CN109927916A - A kind of military aircraft composite material radome fairing - Google Patents
A kind of military aircraft composite material radome fairing Download PDFInfo
- Publication number
- CN109927916A CN109927916A CN201711367184.5A CN201711367184A CN109927916A CN 109927916 A CN109927916 A CN 109927916A CN 201711367184 A CN201711367184 A CN 201711367184A CN 109927916 A CN109927916 A CN 109927916A
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- China
- Prior art keywords
- radome fairing
- military aircraft
- fixedly connected
- sleeve
- composite material
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- 239000002131 composite material Substances 0.000 title claims abstract description 13
- 238000013016 damping Methods 0.000 claims abstract description 18
- 238000003825 pressing Methods 0.000 claims abstract description 14
- 229920000742 Cotton Polymers 0.000 claims description 9
- 230000030279 gene silencing Effects 0.000 claims description 6
- 238000000034 method Methods 0.000 abstract description 6
- 239000010410 layer Substances 0.000 description 9
- 241000219146 Gossypium Species 0.000 description 8
- 230000000694 effects Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 239000011241 protective layer Substances 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
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Abstract
The invention discloses a kind of military aircraft composite material radome fairings, including outer outlet body and interior cover, the inner cover body is located on the inside of outer outlet body, and it is detachably connected, damping device is removably connected between the outer outlet body and interior cover, the damping device includes inner sleeve and outer sleeve, the outer sleeve inner wall slidably connects inner sleeve, No. two springs and pressing plate are equipped with inside the outer sleeve, No. two spring one ends are fixed at the top of outer sleeve, No. two spring other ends are fixedly connected with pressing plate upper end, the inner sleeve upper end is fixedly connected with pressing plate lower end, No.1 spring is equipped on the outside of the inner sleeve, the outer sleeve upper end is fixedly connected with No.1 fixed plate, the inner sleeve lower end is fixedly connected with No. two fixed plates.The military aircraft composite material radome fairing can be realized the multidimensional shock-absorbing function of military aircraft engine, reduce the shock-effect of engine in the process of running by being equipped with damping device.
Description
Technical field
The present invention relates to military aircraft technical field, specially a kind of military aircraft composite material radome fairing.
Background technique
Military aircraft be directly get into action, ensure combat action and military training aircraft general name.It is air arm
Major technique equipment.Specifically include that fighter plane, bomber, fighter-bomber, attack plane, anti-submarine patrol aircraft, armed helicopter,
Reconnaissance plane, early warning plane, electronics countermeasure aircraft, artillery fire-directing and reconnaissance aircraft, seaplane, military transportation airplane, tanker aircraft and
Trainer aircraft etc..Aircraft is used primarily for the military reconnaissance mission that mainly carries out, and is also used for bombing ground target once in a while and attack is aerial
Enemy plane.During the World War I, occur exclusively for the military aircraft for executing certain task and developing, such as be mainly used for
The fighter plane of air battle, dedicated for assaulting the bomber of ground target and the attack plane for directly supporting ground forces' operation,
And radome fairing is almost seen everywhere in our life, as having radome fairing on motorcycle, automobile, train or even electric vehicle
Shadow, military aircraft radome fairing most directly effect be protection the inside equipment and various devices, and be made into it is streamlined nothing but
Exactly in order to lower resistance,.
Existing military aircraft radome fairing generates biggish vibration due to engine operation when in use, so that rectification
A degree of shake occurs for cover, has seriously affected the service life of components in radome fairing.And when engine operation, generate
Biggish noise causes certain noise pollution to engine room inside, and inside radome fairing when generation fire, the intensity of a fire is along whole
Stream cover sprawling, damages aircraft.
Summary of the invention
The purpose of the present invention is to provide a kind of military aircraft composite material radome fairings, whole to solve existing military aircraft
Stream cover is when in use since engine operation generates biggish vibration, so that a degree of shake occurs for radome fairing, sternly
The service life of components in radome fairing is affected again.And when engine operation, biggish noise is generated, engine room inside is made
At certain noise pollution, and inside radome fairing when generation fire, the intensity of a fire is spread along radome fairing, is damaged to aircraft
The problem of.
To achieve the above object, the present invention provides the following technical solutions a kind of military aircraft composite material radome fairing, including
Outer outlet body and interior cover, the inner cover body is located on the inside of outer outlet body, and is detachably connected, can between the outer outlet body and interior cover
Dismantling connection has damping device, and the damping device includes inner sleeve and outer sleeve, and the outer sleeve inner wall slidably connects interior
Sleeve, the outer sleeve inside are equipped with No. two springs and pressing plate, and No. two spring one ends are fixed at the top of outer sleeve, and described two
Number spring other end is fixedly connected with pressing plate upper end, and the inner sleeve upper end is fixedly connected with pressing plate lower end, outside the inner sleeve
Side is equipped with No.1 spring, and the outer sleeve upper end is fixedly connected with No.1 fixed plate, and the inner sleeve lower end is fixedly connected with two
Number fixed plate is equipped with silencing cotton between the outer outlet body and interior cover.
