CN107097963B - Aircraft energy-storage system and energy management method with elastic energy storage mechanism - Google Patents
Aircraft energy-storage system and energy management method with elastic energy storage mechanism Download PDFInfo
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- CN107097963B CN107097963B CN201710274196.7A CN201710274196A CN107097963B CN 107097963 B CN107097963 B CN 107097963B CN 201710274196 A CN201710274196 A CN 201710274196A CN 107097963 B CN107097963 B CN 107097963B
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- energy
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- clutch
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- 238000004146 energy storage Methods 0.000 title claims abstract description 45
- 230000007246 mechanism Effects 0.000 title claims abstract description 15
- 238000007726 management method Methods 0.000 title claims abstract description 10
- 230000005540 biological transmission Effects 0.000 claims abstract description 33
- 239000002184 metal Substances 0.000 claims description 16
- 229910052751 metal Inorganic materials 0.000 claims description 16
- 238000000034 method Methods 0.000 claims description 5
- 230000009194 climbing Effects 0.000 claims description 3
- 238000003912 environmental pollution Methods 0.000 abstract description 3
- 239000000295 fuel oil Substances 0.000 abstract description 3
- 239000002699 waste material Substances 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 5
- 230000008859 change Effects 0.000 description 2
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 1
- 239000010931 gold Substances 0.000 description 1
- 229910052737 gold Inorganic materials 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000003921 oil Substances 0.000 description 1
Classifications
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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
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
- B64D35/02—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions specially adapted for specific power plants
-
- 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
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
-
- 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
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Arrangement Or Mounting Of Propulsion Units For Vehicles (AREA)
Abstract
Aircraft energy-storage system and energy management method with elastic energy storage mechanism, belong to energy storage and field of energy management.Solving the problems, such as aircraft fuel oil, there are a large amount of energy wastes and environmental pollution.One end of one bearing of the output shaft and coupler of engine of the invention is coaxially connected, the other end of first transmission shaft of coupler and the input shaft of retarder are coaxially connected, retarder drives propeller rotation, power is provided for aircraft, one end of No. two transmission shafts of the No.1 transmission shaft and brake of elastic accumulator is coaxially connected, and the other end of No. two transmission shafts of brake is coaxially connected by the second driving shaft of clutch and driver and coupler.The power energy storage that the present invention is suitable for aircraft uses.
Description
Technical field
The invention belongs to energy storage and field of energy management.
Background technique
Aircraft is mainly the main energy sources using fuel oil as aircraft, and conventional airplane has a large amount of energy wave in landing
Take, serious with problem of environmental pollution, to plane discharge, more stringent requirements are proposed, in order to improve the comprehensive utilization of energy
Rate reduces the influence to environment, it is necessary to take more reasonable energy stores and management method, realize to the excellent of energy framework
Change.
Summary of the invention
The present invention is to solve the problems, such as that aircraft fuel oil there are a large amount of energy waste and environmental pollution, proposes one kind
Aircraft energy-storage system and energy management method with elastic energy storage mechanism.
Aircraft energy-storage system of the present invention with elastic energy storage mechanism, it includes engine 1, coupler 2, slows down
Device 3, propeller 4, clutch 5, driver 6, brake 7 and elastic accumulator 8；
The output shaft of engine 1 and one end of the first transmission shaft of coupler 2 are coaxially connected, the first transmission of coupler 2
The other end of axis and the input shaft of retarder 3 are coaxially connected, and retarder 3 drives propeller 4 to rotate, and provide power, bullet for aircraft
The No.1 transmission shaft of property accumulator 8 and one end of No. two transmission shafts of brake 7 are coaxially connected, No. two transmission shafts of brake 7
The other end it is coaxially connected by clutch 5 and driver 6 and the second driving shaft of coupler 2.
Further, brake 7 includes electromagnet 71, sheet metal 72, spring 73,74, No. two transmission shafts 75 of gear and gold
Belong to pin 76；
Electromagnet 71 is oppositely arranged with 72 1 side surface of sheet metal, another side surface of sheet metal 72 and the one of metallic pin 76
End connection, spring 73 are set in the outer surface of metallic pin 76, and gear 74 is set in the outer surface of No. two transmission shafts 75, gear 74
Outer surface is equipped with metal shell, the outer surface of the metal shell prolong circumferencial direction be provided with it is multiple for plugging metallic pin 76
Mouthful.
Further, elastic accumulator 8 includes cabinet 81, No.1 transmission shaft 82, whirlpool spring ontology 83 and chest expander 84；Whirlpool spring
Ontology 83 be arranged in cabinet 81, the outer end of whirlpool spring ontology 83 is connect with one end of chest expander 84, the other end of chest expander 84 and
The inner wall of cabinet 81 is fixedly connected；The fixed outside for being set in No.1 transmission shaft 82 of whirlpool spring ontology 83, and whirlpool spring ontology 83 is interior
End is rigidly connected with 82 side wall of No.1 transmission shaft.
The energy management method of aircraft energy-storage system with elastic energy storage mechanism, the specific steps of this method are as follows:
Step 1: working as aircraft landing, when being braked, clutch 5 is closed, and brake 7 releases brake, and braking energy passes through
Clutch 5 and driver 6 pass to elastic accumulator 8, and elastic accumulator 8 starts to store energy, the pulling force according to suffered by chest expander,
The energy for determining elastic accumulator 8, when the energy of elastic accumulator 8 reaches the 90% of specified energy storage, clutch 5 is disengaged, system
Dynamic device 7 brakes, and stops energy storage；
Step 2: being closed clutch 5 when taking off, climbing or accelerating, brake 7 releases brake, elastic accumulator
8 release energy, and provide flying power jointly with engine 1 for aircraft, the pulling force according to suffered by chest expander determines elastic accumulator
Energy, when the energy of elastic accumulator drops to the 20% of specified energy storage, clutch 5 is disengaged, and brake 7 brakes, elastic energy storage
Device 8 stops energy release.
Aircraft bullet energy-storage system and its energy management method proposed by the present invention with elastic energy storage mechanism, using machinery
Coupling, it is simple and reliable for structure, engine power is converted into elasticity in aircraft landing and releases energy, elasticity is discharged when taking off
Energy is released, engine efficiency and capacity usage ratio is improved, reduces plane discharge, reduce oil consumption, reach environmental protection and section
The about double effects of cost.
Detailed description of the invention
Fig. 1 is the functional block diagram of the aircraft energy-storage system of the present invention with elastic energy storage mechanism；
Fig. 2 is the structural schematic diagram of brake described in specific embodiment two；
Fig. 3 is the structural schematic diagram of elastic accumulator described in specific embodiment three；
Status diagram when Fig. 4 is driver gear 1 described in specific embodiment three；
Status diagram when Fig. 5 is driver gear 2 described in specific embodiment three
Specific embodiment
In order to make the objectives, technical solutions, and advantages of the present invention clearer, with reference to the accompanying drawings and embodiments, right
The present invention is further elaborated.It should be appreciated that the specific embodiments described herein are merely illustrative of the present invention, and
It is not used in the restriction present invention.
Specific embodiment one, embodiment is described with reference to Fig. 1, and elastic energy storage mechanism is had described in present embodiment
Aircraft energy-storage system, it includes engine 1, coupler 2, retarder 3, propeller 4, clutch 5, driver 6, brake 7
With elastic accumulator 8；
The output shaft of engine 1 and one end of the first transmission shaft of coupler 2 are coaxially connected, the first transmission of coupler 2
The other end of axis and the input shaft of retarder 3 are coaxially connected, and retarder 3 drives propeller 4 to rotate, and provide power, bullet for aircraft
The No.1 transmission shaft of property accumulator 8 and one end of No. two transmission shafts of brake 7 are coaxially connected, No. two transmission shafts of brake 7
The other end it is coaxially connected by clutch 5 and driver 6 and the second driving shaft of coupler 2.
Specific embodiment two, embodiment is described with reference to Fig. 2, and present embodiment is to described in specific embodiment one
The aircraft energy-storage system with elastic energy storage mechanism further explanation, brake 7 include electromagnet 71, sheet metal 72, bullet
Spring 73,74, No. two transmission shafts 75 of gear and metallic pin 76；
Electromagnet 71 is oppositely arranged with 72 1 side surface of sheet metal, another side surface of sheet metal 72 and the one of metallic pin 76
End connection, spring 73 are set in the outer surface of metallic pin 76, and gear 74 is set in the outer surface of No. two transmission shafts 75, gear 74
Outer surface is equipped with metal shell, the outer surface of the metal shell prolong circumferencial direction be provided with it is multiple for plugging metallic pin 76
Mouthful.
