CN109268446B - Tandem type three-dimensional vibration reduction single-machine equipment installation device and aircraft - Google Patents
Tandem type three-dimensional vibration reduction single-machine equipment installation device and aircraft Download PDFInfo
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- CN109268446B CN109268446B CN201811253145.7A CN201811253145A CN109268446B CN 109268446 B CN109268446 B CN 109268446B CN 201811253145 A CN201811253145 A CN 201811253145A CN 109268446 B CN109268446 B CN 109268446B
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- 238000009434 installation Methods 0.000 title claims abstract description 36
- 238000013016 damping Methods 0.000 claims abstract description 144
- 239000006096 absorbing agent Substances 0.000 claims description 27
- 230000035939 shock Effects 0.000 claims description 25
- 230000000149 penetrating effect Effects 0.000 claims 2
- 230000000694 effects Effects 0.000 abstract description 7
- 238000010521 absorption reaction Methods 0.000 description 17
- 230000006835 compression Effects 0.000 description 8
- 238000007906 compression Methods 0.000 description 8
- 239000000463 material Substances 0.000 description 7
- 229920002379 silicone rubber Polymers 0.000 description 7
- 230000003321 amplification Effects 0.000 description 4
- 238000003199 nucleic acid amplification method Methods 0.000 description 4
- 230000001681 protective effect Effects 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 238000005259 measurement Methods 0.000 description 3
- 239000002131 composite material Substances 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 229910001220 stainless steel Inorganic materials 0.000 description 2
- 239000010935 stainless steel Substances 0.000 description 2
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
- F16F15/08—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means with rubber springs ; with springs made of rubber and metal
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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
- B64D47/00—Equipment not otherwise provided for
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Abstract
The invention discloses a tandem type three-dimensional vibration reduction single-machine equipment installation device and an aircraft, which relate to the field of aircraft single-machine vibration reduction installation structures and comprise: a deck section housing; the first bracket group comprises a first bracket and a second bracket which are fixed on the cabin section shell, and the first bracket and the second bracket are arranged at intervals. And the first damper group comprises a plurality of dampers, and is used for fixing the single equipment on the first bracket and damping the single equipment. And the second bracket group comprises a third bracket and a fourth bracket which are fixed on the cabin section shell, and the third bracket and the fourth bracket are arranged at intervals. The second support group is connected with the first support group in series, and the third support is connected with the second support. And the second damper group comprises a plurality of dampers, and is used for fixing the single equipment on the third bracket and damping the single equipment. The invention effectively solves the problem of the assembly of single-machine equipment in a narrow and long space, and has good vibration reduction effect and simple structure.
Description
Technical Field
The invention relates to the field of aircraft single-machine vibration damping mounting structures, in particular to a tandem type three-dimensional vibration damping single-machine equipment mounting device and an aircraft.
Background
The vibration of the internal single-machine equipment is caused by the vibration of the aircraft caused by the engine and aerodynamic force in flight, the vibration during transportation and other factors. The stand-alone equipment is divided according to the use, and is generally used as equipment for power supply, control, remote measurement, guidance and the like, and when the stand-alone equipment is used for power supply, the stand-alone equipment can be a battery; when used for control, a stand-alone device may be a controller or a computer; but when used for remote measurement, the stand-alone equipment can be a remote measurement synthesizer; when used for guidance, the stand-alone device may be a seeker.
Most of the stand-alone equipment cannot withstand strong vibration, and excessive vibration can cause the stand-alone equipment to work and fail. The vibration reduction design of single-machine equipment installation is a factor which must be considered when designing an aircraft, and the common vibration reduction technology at present achieves the purpose of vibration reduction by adding a damping structure. The vibration reduction structure mainly comprises a damping plate, a vibration absorber, a vibration reduction pad and the like, and has the function of unidirectional vibration reduction or three-dimensional vibration reduction.
The single-machine equipment independent vibration reduction is usually realized by adopting a vibration absorber, and the vibration absorber is designed by adopting a T-shaped rubber pad, so that the structure is simple, and the vibration reduction effect is good. However, the shock absorber has certain limitation, a single machine dynamic displacement space needs to be reserved for shock absorption installation, and the required structural space is large; for a single machine with large axial size and large mass, in order to avoid shaking and vibration amplification caused by longer cantilever of the single machine, vibration damping mounting structures are generally required to be designed at the front end and the rear end of the single machine, and the single machine has the defects of complex structure, large occupied space, high cost and poor assembly manufacturability; especially for narrow cabin section structures of aircrafts, under the space constraint, the vibration reduction installation of a plurality of single machines is realized at the same time, the layout difficulty is high, the assembly manufacturability of the designed structures is poor, and the space utilization is not ideal.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide the tandem type three-dimensional vibration reduction single-machine equipment installation device which can effectively solve the problem of assembly of single-machine equipment in a long and narrow space, has a good vibration reduction effect and a simple structure.
In order to achieve the above purposes, the technical scheme adopted by the invention is as follows:
a tandem three-dimensional vibration damped stand-alone equipment mounting apparatus comprising:
a deck section housing;
the first bracket group comprises a first bracket and a second bracket which are fixed on the cabin section shell, the first bracket and the second bracket are arranged at intervals, and the first bracket and the second bracket are used for fixing two ends of a single machine;
the first vibration damper group comprises a plurality of vibration dampers, and is used for fixing the single-machine equipment on the first bracket and damping the single-machine equipment;
the second support group comprises a third support and a fourth support which are fixed on the cabin section shell, the third support and the fourth support are arranged at intervals, and the third support and the fourth support are used for fixing two ends of a single machine; the second bracket group is connected with the first bracket group in series, and the third bracket is connected with the second bracket; and
and the second damper group comprises a plurality of dampers, and is used for fixing the single equipment on the third bracket and damping the single equipment.
On the basis of the above technical solution, the first damper group includes three dampers, the first bracket is provided with three assembly holes, and each damper in the first damper group includes:
the limiting screw is used for fixing the single machine equipment on the assembling hole;
the first vibration damping pad is arranged between the single machine equipment and the limiting screw;
a second vibration damping pad disposed between the stand-alone equipment and the first bracket;
the upper shield is arranged between the limiting screw and the first vibration damping pad and used for limiting the first vibration damping pad to move along the radial direction of the limiting screw;
the lower protective cover is arranged between the first support and the second damping pad and used for limiting the second damping pad to move along the radial direction of the limiting screw; and
and the bushing is sleeved on the limit screw and is positioned in the single machine equipment.
On the basis of the above technical solution, the second damper group includes three dampers, the third bracket is provided with three assembly holes, and each damper in the second damper group includes:
the limiting screw is used for fixing the single machine equipment on the assembling hole;
the first vibration damping pad is arranged between the single machine equipment and the limiting screw;
a second vibration damping pad disposed between the stand-alone equipment and the third bracket;
the upper shield is arranged between the limiting screw and the first vibration damping pad and used for limiting the first vibration damping pad to move along the radial direction of the limiting screw;
the lower protective cover is arranged between the third support and the second vibration damping pad and used for limiting the second vibration damping pad to move along the radial direction of the limiting screw; and
and the bushing is sleeved on the limit screw and is positioned in the single machine equipment.
On the basis of the technical proposal, the device comprises a shell,
the first support and the third support are provided with through holes for the single-machine equipment to penetrate through;
the second support and the fourth support are both provided with accommodating grooves for accommodating the end parts of the single-machine equipment, and damping cushions are arranged in the accommodating grooves of the second support and the fourth support.
Meanwhile, the invention also aims to provide the aircraft which can effectively solve the problem of the assembly of single equipment in a narrow and long space, and has good vibration damping effect and simple structure.
An aircraft, comprising:
a first stand-alone device and a second stand-alone device; and
a tandem type three-dimensional vibration damping single equipment installation device comprises,
-a cabin shell;
-a first bracket group comprising a first bracket and a second bracket fixed on the cabin shell, wherein the first bracket and the second bracket are arranged at intervals and used for fixing two ends of a first single-machine device;
-a first set of dampers comprising a plurality of dampers for fixing said first stand-alone equipment to said first support and damping said first stand-alone equipment;
a second bracket group, which comprises a third bracket and a fourth bracket fixed on the cabin shell, wherein the third bracket and the fourth bracket are arranged at intervals and used for fixing two ends of the second single-machine equipment; the second bracket group is connected with the first bracket group in series, and the third bracket is connected with the second bracket;
-a second set of dampers comprising a plurality of dampers, said second set of dampers being adapted to fix said second stand-alone equipment to said third support and damp said second stand-alone equipment.
On the basis of the technical scheme, the first support and the third support are both provided with through holes; and the second support and the fourth support are both provided with accommodating grooves.
On the basis of the technical scheme, the first stand-alone equipment and the second stand-alone equipment respectively comprise a front-end conical section and a rear-end flange section, and the front-end conical section of the first stand-alone equipment penetrates through the through hole of the first support and is accommodated in the accommodating groove of the second support; and the front-end conical section of the second stand-alone equipment penetrates through the through hole of the third support and is accommodated in the accommodating groove of the fourth support, and the rear-end flange section of the second stand-alone equipment is positioned between the second support and the third support.