Preferably, inner cover body surface face is provided with heat release hole.
Preferably, side is equipped with fireprotection layer in the inner cover body, is provided with link block on the inside of the fireprotection layer.
Preferably, the outer outlet body upper end, which is fixed by the connecting rod, is connected with mounting plate, and the installation plate surface is equipped with dress
Distribution.
Preferably, the damping device particular number is provided with four groups.
Compared with prior art, the beneficial effects of the present invention are:
1, the present invention can be realized the multidimensional shock-absorbing function of military aircraft engine, lower by being provided with four groups of damping devices
The shock-effect of engine in the process of running avoids engine that radome fairing covibration is caused to occur at work, improves
The stability of military aircraft radome fairing, and effectively the components inside radome fairing are protected.
2, the present invention is by being provided with silencing cotton, and silencing cotton can effectively reduce making an uproar of generating when aircraft engine work
Sound reduces the noise pollution to engine room inside, and is equipped with protective layer in interior cover side, and fireprotection layer can be avoided effectively
Fire occurs inside radome fairing, improves the safe application performance of radome fairing.
Detailed description of the invention
Fig. 1 is schematic structural view of the invention；
Fig. 2 is shock-damping structure schematic diagram of the present invention.
In figure: 1, outer outlet body, 2, interior cover, 3, damping device, 4, heat release hole, 5, fireprotection layer, 6, mounting plate, 7, assembly
Hole, 8, connecting rod, 9, link block, 10, No.1 fixed plate, 11, outer sleeve, 12, pressing plate, 13, No.1 spring, 14, No. two fixations
Plate, 15, inner sleeve, 16, No. two springs, 17, acoustical cotton.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
The present invention provides a kind of technical solution referring to FIG. 1-2: a kind of military aircraft composite material radome fairing, including outer
Cover 1, interior cover 2, damping device 3, heat release hole 4, fireprotection layer 5, mounting plate 6, pilot hole 7, connecting rod 8, link block 9, No.1
Fixed plate 10, outer sleeve 11, pressing plate 12,13, No. two fixed plates 14 of No.1 spring, inner sleeve 15, No. two springs 16 and acoustical cottons
17, interior cover 2 is located at 1 inside of outer outlet body, and is detachably connected, and interior 2 surface of cover is provided with heat release hole 4, and heat release hole 4 can have
Radiating to radome fairing for effect, avoids radome fairing internal temperature excessively high and reduces the service life of radome fairing, in interior cover 2
Side is equipped with fireprotection layer 5, and link block 9 is provided on the inside of fireprotection layer 5, and fireprotection layer 5 can effectively avoid that fire occurs inside radome fairing
Calamity improves the safe application performance of radome fairing, and link block 9 is convenient for for engine being mounted on inside radome fairing, 1 He of outer outlet body
Damping device 3 is removably connected between interior cover 2, and damping device 3 is specifically equipped with four groups, four groups of damping devices 3 can be real
The multidimensional shock-absorbing function of existing military aircraft engine, reduces the shock-effect of engine in the process of running, avoids engine
It causes radome fairing covibration to occur at work, improves the stability of military aircraft radome fairing, and effectively to rectification
Components inside cover are protected, and damping device 3 includes inner sleeve 15 and outer sleeve 11, and 11 inner wall of outer sleeve slidably connects
Inner sleeve 15 is equipped with No. two springs 16 and pressing plate 12 inside outer sleeve 11, and No. two 16 one end of spring are fixed on 11 top of outer sleeve,
No. two 16 other ends of spring are fixedly connected with 12 upper end of pressing plate, and 15 upper end of inner sleeve is fixedly connected with 12 lower end of pressing plate, inner sleeve
15 outsides are equipped with No.1 spring 13, and 11 upper end of outer sleeve is fixedly connected with No.1 fixed plate 10, and 15 lower end of inner sleeve is fixedly connected
There are No. two fixed plates 14, silencing cotton 17 is equipped between outer outlet body 1 and interior cover 2, silencing cotton 17 can effectively reduce military fly
The noise generated when machine engine operation, reduces the noise pollution to engine room inside, and 1 upper end of outer outlet body is solid by connecting rod 8
Surely it is connected with mounting plate 6,6 surface of mounting plate is equipped with pilot hole 7, and connecting rod 8 is convenient for mounting plate 6 being fixed on 1 upper end of outer outlet body,
Pilot hole 7 is convenient for for radome fairing being mounted on wing.
