CN201371948Y - Shock absorbing mount of aircraft engine - Google Patents
Shock absorbing mount of aircraft engine Download PDFInfo
- Publication number
- CN201371948Y CN201371948Y CN200920126007U CN200920126007U CN201371948Y CN 201371948 Y CN201371948 Y CN 201371948Y CN 200920126007 U CN200920126007 U CN 200920126007U CN 200920126007 U CN200920126007 U CN 200920126007U CN 201371948 Y CN201371948 Y CN 201371948Y
- Authority
- CN
- China
- Prior art keywords
- vibration damper
- damper plate
- shock absorbing
- absorbing plate
- cushion blocking
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
- 230000035939 shock Effects 0.000 title claims abstract description 41
- 238000005452 bending Methods 0.000 claims abstract description 16
- 230000000903 blocking effect Effects 0.000 claims description 22
- 229910000838 Al alloy Inorganic materials 0.000 claims description 3
- 238000012856 packing Methods 0.000 claims description 3
- 238000010521 absorption reaction Methods 0.000 abstract 1
- 238000013016 damping Methods 0.000 description 12
- 229910000831 Steel Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
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- Vibration Prevention Devices (AREA)
Abstract
The utility model discloses a shock absorbing mount of an aircraft engine, which comprises a shock absorbing plate and shock absorbing cushions (1), wherein a support (2) is disposed below the shock absorbing plate. The shock absorbing mount is characterized in that the shock absorbing plate is divided into an upper shock absorbing plate (3) and a lower shock absorbing plate (4), two ends of the upper shock absorbing plate (3) and two ends of the lower shock absorbing plate (4) are all bent upwards, the upper shock absorbing plate (3) and the lower shock absorbing plate (4) are arranged in parallel, the shock absorbing cushions (1) are respectively arranged at the upper surface bending portions of the upper shock absorbing plate (3) and the lower shock absorbing plate (4), and the shock absorbing cushions (1) are fixed onto the upper shock absorbing plate (3) and the lower shock absorbing plate (4) through screw bolts. As the shock absorbing mount adopts two stages of shock absorption, the shock absorbing cushions and the shock absorbing plate can simultaneously absorb shocks, and bending portions of the shock absorbing plate on which the shock absorbing cushions are installed can absorb shocks of left and right impact forces when absorb shocks of up and down impact forces of a working engine.
Description
Technical field
The utility model belongs to a kind of driving engine shock mount, specifically, is the driving engine shock mount that a kind of aircraft is installed.
Background technology
At present, traditional aero-engine shock mount is made up of vibration damper plate, cushion blocking and the support support aboard of aluminium or steel, and cushion blocking is arranged on the vibration damper plate, and described vibration damper plate bottom connects support.The vibrations that driving engine produces at work only are responsible for absorbing impulsive force by cushion blocking, and whole driving engine shock mount remainder does not participate in damping; Because cushion blocking is arranged on the vibration damper plate plane, whole driving engine shock mount can only damping impulsive force up and down, the impulsive force about can not damping, and efficient is not high and mechanism's weight is heavier.
The utility model content
Technical problem to be solved in the utility model is to provide a kind of aero-engine shock mount that left and right sides impulsive force is carried out damping.
The technical solution of the utility model is as follows: a kind of aero-engine shock mount, comprise vibration damper plate and cushion blocking, this vibration damper plate bottom is provided with support, its key is: vibration damper plate is divided into vibration damper plate and following vibration damper plate, the described vibration damper plate of going up all upwards bends with following vibration damper plate two ends, should go up vibration damper plate and be arranged in parallel with following vibration damper plate, the described vibration damper plate of going up all is provided with cushion blocking with following vibration damper plate upper surface bending part, and described cushion blocking and last vibration damper plate are in the same place by bolt with following vibration damper plate.The bending at vibration damper plate two ends is provided with cushion blocking again, and the impulsive force about in the engine operation also can obtain the actv. damping, and it is practical more also to have changed the two-stage damping into.
Above-mentioned vibration damper plate and the play vibration damper plate two ends of going up all bend inwards and 45 spend.Can carry out damping to driving engine impulsive force up and down like this, it is best also to carry out damping effect to left and right sides impulsive force.
Above-mentioned bending place, vibration damper plate two ends down all is connected with support, and described support bottom is a straight section, and this support top bending is captiveed joint with following vibration damper plate homonymy bending place applying.The support bottom has the mounting hole that is installed on the aircraft for the straight section side.
The rubber cradle that above-mentioned cushion blocking is established by double-ply aluminum alloy round packing ring and therebetween is formed.
Beneficial effect: the utility model can participate in damping by cushion blocking and vibration damper plate simultaneously owing to be provided with the two-stage damping; Vibration damper plate is installed the bending of cushion blocking place, when impulsive force carries out damping up and down to engine operation, also left and right sides impulsive force is carried out damping.
