CN110844090A - Supporting type mounting device of piston engine of helicopter - Google Patents
Supporting type mounting device of piston engine of helicopter Download PDFInfo
- Publication number
- CN110844090A CN110844090A CN201910965668.2A CN201910965668A CN110844090A CN 110844090 A CN110844090 A CN 110844090A CN 201910965668 A CN201910965668 A CN 201910965668A CN 110844090 A CN110844090 A CN 110844090A
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- Prior art keywords
- mounting
- shock absorber
- engine
- helicopter
- piston engine
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- 230000035939 shock Effects 0.000 claims abstract description 95
- 239000006096 absorbing agent Substances 0.000 claims abstract description 62
- 238000009434 installation Methods 0.000 claims abstract description 21
- 230000005484 gravity Effects 0.000 claims abstract description 5
- 230000006835 compression Effects 0.000 claims description 5
- 238000007906 compression Methods 0.000 claims description 5
- 238000006073 displacement reaction Methods 0.000 abstract description 8
- 238000010586 diagram Methods 0.000 description 4
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/04—Aircraft characterised by the type or position of power plant of piston type
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- B64D27/40—
Abstract
The embodiment of the invention provides a supporting type mounting device of a piston engine of a helicopter, which comprises: an upper mounting assembly, a main mounting assembly and a bottom mounting assembly; the upper mounting assembly includes: one end of the upper shock absorber and one end of the upper connecting rod are connected to one end of the upper shock absorber, and the other end of the upper shock absorber and the other end of the upper connecting rod are provided with a first mounting hole and a first fastener; the main installation component comprises: the main installation component comprises: the main mounting assembly is mounted on the structural cross beam through the main shock absorber and fixed at the gravity center position of the engine; the bottom mounting assembly includes: the bottom support, the bumper shock absorber casing, third mounting hole and third fastener. The embodiment of the invention solves the problem that the conventional installation mode of the existing piston engine is difficult to meet the requirement that the output shaft can have a certain amount of vertical up-and-down displacement or the coplanarity of the engine and the belt pulley is difficult to adjust.
Description
Technical Field
The present application relates to, but is not limited to, the technical field of aircraft installation, and particularly, to a pop-up type mounting device for a piston engine of a helicopter.
Background
The piston engine of the helicopter not only needs to meet the requirement of the power of the helicopter, but also needs to meet the requirements of installation and vibration isolation of the piston engine on the helicopter. The choice of piston engine installation will affect engine performance, system weight, vibration, noise, and serviceability, etc. Designing a lightweight, reliable mounting system is one of the primary goals of engine mounting design.
The general installation mode of the piston engine can meet the requirements of general installation. However, the piston engine is often mounted on a helicopter by adopting belt pulley transmission, which requires that the output shaft of the engine has a certain amount of vertical up-and-down displacement function and the coplanarity of the engine and the belt pulley needs to be adjusted. However, it is generally difficult to meet the requirement that the output shaft can have a certain amount of vertical up-and-down displacement or to adjust the coplanarity of the engine and the pulley in the conventional installation.
Disclosure of Invention
The purpose of the invention is as follows: the embodiment of the invention provides a supporting type mounting device of a piston engine of a helicopter, which aims to solve the problem that the conventional mounting mode of the piston engine is difficult to meet the requirement that an output shaft can have a certain amount of vertical up-and-down displacement or to adjust the coplanarity of the engine and a belt pulley.
The technical scheme of the invention is as follows:
the embodiment of the invention provides a supporting type mounting device of a piston engine of a helicopter, which comprises: an upper mounting assembly, a main mounting assembly and a bottom mounting assembly;
the upper mounting assembly includes: the connecting rod comprises an upper shock absorber and an upper connecting rod, wherein one end of the upper connecting rod is connected to one end of the upper shock absorber, and the other end of the upper connecting rod is provided with a first mounting hole and a first fastener matched with the first mounting hole;
the main mounting assembly includes: the main mounting assembly is mounted on a structural beam through the main shock absorber, and the second fastener is inserted into the corresponding second mounting hole to fix the main mounting assembly at the gravity center position of the piston engine;
the bottom mounting assembly comprises: the bottom support, weld in the bumper shock absorber casing of bottom support bottom, and set up in third mounting hole on the bottom support, with the third fastener that the third mounting hole one-to-one set up, the bottom installation subassembly is fixed with fuselage structure through running through the screw rod and the bumper shock absorber connecting rod of bumper shock absorber casing, the third fastener inserts in the third mounting hole rather than corresponding, will the bottom installation subassembly is fixed in piston engine's bottom position.