Working principle: when in use, radome fairing is fixed on wing by mounting plate 6, is then tightened in dress with bolt
In distribution 7, then engine is passed through into link block 9 and is mounted in interior cover 2, military aircraft engine can generate centainly at work
Shake, and the damping device 3 between interior cover 9 and outer outlet body 1 can be realized the multidimensional shock-absorbing function of military aircraft engine,
The shock-effect of engine in the process of running is reduced, avoids engine that radome fairing covibration is caused to occur at work,
The stability of military aircraft radome fairing is improved, and effectively the components inside radome fairing are protected, and starts
The noise that machine generates is absorbed by acoustical cotton 17, is reduced the noise generated when aircraft engine work, is reduced to engine room inside
Noise pollution, and the fireprotection layer 5 of 2 inside of interior cover can effectively avoid that fire occurs inside radome fairing, improve radome fairing
Safe application performance.
Although the present invention is described in detail referring to the foregoing embodiments, for those skilled in the art,
It is still possible to modify the technical solutions described in the foregoing embodiments, or part of technical characteristic is carried out etc.
With replacement, all within the spirits and principles of the present invention, any modification, equivalent replacement, improvement and so on should be included in this
Within the protection scope of invention.
Claims (5)
1. a kind of military aircraft composite material radome fairing, including outer outlet body (1) and interior cover (2), the interior cover (2) is located at outer
It on the inside of cover (1), and is detachably connected, it is characterised in that: be removably connected between the outer outlet body (1) and interior cover (2)
Damping device (3), the damping device (3) include inner sleeve (15) and outer sleeve (11), outer sleeve (11) the inner wall sliding
It is connected with inner sleeve (15), No. two springs (16) and pressing plate (12), No. two springs is equipped with inside the outer sleeve (11)
(16) one end is fixed at the top of outer sleeve (11), and No. two springs (16) other end is fixedly connected with pressing plate (12) upper end, institute
It states inner sleeve (15) upper end to be fixedly connected with pressing plate (12) lower end, is equipped with No.1 spring (13) on the outside of the inner sleeve (15), institute
It states outer sleeve (11) upper end to be fixedly connected with No.1 fixed plate (10), inner sleeve (15) lower end is fixedly connected with No. two fixations
Plate (14) is equipped with silencing cotton (17) between the outer outlet body (1) and interior cover (2).
2. a kind of military aircraft composite material radome fairing according to claim 1, it is characterised in that: the interior cover (2)
Surface is provided with heat release hole (4).
3. a kind of military aircraft composite material radome fairing according to claim 1, it is characterised in that: the interior cover (2)
Inside is equipped with fireprotection layer (5), is provided with link block (9) on the inside of the fireprotection layer (5).
4. a kind of military aircraft composite material radome fairing according to claim 1, it is characterised in that: the outer outlet body (1)
Upper end is fixedly connected with mounting plate (6) by connecting rod (8), and mounting plate (6) surface is equipped with pilot hole (7).
5. a kind of military aircraft composite material radome fairing according to claim 1, it is characterised in that: the damping device
(3) particular number is provided with four groups.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711367184.5A CN109927916A (en) | 2017-12-18 | 2017-12-18 | A kind of military aircraft composite material radome fairing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711367184.5A CN109927916A (en) | 2017-12-18 | 2017-12-18 | A kind of military aircraft composite material radome fairing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109927916A true CN109927916A (en) | 2019-06-25 |
Family
ID=66982894
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711367184.5A Pending CN109927916A (en) | 2017-12-18 | 2017-12-18 | A kind of military aircraft composite material radome fairing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109927916A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110374747A (en) * | 2019-07-25 | 2019-10-25 | 中国航发沈阳发动机研究所 | A kind of aircraft engine bleed air line with self-compensating function |
| CN111846251A (en) * | 2020-07-10 | 2020-10-30 | 山东太古飞机工程有限公司 | Sand prevention protection device for air inlet, exhaust and tail nozzle of engine |
-
2017
- 2017-12-18 CN CN201711367184.5A patent/CN109927916A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110374747A (en) * | 2019-07-25 | 2019-10-25 | 中国航发沈阳发动机研究所 | A kind of aircraft engine bleed air line with self-compensating function |
| CN111846251A (en) * | 2020-07-10 | 2020-10-30 | 山东太古飞机工程有限公司 | Sand prevention protection device for air inlet, exhaust and tail nozzle of engine |
| CN111846251B (en) * | 2020-07-10 | 2024-03-19 | 山东太古飞机工程有限公司 | Sand-proof protection device for air inlet, exhaust and tail nozzle of engine |
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| PB01 | Publication | ||
| PB01 | Publication | ||
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20190625 |