On the basis of the above technical solution, the first damper group includes three dampers, the first bracket is provided with three assembly holes, and each damper in the first damper group includes:
the limiting screw penetrates through a rear end flange section of the first stand-alone equipment and an assembling hole of the first support;
the first vibration damping pad is arranged between the rear end flange section of the first stand-alone equipment and the limiting screw;
a second vibration damping pad disposed between the rear end flange section of the first stand-alone equipment and the first bracket;
the upper shield is arranged between the limiting screw and the first vibration damping pad and used for limiting the first vibration damping pad to move along the radial direction of the limiting screw;
the lower protective cover is arranged between the first support and the second damping pad and used for limiting the second damping pad to move along the radial direction of the limiting screw; and
and the bushing is sleeved on the limit screw and is positioned in the rear end flange section of the first stand-alone equipment.
On the basis of the above technical solution, the second damper group includes three dampers, the third bracket is provided with three assembly holes, and each damper in the second damper group includes:
the limiting screw penetrates through a rear end flange section of the second stand-alone equipment and an assembling hole of the third support;
the first vibration damping pad is arranged between the rear end flange section of the second single-machine equipment and the limiting screw;
a second vibration damping pad disposed between a rear end flange section of the second stand-alone equipment and a third bracket;
the upper shield is arranged between the limiting screw and the first vibration damping pad and used for limiting the first vibration damping pad to move along the radial direction of the limiting screw;
the lower protective cover is arranged between the third support and the second vibration damping pad and used for limiting the second vibration damping pad to move along the radial direction of the limiting screw; and
and the bushing is sleeved on the limit screw and is positioned in the rear end flange section of the first stand-alone equipment.
On the basis of the technical scheme, damping cushions are arranged in the containing grooves of the second support and the fourth support.
Compared with the prior art, the invention has the advantages that:
the tandem type three-dimensional vibration reduction single-machine equipment installation device comprises a first support group and a second support group, wherein the first support group and the second support group realize tandem type installation of 2 single-machine equipment, a vibration reduction function is realized by a vibration absorber and a damping pad, and a cabin section shell provides an installation space and an installation flange surface. The shock absorber and the damping pad which are prepared from silicon rubber materials jointly act to realize three-dimensional shock absorption of single-machine equipment, the problems of large-length cantilever shaking and vibration amplification of the single-machine equipment can be effectively solved, and a good shock absorption effect is realized by reasonably designing the first shock absorption pad, the second shock absorption pad and the damping pad; the multilayer support structure composed of 4 supports realizes the serial installation of 2 single-machine equipment, effectively solves the assembly of the 2 single-machine equipment in a long and narrow space, and has the advantages of good assembly manufacturability and compact structure.
Drawings
FIG. 1 is a perspective view of a tandem type three-dimensional vibration damping single-machine equipment installation apparatus according to an embodiment of the present invention;
FIG. 2 is a front view of a tandem three-dimensional vibration damping single-machine installation apparatus according to an embodiment of the present invention;
FIG. 3 is a cross-sectional view taken along the line A-A of FIG. 2;
FIG. 4 is an enlarged view of a portion I of FIG. 3;
FIG. 5 is an enlarged view of a portion II of FIG. 3;
FIG. 6 is a schematic structural diagram of a damping pad according to an embodiment of the present invention.
In the figure: 1-cabin shell, 11-flange face, 2-first support group, 21-first support, 22-second support, 3-second support group, 31-third support, 32-fourth support, 4-through hole, 5-accommodating groove, 6-first stand-alone equipment, 7-second stand-alone equipment, 8-vibration absorber, 81-limiting screw, 82-first vibration absorbing pad, 83-second vibration absorbing pad, 84-upper shield, 85-lower shield, 86-bushing and 9-damping pad.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and examples.
Referring to fig. 1 to 3, an embodiment of the present invention provides a tandem type three-dimensional vibration damping single-machine equipment installation apparatus, which includes a cabin shell 1, a first bracket group 2 and a second bracket group 3.
The first bracket group 2 comprises a first bracket 21 and a second bracket 22 which are fixed on the cabin shell 1, the first bracket 21 and the second bracket 22 are arranged at intervals, and the first bracket 21 and the second bracket 22 are used for fixing two ends of a single machine.
The second bracket group 3 comprises a third bracket 31 and a fourth bracket 32 which are fixed on the cabin shell 1 and are arranged at intervals, and the third bracket 31 and the fourth bracket 32 are used for fixing two ends of the single machine equipment; the second bracket set 3 is arranged in series with the first bracket set 2, and the third bracket 31 is connected with the second bracket 22.