Alternatively, in the above-described lift-off type mounting apparatus for a piston engine of a helicopter, the upper connecting rod is configured to adjust a front-rear position of the engine by adjusting a fixing position of a nut on the upper connecting rod.
Optionally, in the above-mentioned lift-off mounting device for a piston engine of a helicopter, two cylindrical shock-absorbing pads are arranged in the upper shock absorber, and the two cylindrical shock-absorbing pads are used for clamping a structural wall between the shock-absorbing pads to prevent the engine from moving back and forth.
Optionally, in the above-mentioned lift-up mounting device for a piston engine of a helicopter, a joint bearing is disposed in the first mounting hole of the upper connecting rod, and is connected to the engine, and is configured to tilt the upper bracket and drive the front portion of the engine to move vertically within a preset range through rotation of the joint bearing and compression deformation of the upper shock absorber.
Optionally, in the above-described lift-up mounting device for a helicopter piston engine, the second mounting hole includes two mounting through holes, and the second fastening member is a bolt disposed in one-to-one correspondence with the second mounting through hole; alternatively, the first and second electrodes may be,
the second mounting hole is a straight-line-shaped mounting through hole, so that the front and back relative positions of the engine and the main mounting assembly are changed within the range limited by the straight-line-shaped mounting through hole.
Optionally, in the above-described lift-up type mounting device for a piston engine of a helicopter, the two ends of the main body bracket are respectively provided with a shock absorber mounting hole, the main body shock absorber includes a first shock pad located above the shock absorber mounting hole, a second shock pad and a third shock pad located below the shock absorber mounting hole, the rod body on the upper portion of the second shock pad passes through the shock absorber mounting hole and is embedded into the first shock pad, and the second shock pad and the third shock pad are used for clamping the structural beam between the two shock pads to prevent the engine from moving back and forth.
Alternatively, in the above-mentioned lift-up mounting device for a piston engine of a helicopter, the main mounting assembly is configured to tilt and move the front portion of the engine vertically within a predetermined range by compressive deformation of the shock absorber.
Optionally, in the above supporting-type mounting device for a helicopter piston engine, the bottom bracket is a V-shaped bracket, an intersection of the V-shaped bracket and the damper housing is welded and fixed, and the two ends of the V-shaped bracket, which are not welded to the damper housing, are respectively provided with the third mounting holes;
the V-shaped bracket is configured to penetrate through the limit of the screw rod of the shock absorber shell and the shock absorber connecting rod, and the torsion of the engine is prevented.
Optionally, in the above-mentioned lift-up type mounting device for a piston engine of a helicopter, one end of the connecting rod connected to the body structure is provided with a knuckle bearing, and the knuckle bearing is configured to rotate so as to enable the bottom bracket to tilt and drive the upper bracket to vertically move within a preset range.
The invention has the beneficial effects that: the embodiment of the invention provides a supporting type mounting device of a helicopter piston engine, which comprises: the upper portion installation component, main installation component and bottom installation component should hold up formula installation device promptly and constitute by the installing support of three different functions, and structural design is light, easily realizes. In addition, the supporting type mounting device can reliably fix the engine on the helicopter, so that the engine can provide stable power output, the function of enabling the output shaft of the engine to have a certain amount of vertical up-and-down displacement can be realized, and the coplanarity of the engine and the belt pulley can be adjusted.
Drawings
FIG. 1 is a schematic structural diagram of a cradle mount assembly for a helicopter piston engine according to an embodiment of the present invention;
FIG. 2 is a schematic structural view of an upper mounting assembly of the lift-off mounting arrangement of the helicopter piston engine of FIG. 1;
FIG. 3 is a schematic structural view of one of the primary mounting assemblies of the lift-off mounting arrangement of the helicopter piston engine of FIG. 1;
FIG. 4 is a schematic structural view of one of the bottom mount assemblies of the lift-off mount arrangement of the helicopter piston engine of FIG. 1;
FIG. 5 is a schematic view of an upper shock absorber of a lift-off mounting arrangement for a helicopter piston engine according to an embodiment of the present invention;
fig. 6 is a schematic structural diagram of a main damper in a lift-off mounting device of a piston engine of a helicopter according to an embodiment of the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Fig. 1 is a schematic structural diagram of a lift-off mounting device of a piston engine of a helicopter according to an embodiment of the present invention, and the lift-off mounting device of a piston engine of a helicopter according to an embodiment of the present invention may include: an upper mounting assembly 1, a main mounting assembly 3 and a bottom mounting assembly 2.
Fig. 2 is a schematic view of an upper mounting assembly of the lift-off mounting device of the piston engine of the helicopter shown in fig. 1, fig. 3 is a schematic view of a main mounting assembly of the lift-off mounting device of the piston engine of the helicopter shown in fig. 1, and fig. 4 is a schematic view of a bottom mounting assembly of the lift-off mounting device of the piston engine of the helicopter shown in fig. 1.
As can be seen in fig. 2, the upper mounting assembly 1 may comprise: the shock absorber 9 and the upper connecting rod 10, one end of the upper connecting rod 10 is connected to one end of the upper shock absorber 9, the other end of the upper connecting rod 10 is provided with a first mounting hole, and a first fastening piece 12 matched with the first mounting hole.
As can be seen in fig. 3, the main mounting assembly 3 may comprise: the main part support 14 with set up respectively in the main part bumper shock absorber 13 at main part support 14 both ends, be provided with the second mounting hole on the main part support 14 to and the second fastener 15 that sets up with the second mounting hole one-to-one, main installation component 3 is installed on the structure crossbeam through main part bumper shock absorber 13, second fastener 15 inserts in the second mounting hole rather than corresponding, fixes 3 the centre of gravity position at piston engine with main installation component.
As can be seen in fig. 4, the bottom mounting assembly 2 may comprise: bottom support 6 welds in the bumper shock absorber casing 5 of bottom support 6 bottom to and set up the third mounting hole on bottom support 6, with third fastener 4 that the third mounting hole one-to-one set up, bottom installation component 2 is fixed with the fuselage structure through the screw rod and the bumper shock absorber connecting rod 7 that run through bumper shock absorber casing 5, third fastener 4 inserts in the third mounting hole rather than corresponding, fixes bottom installation component 2 in piston engine's bottom position.
The supporting type mounting device of the helicopter piston engine provided by the embodiment of the invention consists of three mounting brackets with different functions, and has the advantages of light structural design and easiness in implementation. In addition, the supporting type mounting device can reliably fix the engine on the helicopter, so that the engine can provide stable power output, the function of enabling the output shaft of the engine to have a certain amount of vertical up-and-down displacement can be realized, and the coplanarity of the engine and the belt pulley can be adjusted.
As shown in fig. 2, in the upper mount assembly 1, the upper connecting rod 10 is configured to adjust the front-rear position of the engine by adjusting the fixing position of the nut on the upper connecting rod 10.
Referring to fig. 5, there is shown a schematic structural view of an upper shock absorber in a lift-off type mounting device for a helicopter piston engine according to an embodiment of the present invention, wherein two cylindrical shock absorbing pads, such as shock absorbing pads 29 and 30 in fig. 5, are disposed in the upper shock absorber 9, the two cylindrical shock absorbing pads have a through hole at the center for passing through a connecting screw 27, and the two cylindrical shock absorbing pads are respectively provided with a mounting plate 28 and a fastening member 31 at both ends. The two cylindrical shock absorbing pads are used for clamping the structural wall between the shock absorbing pads to prevent the engine from moving forwards and backwards.