Description of drawings
Fig. 1 is a structural representation of the present utility model;
Fig. 2 is the structural scheme of mechanism of the middle cushion blocking 1 of Fig. 1.
The specific embodiment
The utility model is described in further detail below in conjunction with drawings and Examples:
As shown in Figure 1 and Figure 2, a kind of aero-engine shock mount of the utility model, form by vibration damper plate and cushion blocking 1 and support 2, this vibration damper plate below is provided with support 2, described vibration damper plate is divided into vibration damper plate 3 and following vibration damper plate 4, the described vibration damper plate 3 of going up all upwards bends with following vibration damper plate 4 two ends, should go up vibration damper plate 3 be arranged in parallel with following vibration damper plate 4, describedly go up vibration damper plate 3 and play vibration damper plate 4 upper surface bending parts all are provided with cushion blocking 1, described cushion blocking 1 and last vibration damper plate 3 and following vibration damper plate 4 are in the same place by bolt.Last vibration damper plate 3 and play vibration damper plate 4 two ends all bend inwards and 45 spend.Two cushion blocking central lines of the same side, last vibration damper plate 3 all is in the same place by same bolt with the cushion blocking 1 on the following vibration damper plate 4 two ends bending parts.Last vibration damper plate 3 middle parts have the mounting hole that driving engine is installed.Following vibration damper plate 4 two ends bending parts all are connected with support 2, and described support 2 bottoms are straight section, fit with following vibration damper plate 4 bending parts in these support 2 tops.The rubber cradle 1b that described cushion blocking 1 is established by two-layer aluminum alloy round packing ring 1a and therebetween forms.
Claims (4)
1, a kind of aero-engine shock mount, comprise vibration damper plate and cushion blocking (1), this vibration damper plate below is provided with support (2), it is characterized in that: described vibration damper plate is divided into vibration damper plate (3) and following vibration damper plate (4), the all upwards bendings of described upward vibration damper plate (3) and following vibration damper plate (4) two ends, upward vibration damper plate (3) and following vibration damper plate (4) be arranged in parallel, described upward vibration damper plate (3) and following vibration damper plate (4) upper surface bending part all are provided with cushion blocking (1), and described cushion blocking (1) passes through bolt together with last vibration damper plate (3) and following vibration damper plate (4).
2, according to the described aero-engine shock mount of claim 1, it is characterized in that: described vibration damper plate (3) and following vibration damper plate (4) two ends of going up all bend inwards and 45 spend.
3, according to the described aero-engine shock mount of claim 1, it is characterized in that: described vibration damper plate (4) two ends bending part down all is connected with support (2), and described support (2) bottom is a straight section, fits with following vibration damper plate (4) bending part in this support (2) top.
4, according to the described aero-engine shock mount of claim 1, it is characterized in that: the rubber cradle (1b) that described cushion blocking (1) is established by two-layer aluminum alloy round packing ring (1a) and therebetween is formed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200920126007U CN201371948Y (en) | 2009-01-04 | 2009-01-04 | Shock absorbing mount of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200920126007U CN201371948Y (en) | 2009-01-04 | 2009-01-04 | Shock absorbing mount of aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201371948Y true CN201371948Y (en) | 2009-12-30 |
Family
ID=41498031
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200920126007U Expired - Fee Related CN201371948Y (en) | 2009-01-04 | 2009-01-04 | Shock absorbing mount of aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201371948Y (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102267569A (en) * | 2011-05-10 | 2011-12-07 | 北京航空航天大学 | Suspended engine connecting device for small-size unmanned helicopter |
| CN106428163A (en) * | 2016-11-25 | 2017-02-22 | 沈阳黎明航空发动机(集团)有限责任公司 | High-quality engine shock absorption transportation vehicle |
| CN111746805A (en) * | 2020-05-21 | 2020-10-09 | 卓尔飞机制造（武汉）有限公司 | Novel aircraft engine installing support |
-
2009
- 2009-01-04 CN CN200920126007U patent/CN201371948Y/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102267569A (en) * | 2011-05-10 | 2011-12-07 | 北京航空航天大学 | Suspended engine connecting device for small-size unmanned helicopter |
| CN102267569B (en) * | 2011-05-10 | 2013-12-04 | 北京航空航天大学 | Suspended engine connecting device for small-size unmanned helicopter |
| CN106428163A (en) * | 2016-11-25 | 2017-02-22 | 沈阳黎明航空发动机(集团)有限责任公司 | High-quality engine shock absorption transportation vehicle |
| CN111746805A (en) * | 2020-05-21 | 2020-10-09 | 卓尔飞机制造（武汉）有限公司 | Novel aircraft engine installing support |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20091230 Termination date: 20130104 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |