CN103847973A - Small general-purpose aircraft power supply capacity expanding system - Google Patents
Small general-purpose aircraft power supply capacity expanding system Download PDFInfo
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- CN103847973A CN103847973A CN201210515463.2A CN201210515463A CN103847973A CN 103847973 A CN103847973 A CN 103847973A CN 201210515463 A CN201210515463 A CN 201210515463A CN 103847973 A CN103847973 A CN 103847973A
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- electrical generator
- small general
- power supply
- power
- driving device
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Abstract
The invention relates to a small general-purpose aircraft power supply capacity expanding system. The small general-purpose aircraft power supply capacity expanding system structurally comprises an electrical generator, a transmission gear and an electrical generator mounting base, wherein the power of the electrical generator is at least more than 12kW; the transmission gear is connected between the power output shaft of an aircraft engine and the electrical generator and has steering and speed increasing functions; the electrical generator mounting base is used for mounting and fixing the electrical generator on the transmission gear; the transmission gear comprises a shell, an end cover buckled on the shell, and a gear variable transmission mechanism arranged in the shell; the electrical generator mounting base is fixed on the outer side face of the end cover on the transmission gear. The system is suitable for power capacity expansion of various small general-purpose aircrafts, is simple in structure, reasonable in design, good in operability, convenient to mount and maintain, can meet the electricity demand of high-power loading equipment, improves the stability of working current, and is beneficial to improving the flight safety of the small general-purpose aircrafts.
Description
Technical field
The present invention relates to a kind of power-supply system of aircraft, specifically a kind of Small General Aircraft power supply capacity-enlarging system.
Background technology
The power-supply system of Small General Aircraft is made up of main power source, emergency source of electrical power and secondary power supply, sometimes also comprises accessory feed; Wherein main power source is made up of electrical generator and the power supply control protection equipment etc. of aero-engine transmission, awing for the consumer on Small General Aircraft provides stable working power.Consumer on Small General Aircraft is not all to work in whole flight course simultaneously, and the equipment that aircraft task different mission phases different or same task use is also often not identical.Generally, the power of the power-supply system of Small General Aircraft is to design according to the aerial mission of electric power maximum and mission phase, conventionally requires the power of aircraft power supply to be greater than the desired electric power of maximum consumer.But the capacity of the power-supply system under the former design point of part Small General Aircraft is all less at present, the power of its output can not meet the need for electricity of the equipment that flight load power consumption is larger far away.
Summary of the invention
Object of the present invention is just to provide a kind of Small General Aircraft power supply capacity-enlarging system, to solve existing aircraft power system because capacity is compared with the problem of the little need for electricity that can not meet the equipment that flight load is larger.
The object of the present invention is achieved like this: a kind of Small General Aircraft power supply capacity-enlarging system, comprise: power is the electrical generator more than 12kW at least, be connected to the driving device with tuning and speedup function between aero-engine power take-off shaft and described electrical generator, and described electrical generator is fixed on to the electrical generator mount pad on described driving device;
Described driving device comprises: housing, is fastened on the end cap on described housing, and is arranged on the speed-changing gear driving device in described housing;
Described electrical generator mount pad is fixed on the lateral surface of the described end cap on described driving device.
On described electrical generator mount pad, be provided with quick-release ring, described electrical generator is fixedly mounted on described electrical generator mount pad by quick-release ring.
Described speed-changing gear driving device includes driving gear and driven gear; Described driving gear is supported by plain bearing, and described driven gear is supported by ball-bearing casing, and described driving gear and described driven gear are made axial limiting with collar.
The present invention be by adopt power at least the electrical generator more than 12 kW replace the 3 kW electrical generators that tradition is used on Small General Aircraft, expanded the capacity of aircraft power system, thereby met the high-performance power consumption requirements of mission payload; And for supporting high-power generator, also between the power take-off shaft of aero-engine and electrical generator design and installation there is the driving device of tuning and speedup function, this driving device makes driving gear be meshed with transmission gear by built-in speed-changing gear driving device, realize the function of speedup and commutation, drive electrical generator to send continual and steady working current.In addition, at the end cap arranged outside electrical generator mount pad of driving device, by this mount pad, electrical generator is fixed on driving device, forms integrative-structure, make the compact conformation of aircraft power supply capacity-enlarging system; On electrical generator mount pad, be also provided with quick-release ring, can carry out Fast Installation or dismounting to electrical generator by quick-release ring, improved the inspection operation of this aircraft power supply appearance system.
The present invention has solved the power supply dilatation problem of Small General Aircraft well, it is simple in structure, reasonable in design, good operability, installation and maintenance is convenient, with the equipped small power generator of this equipment replacement Small General Aircraft tradition, can meet the need for electricity of high-power loading device, improve the stability of working current, be conducive to improve the flight safety of Small General Aircraft.The present invention can be suitable for the power supply dilatation of multiple Small General Aircraft.
Brief description of the drawings
Fig. 1 is structural representation of the present invention.
Detailed description of the invention
As shown in Figure 1, the present invention is fixedly connected with driving device by the screw rod and the cover copper nut that arrange on the driving engine bonnet of Small General Aircraft, and described driving device comprises housing 1, is fastened on the end cap 2 on housing 1 and is arranged on the speed-changing gear driving device of housing 1 inside.Described speed-changing gear driving device comprises driving gear 3 and driven gear 4, and wherein driving gear 3 is supported by plain bearing, and driven gear 4 is supported by ball-bearing casing, and driving gear 3 and driven gear 4 adopt collar to make axial limiting.Have electrical generator mount pad 5 in the arranged outside of end cap 2, be provided with quick-release ring 7 at the front end of electrical generator mount pad 5, power is that the electrical generator 6 of 12 kW, 15 kW or 18 kW is fixed on electrical generator mount pad 5 by quick-release ring 7.The mouth of driven gear 4 drives electrical generator 6 to rotate, and produces stable working current.
The jointing that is provided with channel for oiling 8 above the housing 1 of described driving device, can make lubricating oil enter in housing 1 by channel for oiling 8, with oilgear and bearing, ensures the lubricated and cooling of driving device.Lubricated driving gear 3 and plain bearing can adopt enforced lubricating, and driven gear 4 and ball-bearing casing can adopt lubrication by atomization; Lubricating oil after lubricated directly flows in the recovery mouth of channel for oiling 8 of the foot of housing, and the oil pipe by oil return pipe on engine booster casing is latter half of, flows to lubricating oil pond.The mouth of driven gear 4 adopts screw thread and cup leather packing, in case on-slip oil seepage is to sending out in electrical generator, affects the normal work of equipment.
Working process of the present invention is: the power take-off shaft by driving engine drives the driving gear 3 in driving device to rotate by rectangular spline, driving gear 3 by with the engaging of driven gear 4, drive driven gear 4 to rotate, drive electrical generator 6 to rotate by driven gear 4, produce stable working current.
The present invention adopts 12 kW or more high-performance electrical generator to replace the electrical generator of 3 kW that use on original Small General Aircraft, to reach the required power supply capacity of power-supply system of Small General Aircraft, meets the need for electricity of the large power consumption of mission payload.At present Installation and trial run on Small General Aircraft successfully of this aircraft power supply capacity-enlarging system, and in repeatedly executing the task, met high-performance operating needs.Show through great many of experiments, this device is applicable to the power supply dilatation of multiple Small General Aircraft.
Claims (3)
1. a Small General Aircraft power supply capacity-enlarging system, it is characterized in that, comprise: power is the electrical generator more than 12kW at least, be connected to the driving device with tuning and speedup function between aero-engine power take-off shaft and described electrical generator, and described electrical generator is fixed on to the electrical generator mount pad on described driving device;
Described driving device comprises: housing, is fastened on the end cap on described housing, and is arranged on the speed-changing gear driving device in described housing;
Described electrical generator mount pad is fixed on the lateral surface of the described end cap on described driving device.
2. Small General Aircraft power supply capacity-enlarging system according to claim 1, is characterized in that, on described electrical generator mount pad, is provided with quick-release ring, and described electrical generator is fixedly mounted on described electrical generator mount pad by quick-release ring.
3. Small General Aircraft power supply capacity-enlarging system according to claim 1, is characterized in that, described speed-changing gear driving device includes driving gear and driven gear; Described driving gear is supported by plain bearing, and described driven gear is supported by ball-bearing casing, and described driving gear and described driven gear are made axial limiting with collar.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210515463.2A CN103847973A (en) | 2012-12-05 | 2012-12-05 | Small general-purpose aircraft power supply capacity expanding system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210515463.2A CN103847973A (en) | 2012-12-05 | 2012-12-05 | Small general-purpose aircraft power supply capacity expanding system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103847973A true CN103847973A (en) | 2014-06-11 |
Family
ID=50856188
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210515463.2A Pending CN103847973A (en) | 2012-12-05 | 2012-12-05 | Small general-purpose aircraft power supply capacity expanding system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103847973A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104890885A (en) * | 2015-06-23 | 2015-09-09 | 中国航空动力机械研究所 | Aero-generator mounting adapter and adapting mounting system |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1242883A (en) * | 1996-12-03 | 2000-01-26 | 艾略特能源系统股份有限公司 | Electrical system for turbin/alternator on common shaft |
| CN1705585A (en) * | 2002-10-22 | 2005-12-07 | 波音公司 | Electric-based secondary power system architectures for aircraft |
| CN101066704A (en) * | 2006-05-05 | 2007-11-07 | 伊斯帕诺-絮扎公司 | An electrical power supply arrangement for an aircraft |
| US20110252807A1 (en) * | 2010-04-20 | 2011-10-20 | General Electric Company | Accessory gearbox with a starter/generator |
-
2012
- 2012-12-05 CN CN201210515463.2A patent/CN103847973A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1242883A (en) * | 1996-12-03 | 2000-01-26 | 艾略特能源系统股份有限公司 | Electrical system for turbin/alternator on common shaft |
| CN1705585A (en) * | 2002-10-22 | 2005-12-07 | 波音公司 | Electric-based secondary power system architectures for aircraft |
| CN101066704A (en) * | 2006-05-05 | 2007-11-07 | 伊斯帕诺-絮扎公司 | An electrical power supply arrangement for an aircraft |
| US20110252807A1 (en) * | 2010-04-20 | 2011-10-20 | General Electric Company | Accessory gearbox with a starter/generator |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104890885A (en) * | 2015-06-23 | 2015-09-09 | 中国航空动力机械研究所 | Aero-generator mounting adapter and adapting mounting system |
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| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20140611 |