Preferably, the present embodiment is provided with a plurality of flange surfaces 11 on the cabin shell 1, and the first bracket 21, the third bracket 31 and the fourth bracket 32 are fixed on the flange surfaces 11. Specifically, the cabin shell 1 is provided with 3 flange surfaces 11, and the first bracket 21, the third bracket 31 and the fourth bracket 32 are respectively connected with one of the flange surfaces 11.
Because third support 31 and second support 22 link to each other, third support 31 will fix on flange face 11 with second support 22, again because of second support group 3 and the 2 series connection settings of first support group, thereby 1 single-machine equipment respectively has 1 support to realize the installation by the front and back end, install on the support of 1 single-machine equipment rear end in addition through the support with 1 single-machine equipment front end, thereby realize the series connection installation of 2 single-machine equipment and its support, 3 flange faces 11 of rethread cabin section casing 1 are with 2 series connection single-machine equipment installations on the cabin section casing. The assembly of 2 single-machine equipment in a long and narrow space is effectively solved, and the device has the advantages of good assembly manufacturability and compact structure.
Referring to fig. 4, the first damper group in the present embodiment includes three dampers 8, the first bracket 21 is provided with three fitting holes, and each damper 8 in the first damper group includes:
a limit screw 81 for fixing the stand-alone equipment to the fitting hole;
a first vibration damping pad 82 provided between the stand-alone equipment and the limit screw 81;
a second vibration-damping pad 83 provided between the stand-alone equipment and the first bracket 21;
an upper shield 84 disposed between the limit screw 81 and the first damping pad 82, the upper shield 84 being configured to limit the first damping pad 82 from moving in a radial direction of the limit screw 81;
a lower shroud 85 disposed between the first bracket 21 and the second damping pad 83, the lower shroud 85 being configured to limit the second damping pad 83 from moving in a radial direction of the limit screw 81; and
and the bushing 86 is sleeved on the limiting screw 81 and is positioned in the single machine.
The second damper group in this embodiment includes three dampers 8, the third bracket 31 is provided with three fitting holes, and each damper 8 in the second damper group includes:
a limit screw 81 for fixing the stand-alone equipment to the fitting hole;
a first vibration damping pad 82 provided between the stand-alone equipment and the limit screw 81;
a second vibration-damping pad 83 provided between the stand-alone equipment and the third bracket 31;
an upper shield 84 disposed between the limit screw 81 and the first damping pad 82, the upper shield 84 being configured to limit the first damping pad 82 from moving in a radial direction of the limit screw 81;
a lower shield 85 disposed between the third bracket 31 and the second damping pad 83, the lower shield 85 being configured to limit the second damping pad 83 from moving in a radial direction of the limit screw 81; and
and the bushing 86 is sleeved on the limiting screw 81 and is positioned in the single machine.
Further, the first support 21 and the third support 31 are both provided with through holes 4 for the single machine equipment to penetrate through;
the second bracket 22 and the fourth bracket 32 are each provided with a receiving groove 5 for receiving an end of the stand-alone equipment. Referring to fig. 5 and 6, the damping pad 9 is disposed in each of the receiving grooves 5 of the second bracket 22 and the fourth bracket 32.
In this embodiment, a composite vibration damping technology of the vibration absorber 8 and the damping pad 9 is adopted, and the vibration absorbing function is mainly performed by the vibration absorber 8 and assisted by the damping pad 9. The three-dimensional vibration reduction of the large-length single machine is realized by installing 1 damping pad 9 at the front end of each single machine device and installing 3 vibration absorbers at the rear end. The vibration absorber 8 realizes three-dimensional vibration absorption of single-machine equipment, and the damping pad 9 realizes flexible auxiliary support and vibration absorption of a single machine.
The first vibration reduction pad 82, the second vibration reduction pad 83 and the bushing 86 are made of silicon rubber materials, and therefore the damping vibration reduction function is achieved. The upper shield 84, the lower shield 85 and the limit screws are made of stainless steel, the upper shield 84 and the lower shield 85 are designed with 1mm flanges, the first damping pads 82 and the second damping pads 83 are restrained in the radial direction, and the limit screws 81 are used for controlling the compression amount of the first damping pads 82 and the second damping pads 83 and installing single-machine equipment. The damping pad 9 is made of silicon rubber materials and is in a conical structure of a revolving body, and the damping pad 9 is provided with a plurality of round holes so as to reduce the rigidity and improve the vibration damping performance.
In the present embodiment, the compression ratio of the first and second vibration damping pads 82 and 83 is designed to be 10% to 12%, the compression ratio of the damping pad 9 is designed to be 5% to 8%, and the compression ratio of the bush 86 is not designed.
