lifting pushing module is used for pressurizing and cooling the air inlet of the airplane, so that the power of the airplane can be directly lifted in a safe mode, and the balance weight of the airplane is lightened in the engine and the fuselage of the airplane, so that the power of the airplane is directly lifted.
Drawings
FIG. 1 is a system block diagram of an enhanced aircraft power propulsion system in accordance with the present invention;
FIG. 2 is a block diagram of a direct lift push module system according to the present invention;
FIG. 3 is a block diagram of an indirect lifting pushing module system according to the present invention;
FIG. 4 is a schematic diagram of an aircraft air intake cooling module according to the present invention;
fig. 5 is a schematic view of an aircraft air intake pressurization module according to the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments.
Referring to FIG. 1, a propulsion system for enhancing power of an aircraft, comprising: the system comprises a direct lifting pushing module, an indirect lifting pushing module and an airborne control module; the direct lifting pushing module and the indirect lifting pushing module are electrically connected through the airborne control module;
directly lifting the power module, performing supercharging and cooling treatment on the engine on the premise of safety and stability, and performing weight reduction treatment on the material;
the power module is indirectly lifted, reasonable distribution is carried out on the basis of normal airplane power, energy is reasonably utilized, and power is optimized on the premise of safety;
and the airborne control module is used for detecting, controlling and recording the systems and managing and planning the systems.
The direct lift push module includes: the power filling module and the power detection module.
The indirect lifting pushing module comprises: the driving detection module, the energy distribution module, the data recording module, the data simulation module and the power detection module.
Example one
Referring to fig. 2, a propulsion system for enhancing power of an aircraft, comprising: directly lifting the pushing module; wherein the direct lift push module comprises: module, power detection module are filled to power, and the module is filled to power includes: the air inlet pressurizing module is used for increasing the air flow speed of an air inlet, and the air inlet cooling module is used for cooling high-speed flowing air of the air inlet in a large range and cooling an engine;
and the power detection module is used for detecting based on the power filling module, and compared with the normalized airplane flight mode, the power detection module is used for detecting all aspects of power.
Wherein only contain direct promotion module, increase air inlet pressurization module, air inlet cooling module on current basis, air inlet pressurization module improves air inlet air flow velocity, and air inlet cooling module cools down on a large scale the high-speed air that flows of air inlet to cooling down the engine, solitary promotion scope is limited, can't change the lack of current power, and the phenomenon that consumes the energy still exists.
Example two
Referring to fig. 3, a propulsion system for enhancing power of an aircraft, comprising: indirectly lifting the pushing module; the indirect lifting pushing module comprises: the driving detection module, the energy distribution module, the data recording module, the data simulation module and the power detection module;
the driving detection module is used for detecting the driving information of the aircraft driver and detecting and recording the operation modes under different conditions;
the energy distribution module is used for performing algorithmic energy distribution on performance indexes among the systems and the result of the power actual measurement analysis through a set algorithm;
the data recording module is used for carrying out interactive recording on all subsystems of the airplane to obtain performance indexes between all the systems and power under different environments and different operations;
the data simulation module is used for carrying out digital simulation on each system and analyzing and simulating the performance indexes among the systems;
and the power detection module is used for carrying out experimental detection on each index of the data simulation and testing the influence relationship between independent operation among the systems and other systems.
Wherein indirect promotion promotes the module, only goes to detect in the flight mode of normality and simulate out one set of reasonable flight mode and mode of driving, and it is serious to have solved the energy among the prior art and consume, drives the canonicalization, can adjust according to the difference of environment to a certain extent, improves certain power of aircraft, but promotes limitedly, promotes the power effect unobvious.
In summary, the first embodiment and the second embodiment show that both the direct lifting pushing module and the indirect pushing module are indispensable, and the engine and the fuselage of the airplane are required to be relatively improved under the condition of standard reasonable distribution of the energy of the existing airplane.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be able to substitute or change the technical solution and the inventive concept of the present invention within the technical scope of the present invention.
Claims (9)
1. An enhanced aircraft power propulsion system, comprising: the system comprises a direct lifting pushing module, an indirect lifting pushing module and an airborne control module; the direct lifting pushing module and the indirect lifting pushing module are electrically connected through the airborne control module;
directly lifting the power module, performing supercharging and cooling treatment on the engine on the premise of safety and stability, and performing weight reduction treatment on the material;
the power module is indirectly lifted, reasonable distribution is carried out on the basis of normal airplane power, energy is reasonably utilized, and power is optimized on the premise of safety;
and the airborne control module is used for detecting, controlling and recording the systems and managing and planning the systems.
2. An enhanced aircraft powered propulsion system as claimed in claim 1, wherein the direct lift propulsion module comprises: the power filling module and the power detection module.
3. An enhanced aircraft powered propulsion system as claimed in claim 1, wherein the indirect lift propulsion module comprises: the driving detection module, the energy distribution module, the data recording module, the data simulation module and the power detection module.