Specific embodiment three, embodiment is described with reference to Fig. 3, and present embodiment is to described in specific embodiment one
The aircraft energy-storage system with elastic energy storage mechanism further explanation, elastic accumulator 8 include cabinet 81, No.1 transmission shaft
82, whirlpool spring ontology 83 and chest expander 84；Whirlpool spring ontology 83 is arranged in cabinet 81, outer end and the chest expander 84 of whirlpool spring ontology 83
One end connection, the other end of chest expander 84 are fixedly connected with the inner wall of cabinet 81；Whirlpool spring ontology 83 is fixed to be set in No.1 transmission
The outside of axis 82, and the inner end of whirlpool spring ontology 83 and 82 side wall of No.1 transmission shaft are rigidly connected.
When elastic accumulator stores energy, the gear change of driver such as Fig. 4；When elastic accumulator releases energy, gear
Such as Fig. 5.
The energy pipe of aircraft energy-storage system described in specific embodiment four, present embodiment with elastic energy storage mechanism
Reason method, the specific steps of this method are as follows:
Step 1: working as aircraft landing, when being braked, clutch 5 is closed, and brake 7 releases brake, and braking energy passes through
Clutch 5 and driver 6 pass to elastic accumulator 8, and elastic accumulator 8 starts to store energy, the pulling force according to suffered by chest expander,
The energy for determining elastic accumulator 8, when the energy of elastic accumulator 8 reaches the 90% of specified energy storage, clutch 5 is disengaged, system
Dynamic device 7 brakes, and stops energy storage；
Step 2: being closed clutch 5 when taking off, climbing or accelerating, brake 7 releases brake, elastic accumulator
8 release energy, and provide flying power jointly with engine 1 for aircraft, the pulling force according to suffered by chest expander determines elastic accumulator
Energy, when the energy of elastic accumulator drops to the 20% of specified energy storage, clutch 5 is disengaged, and brake 7 brakes, elastic energy storage
Device 8 stops energy release.
In present embodiment, before elastic accumulator device practical application, first elastic accumulator is tested, is obtained more
Pulling force T and bullet suffered by the chest expander that the experiment historical data of energy U stored by pulling force T and spring suffered by group chest expander is fitted
The relational expression U=f (T) of energy U stored by spring.
In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, is integrally connected, may be a detachable connection；It can be with
It is the connection inside two elements；It can be directly connected, it can also indirectly connected through an intermediary, for the general of this field
For logical technical staff, the concrete meaning of above-mentioned term in the present invention can be understood with concrete condition.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all in essence of the invention
Made any modifications, equivalent replacements, and improvements etc., should all be included in the protection scope of the present invention within mind and principle.
Claims (3)
1. having the aircraft energy-storage system of elastic energy storage mechanism, which is characterized in that it includes engine (1), coupler (2), subtracts
Fast device (3), propeller (4), clutch (5), driver (6), brake (7) and elastic accumulator (8)；
The output shaft of engine (1) and one end of the first transmission shaft of coupler (2) are coaxially connected, and the first of coupler (2) passes
The other end of moving axis and the input shaft of retarder (3) are coaxially connected, and retarder (3) drives propeller (4) rotation, provide for aircraft
Power, the No.1 transmission shaft of elastic accumulator (8) and one end of No. two transmission shafts of brake (7) are coaxially connected, brake (7)
No. two transmission shafts the other end it is coaxially connected by clutch (5) and driver (6) and the second driving shaft of coupler (2)；
Brake (7) includes electromagnet (71), sheet metal (72), spring (73), gear (74), No. two transmission shafts (75) and metal
It sells (76)；
Electromagnet (71) is oppositely arranged with (72) one side surface of sheet metal, another side surface and metallic pin (76) of sheet metal (72)
One end connection, spring (73) is set in the outer surface of metallic pin (76), and gear (74) is set in the outer of No. two transmission shafts (75)
The outer surface on surface, gear (74) is equipped with metal shell, and the outer surface of the metal shell prolongs circumferencial direction and is provided with multiple be used for
Plug the mouth of metallic pin (76).