In summary, in this embodiment, the first bracket set 2 and the second bracket set 3 realize the tandem installation of 2 single devices, the vibration absorber 8 and the damping pad 9 realize the vibration absorbing function, and the cabin shell 1 provides the installation space and the installation flange surface. The shock absorber 8 and the damping pad 9 which are made of silicon rubber materials jointly act to realize three-dimensional shock absorption of single-machine equipment, the problems of large-length cantilever shaking and vibration amplification of the single-machine equipment can be effectively solved, and a good shock absorption effect is realized by reasonably designing the first shock absorption pad 82, the second shock absorption pad 83 and the damping pad 9; the multilayer support structure composed of 4 supports realizes the serial installation of 2 single-machine equipment, effectively solves the assembly of the 2 single-machine equipment in a long and narrow space, and has the advantages of good assembly manufacturability and compact structure.
Referring to fig. 1 to 6, an embodiment of the present invention further provides an aircraft including a tandem three-dimensional vibration damping stand-alone equipment installation device, a first stand-alone equipment 6, and a second stand-alone equipment 7.
Wherein, the tandem type three-dimensional vibration reduction single machine equipment installation device comprises,
a cabin shell 1;
a first bracket group 2 comprising a first bracket 21 and a second bracket 22 fixed on the cabin shell 1, wherein the first bracket 21 and the second bracket 22 are arranged at intervals, and the first bracket 21 and the second bracket 22 are used for fixing two ends of the first single-machine equipment 6;
a first set of dampers comprising a plurality of dampers 8 for fixing the first stand-alone equipment 6 to the first support 21 and damping the first stand-alone equipment 6;
a second bracket group 3, which comprises a third bracket 31 and a fourth bracket 32 fixed on the cabin shell 1, wherein the third bracket 31 and the fourth bracket 32 are arranged at intervals, and the third bracket 31 and the fourth bracket 32 are used for fixing two ends of the second single-machine equipment 7; the second bracket group 3 is connected with the first bracket group 2 in series, and the third bracket 31 is connected with the second bracket 22;
a second set of dampers comprising a plurality of dampers 8 for fixing the second stand-alone equipment 7 to the third support 31 and damping the second stand-alone equipment 7.
Preferably, the present embodiment is provided with a plurality of flange surfaces 11 on the cabin shell 1, and the first bracket 21, the third bracket 31 and the fourth bracket 32 are fixed on the flange surfaces 11. Specifically, the cabin shell 1 is provided with 3 flange surfaces 11, and the first bracket 21, the third bracket 31 and the fourth bracket 32 are respectively connected with one of the flange surfaces 11.
Because third support 31 and second support 22 link to each other, third support 31 will fix on flange face 11 with second support 22, again because of second support group 3 and the 2 series connection settings of first support group, thereby 1 single-machine equipment respectively has 1 support to realize the installation by the front and back end, install on the support of 1 single-machine equipment rear end in addition through the support with 1 single-machine equipment front end, thereby realize the series connection installation of 2 single-machine equipment and its support, 3 flange faces 11 of rethread cabin section casing 1 are with 2 series connection single-machine equipment installations on the cabin section casing. The assembly of 2 single-machine equipment in a long and narrow space is effectively solved, and the device has the advantages of good assembly manufacturability and compact structure.
Further, the first bracket 21 and the third bracket 31 are both provided with through holes 4; the second bracket 22 and the fourth bracket 32 are each provided with a housing groove 5.
Further, the first stand-alone equipment 6 and the second stand-alone equipment 7 both comprise a front-end conical section and a rear-end flange section, and the front-end conical section of the first stand-alone equipment 6 penetrates through the through hole of the first bracket 21 and is accommodated in the accommodating groove 5 of the second bracket 22; the front end conical section of the second stand-alone equipment 7 passes through the through hole 4 of the third bracket 31 and is accommodated in the accommodating groove 5 of the fourth bracket 32, and the rear end flange section of the second stand-alone equipment 7 is positioned between the second bracket 22 and the third bracket 31.
Further, the damping pad 9 is disposed in the storage groove 5 of each of the second bracket 22 and the fourth bracket 32.
Referring to the drawings, the first damper group in the present embodiment includes three dampers 8, the first bracket 21 is provided with three fitting holes, and each damper 8 in the first damper group includes:
a limit screw 81 which is inserted through the rear end flange section of the first stand-alone equipment 6 and the fitting hole of the first bracket 21;
a first vibration damping pad 82 provided between the rear end flange section of the first stand-alone equipment 6 and the limit screw 81;
a second vibration damping pad 83 provided between the rear end flange section of the first stand-alone equipment 6 and the first bracket 21;
an upper shield 84 disposed between the limit screw 81 and the first damping pad 82, the upper shield 84 being configured to limit the first damping pad 82 from moving in a radial direction of the limit screw 81;
a lower shroud 85 disposed between the first bracket 21 and the second damping pad 83, the lower shroud 85 being configured to limit the second damping pad 83 from moving in a radial direction of the limit screw 81; and
and a bushing 86 which is sleeved on the limit screw 81 and is positioned in the rear end flange section of the first single machine equipment 6.