4. A propulsion system for augmenting power of an aircraft according to claim 3, wherein the piloting detection module is adapted to detect piloting information of the aircraft pilot, detect and record operating modes under different conditions;
the energy distribution module is used for performing algorithmic energy distribution on performance indexes among the systems and the result of the power actual measurement analysis through a set algorithm;
the data recording module is used for carrying out interactive recording on all subsystems of the airplane to obtain performance indexes between all the systems and power under different environments and different operations;
the data simulation module is used for carrying out digital simulation on each system and analyzing and simulating the performance indexes among the systems;
and the power detection module is used for carrying out experimental detection on each index of the data simulation and testing the influence relationship between independent operation among the systems and other systems.
5. An enhanced aircraft power propulsion system as claimed in claim 2, wherein said power replenishment module comprises: air inlet pressurization module, air inlet cooling module, air inlet pressurization module improves air inlet air flow velocity, and air inlet cooling module carries out cooling on a large scale to the high-speed air that flows of air inlet to rationally cool down the engine.
6. An enhanced aircraft power propulsion system according to claim 3, wherein the data simulation module is configured to perform optimal simulation testing of a single system under different circumstances.
7. A propulsion system for augmenting power of an aircraft according to claim 3, wherein the energy distribution module is configured to distribute energy to the systems and record the habitual adjustments of the pilot based on the values obtained by the particle swarm optimization.
8. The propulsion system for enhancing power of an airplane as claimed in claim 3, wherein the power detection module is based on a data simulation module for performing an overall test and detection on power, and a specific set value is obtained on the premise of safely improving power.
9. An indirect power boost method for an aircraft powered propulsion system according to claim 1, including the steps of:
step 1, carrying out interactive recording on all subsystems of an airplane, and recording the relation between the power and the operation of the airplane;
step 2, acquiring performance indexes between each system and power under different environments and different operations;
step 3, establishing a visual digital model for the obtained information and the power performance index;
step 4, analyzing each system and performance through a visual digital model, and analyzing the operation habits and the dynamic performance of a driver;
step 5, obtaining a power optimal flight mode, and analyzing the operation habits of a driver to obtain a power optimal operation mode;
and 6, reasonably distributing and optimally distributing the systems based on the visual digital models among the systems, and reasonably arranging the operation modes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111205305.2A CN113859551B (en) | 2021-10-15 | 2021-10-15 | Propelling system for enhancing power of airplane |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111205305.2A CN113859551B (en) | 2021-10-15 | 2021-10-15 | Propelling system for enhancing power of airplane |
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| CN113859551A true CN113859551A (en) | 2021-12-31 |
| CN113859551B CN113859551B (en) | 2024-04-12 |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140336847A1 (en) * | 2011-08-22 | 2014-11-13 | Borealis Technical Limited | Method for optimizing operation of aircraft ground travel drive system |
| CN205221119U (en) * | 2015-12-28 | 2016-05-11 | 黑龙江八一农垦大学 | Spray insecticide with telecontrolled aircraft watering can mount |
| CA2996844A1 (en) * | 2014-08-29 | 2016-06-16 | Tzunum, Inc. | Power train for a hybrid-electric aircraft |
| CN109101036A (en) * | 2018-10-30 | 2018-12-28 | 佛山市神风航空科技有限公司 | A kind of more rotor manned vehicle flight control systems |
| US20190283888A1 (en) * | 2018-03-13 | 2019-09-19 | U. S. Aeronautics, Inc. | Efficient low-noise aircraft propulsion system |
| CN210555636U (en) * | 2019-06-25 | 2020-05-19 | 黑龙江八一农垦大学 | Visual control spraying test bed for multi-rotor unmanned aerial vehicle |
-
2021
- 2021-10-15 CN CN202111205305.2A patent/CN113859551B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140336847A1 (en) * | 2011-08-22 | 2014-11-13 | Borealis Technical Limited | Method for optimizing operation of aircraft ground travel drive system |
| CA2996844A1 (en) * | 2014-08-29 | 2016-06-16 | Tzunum, Inc. | Power train for a hybrid-electric aircraft |
| CN205221119U (en) * | 2015-12-28 | 2016-05-11 | 黑龙江八一农垦大学 | Spray insecticide with telecontrolled aircraft watering can mount |
| US20190283888A1 (en) * | 2018-03-13 | 2019-09-19 | U. S. Aeronautics, Inc. | Efficient low-noise aircraft propulsion system |
| CN109101036A (en) * | 2018-10-30 | 2018-12-28 | 佛山市神风航空科技有限公司 | A kind of more rotor manned vehicle flight control systems |
| CN210555636U (en) * | 2019-06-25 | 2020-05-19 | 黑龙江八一农垦大学 | Visual control spraying test bed for multi-rotor unmanned aerial vehicle |
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| CN113859551B (en) | 2024-04-12 |
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