2. the aircraft energy-storage system according to claim 1 with elastic energy storage mechanism, which is characterized in that elastic accumulator
It (8) include cabinet (81), No.1 transmission shaft (82), whirlpool spring ontology (83) and chest expander (84)；Whirlpool spring ontology (83) is arranged in case
In body (81), the outer end of whirlpool spring ontology (83) is connect with one end of chest expander (84), the other end and cabinet of chest expander (84)
(81) inner wall is fixedly connected；The fixed outside for being set in No.1 transmission shaft (82) of whirlpool spring ontology (83), and whirlpool spring ontology (83)
Inner end and No.1 transmission shaft (82) side wall be rigidly connected.
3. the energy management method of the aircraft energy-storage system with elastic energy storage mechanism, feature exist as described in claim 1
In the specific steps of this method are as follows:
Step 1: working as aircraft landing, when being braked, clutch (5) closure, brake (7) releases brake, and braking energy passes through
Clutch (5) and driver (6) pass to elastic accumulator (8), and elastic accumulator (8) starts to store energy, according to chest expander
Suffered pulling force determines the energy of elastic accumulator (8), when the energy of elastic accumulator (8) reaches the 90% of specified energy storage, from
Clutch (5) disengages, and brake (7) brake stops energy storage；
Step 2: being closed clutch (5) when taking off, climbing or accelerating, brake (7) releases brake, elastic accumulator
(8) it releases energy, provides flying power jointly with engine (1) for aircraft, the pulling force according to suffered by chest expander determines elastic energy storage
The energy of device, when the energy of elastic accumulator drops to the 20% of specified energy storage, clutch (5) is disengaged, brake (7) brake,
Elastic accumulator (8) stops energy release.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710274196.7A CN107097963B (en) | 2017-04-24 | 2017-04-24 | Aircraft energy-storage system and energy management method with elastic energy storage mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710274196.7A CN107097963B (en) | 2017-04-24 | 2017-04-24 | Aircraft energy-storage system and energy management method with elastic energy storage mechanism |
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| Publication Number | Publication Date |
|---|---|
| CN107097963A CN107097963A (en) | 2017-08-29 |
| CN107097963B true CN107097963B (en) | 2019-06-04 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201710274196.7A Expired - Fee Related CN107097963B (en) | 2017-04-24 | 2017-04-24 | Aircraft energy-storage system and energy management method with elastic energy storage mechanism |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107539485A (en) * | 2017-10-17 | 2018-01-05 | 天津邬金机械设备有限公司 | Suitable for the engine of general aviation aircraft |
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|---|---|---|---|---|
| CN101654098A (en) * | 2008-08-18 | 2010-02-24 | 封永记 | Energy-saving device of transport facility |
| CN201900998U (en) * | 2009-11-11 | 2011-07-20 | 曹国杰 | Energy storage and oil saving accelerator for brake |
| CN102442208A (en) * | 2011-11-02 | 2012-05-09 | 华北电力大学（保定） | Mechanical elastic energy storage driving device |
| CN104097760A (en) * | 2013-04-05 | 2014-10-15 | 青岛科技大学 | Mechanical energy storage vessel |
| CN204020570U (en) * | 2014-07-11 | 2014-12-17 | 肇庆工商职业技术学院 | The endergonic saving emission reduction device for automobile of one braking effect |
| CN204801759U (en) * | 2015-04-29 | 2015-11-25 | 南宁燎旺车灯有限责任公司 | Spring stored energy formula car braking energy recovery unit |
-
2017
- 2017-04-24 CN CN201710274196.7A patent/CN107097963B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101654098A (en) * | 2008-08-18 | 2010-02-24 | 封永记 | Energy-saving device of transport facility |
| CN201900998U (en) * | 2009-11-11 | 2011-07-20 | 曹国杰 | Energy storage and oil saving accelerator for brake |
| CN102442208A (en) * | 2011-11-02 | 2012-05-09 | 华北电力大学（保定） | Mechanical elastic energy storage driving device |
| CN104097760A (en) * | 2013-04-05 | 2014-10-15 | 青岛科技大学 | Mechanical energy storage vessel |
| CN204020570U (en) * | 2014-07-11 | 2014-12-17 | 肇庆工商职业技术学院 | The endergonic saving emission reduction device for automobile of one braking effect |
| CN204801759U (en) * | 2015-04-29 | 2015-11-25 | 南宁燎旺车灯有限责任公司 | Spring stored energy formula car braking energy recovery unit |
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| CN107097963A (en) | 2017-08-29 |
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Granted publication date: 20190604 Termination date: 20200424 |