Meanwhile, the second damper group in the present embodiment includes three dampers 8, the third bracket 31 is provided with three fitting holes, and each damper 8 in the second damper group includes:
a limit screw 81 which is inserted through the rear end flange section of the second stand-alone device 7 and the fitting hole of the third bracket 31;
a first vibration damping pad 82 provided between the rear end flange section of the second stand-alone equipment 7 and the limit screw 81;
a second vibration-damping pad 83 provided between the rear-end flange section of the second stand-alone equipment 7 and the third bracket 31;
an upper shield 84 disposed between the limit screw 81 and the first damping pad 82, the upper shield 84 being configured to limit the first damping pad 82 from moving in a radial direction of the limit screw 81;
a lower shield 85 disposed between the third bracket 31 and the second damping pad 83, the lower shield 85 being configured to limit the second damping pad 83 from moving in a radial direction of the limit screw 81; and
and a bushing 86 which is sleeved on the limit screw 81 and is positioned in the rear end flange section of the first single machine equipment 6.
In this embodiment, a composite vibration damping technology of the vibration absorber 8 and the damping pad 9 is adopted, and the vibration absorbing function is mainly performed by the vibration absorber 8 and assisted by the damping pad 9. The three-dimensional vibration reduction of the large-length single machine is realized by installing 1 damping pad 9 at the front end of each single machine device and installing 3 vibration absorbers at the rear end. The vibration absorber 8 realizes three-dimensional vibration absorption of single-machine equipment, and the damping pad 9 realizes flexible auxiliary support and vibration absorption of a single machine.
The first vibration reduction pad 82, the second vibration reduction pad 83 and the bushing 86 are made of silicon rubber materials, and therefore the damping vibration reduction function is achieved. The upper shield 84, the lower shield 85 and the limit screws are made of stainless steel, the upper shield 84 and the lower shield 85 are designed with 1mm flanges, the first damping pads 82 and the second damping pads 83 are restrained in the radial direction, and the limit screws 81 are used for controlling the compression amount of the first damping pads 82 and the second damping pads 83 and installing single-machine equipment. The damping pad 9 is made of silicon rubber materials and is in a conical structure of a revolving body, and the damping pad 9 is provided with a plurality of round holes so as to reduce the rigidity and improve the vibration damping performance.
In the present embodiment, the compression ratio of the first and second vibration damping pads 82 and 83 is designed to be 10% to 12%, the compression ratio of the damping pad 9 is designed to be 5% to 8%, and the compression ratio of the bush 86 is not designed.
In summary, in the aircraft of the present embodiment, the first bracket group 2 and the second bracket group 3 achieve the series installation of 2 single devices, the vibration absorber 8 and the damping pad 9 achieve the vibration absorbing function, and the cabin shell 1 provides the installation space and the installation flange surface. The shock absorber 8 and the damping pad 9 which are prepared from silicon rubber materials jointly act to realize three-dimensional shock absorption of single-machine equipment, the problems of large-length cantilever shaking and vibration amplification of the single-machine equipment can be effectively solved, and a first shock absorption pad 82, a second shock absorption pad 83 and the damping pad 9 are reasonably designed to realize a good shock absorption effect; the multilayer support structure composed of 4 supports realizes the serial installation of 2 single-machine equipment, effectively solves the assembly of 2 single-machine equipment in a long and narrow space in an aircraft, and has the advantages of good assembly manufacturability and compact structure.
The present invention is not limited to the above-described embodiments, and it will be apparent to those skilled in the art that various modifications and improvements can be made without departing from the principle of the present invention, and such modifications and improvements are also considered to be within the scope of the present invention. Those not described in detail in this specification are within the skill of the art.
Claims (6)
1. A tandem type three-dimensional vibration damping single-machine equipment installation device is characterized by comprising:
a cabin shell (1);
the first bracket group (2) comprises a first bracket (21) and a second bracket (22) which are fixed on the cabin shell (1), the first bracket (21) and the second bracket (22) are arranged at intervals, and the first bracket (21) and the second bracket (22) are used for fixing two ends of a first single machine device (6);
a first set of dampers comprising a plurality of dampers (8) for fixing the first stand-alone equipment (6) on the first support (21) and damping the first stand-alone equipment (6);
the second bracket group (3) comprises a third bracket (31) and a fourth bracket (32) which are fixed on the cabin shell (1), the third bracket (31) and the fourth bracket (32) are arranged at intervals, and the third bracket (31) and the fourth bracket (32) are used for fixing two ends of a second single machine device (7); the second bracket group (3) and the first bracket group (2) are arranged in series, and the third bracket (31) is connected with the second bracket (22); and
a second set of dampers comprising a plurality of dampers (8) for fixing the second stand-alone equipment (7) on the third support (31) and damping the second stand-alone equipment (7);
the first shock absorber group comprises three shock absorbers (8), the first bracket (21) is provided with three assembly holes, and each shock absorber (8) in the first shock absorber group comprises:
a limit screw (81) for fixing the first stand-alone equipment (6) to the fitting hole;
a first damping pad (82) disposed between the first stand-alone device (6) and the limit screw (81);
a second damping pad (83) disposed between the first stand-alone equipment (6) and the first bracket (21);
an upper shield (84) disposed between the limit screw (81) and a first damping pad (82), the upper shield (84) for limiting movement of the first damping pad (82) in a radial direction of the limit screw (81);
a lower shield (85) disposed between the first bracket (21) and a second damping pad (83), the lower shield (85) being configured to limit the second damping pad (83) from moving in a radial direction of the limit screw (81); and
the bushing (86) is sleeved on the limiting screw (81) and is positioned in the first single-machine equipment (6);
the second damper group comprises three dampers (8), the third bracket (31) is provided with three assembly holes, and each damper (8) in the second damper group comprises:
a limit screw (81) for fixing the second stand-alone device (7) to the fitting hole;
a first damping pad (82) disposed between the second stand-alone equipment (7) and the limit screw (81);
a second vibration-damping pad (83) provided between the second stand-alone equipment (7) and the third bracket (31);
an upper shield (84) disposed between the limit screw (81) and a first damping pad (82), the upper shield (84) for limiting movement of the first damping pad (82) in a radial direction of the limit screw (81);
a lower shield (85) disposed between the third bracket (31) and a second damping pad (83), the lower shield (85) being configured to limit the second damping pad (83) from moving in a radial direction of the limit screw (81); and
and the bushing (86) is sleeved on the limiting screw (81) and is positioned in the second single-machine equipment (7).
2. The tandem type three-dimensional vibration damping stand-alone equipment installation device according to claim 1, wherein:
the first support (21) and the third support (31) are provided with through holes (4) for single machine equipment to penetrate through;
the second support (22) and the fourth support (32) are provided with accommodating grooves (5) used for accommodating the end parts of the single-machine equipment, and damping pads (9) are arranged in the accommodating grooves (5) of the second support (22) and the fourth support (32).
3. An aircraft, characterized in that it comprises:
a first stand-alone device (6) and a second stand-alone device (7); and
a tandem type three-dimensional vibration damping single equipment installation device comprises,
-a cabin shell (1);
-a first bracket group (2) comprising a first bracket (21) and a second bracket (22) fixed on the cabin shell (1), and the first bracket (21) and the second bracket (22) are arranged at intervals, and the first bracket (21) and the second bracket (22) are used for fixing two ends of a first single machine (6);
-a first set of dampers comprising a plurality of dampers (8) for fixing said first stand-alone equipment (6) on said first support (21) and damping said first stand-alone equipment (6);
-a second group of brackets (3) comprising a third bracket (31) and a fourth bracket (32) fixed to the cabin shell (1), the third bracket (31) and the fourth bracket (32) being arranged at intervals, the third bracket (31) and the fourth bracket (32) being used for fixing two ends of the second stand-alone equipment (7); the second bracket group (3) and the first bracket group (2) are arranged in series, and the third bracket (31) is connected with the second bracket (22);
-a second set of dampers comprising a plurality of dampers (8) for fixing said second stand-alone equipment (7) on said third support (31) and damping said second stand-alone equipment (7);
the first stand-alone equipment (6) and the second stand-alone equipment (7) both comprise a front-end conical section and a rear-end flange section;
the first shock absorber group comprises three shock absorbers (8), the first bracket (21) is provided with three assembly holes, and each shock absorber (8) in the first shock absorber group comprises:
the limiting screw (81) is arranged on a rear end flange section of the first stand-alone equipment (6) and an assembling hole of the first bracket (21) in a penetrating mode;
a first vibration damping pad (82) provided between a rear end flange section of the first stand-alone equipment (6) and a limit screw (81);
a second vibration-damping pad (83) provided between a rear-end flange section of the first stand-alone equipment (6) and the first bracket (21);
an upper shield (84) disposed between the limit screw (81) and a first damping pad (82), the upper shield (84) for limiting movement of the first damping pad (82) in a radial direction of the limit screw (81);
a lower shield (85) disposed between the first bracket (21) and a second damping pad (83), the lower shield (85) being configured to limit the second damping pad (83) from moving in a radial direction of the limit screw (81); and
the bushing (86) is sleeved on the limiting screw (81) and is positioned in the rear end flange section of the first single-machine equipment (6);
the second damper group comprises three dampers (8), the third bracket (31) is provided with three assembly holes, and each damper (8) in the second damper group comprises:
the limiting screws (81) are arranged on the rear end flange section of the second single-machine equipment (7) and the assembly holes of the third bracket (31) in a penetrating mode;
a first vibration damping pad (82) provided between a rear end flange section of the second stand-alone equipment (7) and a limit screw (81);
a second vibration-damping pad (83) provided between a rear-end flange section of the second stand-alone equipment (7) and the third bracket (31);
an upper shield (84) disposed between the limit screw (81) and a first damping pad (82), the upper shield (84) for limiting movement of the first damping pad (82) in a radial direction of the limit screw (81);
a lower shield (85) disposed between the third bracket (31) and a second damping pad (83), the lower shield (85) being configured to limit the second damping pad (83) from moving in a radial direction of the limit screw (81); and
and the bushing (86) is sleeved on the limiting screw (81) and is positioned in the rear end flange section of the first single-machine equipment (6).
4. The aircraft of claim 3, wherein: the first support (21) and the third support (31) are both provided with through holes (4); and the second bracket (22) and the fourth bracket (32) are both provided with accommodating grooves (5).
5. The aircraft of claim 4, wherein: the front end conical section of the first stand-alone equipment (6) penetrates through the through hole of the first support (21) and is accommodated in the accommodating groove (5) of the second support (22); the front end conical section of the second stand-alone equipment (7) penetrates through the through hole (4) of the third support (31) and is contained in the containing groove (5) of the fourth support (32), and the rear end flange section of the second stand-alone equipment (7) is located between the second support (22) and the third support (31).
6. The aircraft of claim 4, wherein: damping cushions (9) are arranged in the containing grooves (5) of the second support (22) and the fourth support (32).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811253145.7A CN109268446B (en) | 2018-10-25 | 2018-10-25 | Tandem type three-dimensional vibration reduction single-machine equipment installation device and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811253145.7A CN109268446B (en) | 2018-10-25 | 2018-10-25 | Tandem type three-dimensional vibration reduction single-machine equipment installation device and aircraft |
Publications (2)
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| CN109268446A CN109268446A (en) | 2019-01-25 |
| CN109268446B true CN109268446B (en) | 2020-08-18 |
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| CN201811253145.7A Active CN109268446B (en) | 2018-10-25 | 2018-10-25 | Tandem type three-dimensional vibration reduction single-machine equipment installation device and aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114198456A (en) * | 2021-11-16 | 2022-03-18 | 北京卫星制造厂有限公司 | Vibration damper |
| CN114673762A (en) * | 2022-03-28 | 2022-06-28 | 宁波天擎航天科技有限公司 | Shock absorber of single machine for arrow |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
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| DE4340316C2 (en) * | 1993-11-26 | 1996-03-21 | Daimler Benz Aerospace Airbus | Arrangement for cooling food in an aircraft |
| JPH08239100A (en) * | 1995-03-03 | 1996-09-17 | Yamaha Motor Co Ltd | Support structure of loaded equipment for unmanned helicopter |
| CN1193588A (en) * | 1997-09-11 | 1998-09-23 | 朱天赉 | Aerodynamical apparatus drived by mechanical energy |
| FR2962176B1 (en) * | 2010-07-01 | 2012-07-13 | Turbomeca | DYNAMIC DAMPING METHOD FOR A POWER SHAFT, ESPECIALLY A SURFACE TREE, AND DAMPING ARCHITECTURE FOR IMPLEMENTING THE SAME |
| CN103115100B (en) * | 2013-02-06 | 2015-09-23 | 航天材料及工艺研究所 | A kind of combined rubber vibration damper |
| CN204692419U (en) * | 2015-04-08 | 2015-10-07 | 深圳市大疆创新科技有限公司 | Shock bracket and apply the flight equipment of this shock bracket |
| CN105757164A (en) * | 2016-04-08 | 2016-07-13 | 北京航天计量测试技术研究所 | Vibration reducing mechanism suitable for infrared camera on aircraft |
| CN205937612U (en) * | 2016-08-15 | 2017-02-08 | 中国航空工业集团公司沈阳发动机设计研究所 | Vibration -control system |
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