In addition, a joint bearing 11 is disposed in the first mounting hole of the upper connecting rod 10, and is connected to the engine, and is configured to tilt the upper bracket 10 and move the front portion of the engine vertically within a preset range by the rotation of the joint bearing 11 and the compression deformation of the upper damper 9.
The upper bracket component 1 of the embodiment of the invention is arranged at the upper part of an engine (see figure 1), an upper connecting rod 10 is fixed with the engine through a fastener 12, and is fixed with a fuselage structure through an upper shock absorber 9, so that the fore-and-aft displacement of the engine is prevented, and the radial expansion of the engine is absorbed. Wherein, the upper connecting rod 10 is provided with a joint bearing 11 at one end connected with the engine, and the front part of the engine is allowed to move up and down by a certain amount through the compression deformation of the upper shock absorber 9. The engine and structural vibrations are isolated by the upper shock absorber 9.
Fig. 3 shows a schematic structural diagram of a main damper in a main mounting assembly 3, as shown in fig. 6, in a lift-off mounting device of a helicopter piston engine according to an embodiment of the present invention. The both ends of main part support 14 are provided with the bumper shock absorber mounting hole respectively, main part bumper shock absorber 13 is including the first shock pad 23 that is located bumper shock absorber mounting hole top, be located second shock pad 25 and third shock pad 26 of bumper shock absorber mounting hole below, the body of rod on second shock pad 25 upper portion passes the bumper shock absorber mounting hole to in the first shock pad 23 of embedding, second shock pad 25 and third shock pad 26 are used for with the structure crossbeam clamping between two shock pads, prevent the engine back-and-forth movement. In fig. 6, the fastener 21 is used to pass through the mounting plate 22 and the shock absorbing pad, and the body bracket 24 in fig. 6 is the body bracket 14 in fig. 3.
In addition, the main mounting assembly 3 in the embodiment of the present invention is configured to tilt the main mounting assembly 3 by the compressive deformation of the damper 13 and move the front portion of the engine vertically within a preset range.
The main mounting component 3 of the embodiment of the invention is arranged near the center of gravity of the engine, the main body bracket 14 is fixed with the engine through the fastener 5, then the structural supporting plate is clamped through the main body shock absorber 13 and is supported on the body structure, and the influence of vertical up-and-down certain displacement at the front part of the engine can be absorbed through the main body shock absorber 13. The body bracket 14 is provided with a slotted hole to allow the engine to be adjusted fore and aft to change the co-planarity of the engine and the pulley. The engine and structure vibrations are isolated by the body damper 13.
Optionally, the second mounting hole in the embodiment of the present invention includes two mounting through holes, and the second fastening member is a bolt disposed in one-to-one correspondence to the second mounting through hole.
Optionally, the second mounting hole in the embodiment of the present invention is a straight-line mounting through hole, so that the front-rear relative position of the engine and the main mounting assembly varies within a range defined by the straight-line mounting through hole.
As shown in fig. 4, in the bottom mounting assembly 2, the bottom bracket 6 is a V-shaped bracket, the intersection point of the V-shaped bracket is welded and fixed with the damper housing 5, and the two ends of the V-shaped bracket, which are not welded with the damper housing, are respectively provided with a third mounting hole;
the V-shaped bracket is configured to prevent the engine from twisting by being restricted by a screw penetrating the damper housing 5 and the damper connecting rod 7.
In addition, the end of the shock absorber connecting rod 7 connected with the machine body structure is provided with a joint bearing, and the joint bearing is configured to rotate through the joint bearing 8, so that the bottom bracket 6 can be tilted, and the upper bracket 10 can be driven to vertically move within a preset range.
According to the bottom mounting assembly 2 provided by the embodiment of the invention, the bottom support 6 is fixed with the engine through the fastener 4 at the lower part of the engine, and is fixed with the machine body structure through the connecting rod 7 to offset the torsional force generated by the engine. Wherein, the connecting rod 7 is provided with a joint bearing 8 at one end connected with the structure, and the engine is allowed to move up and down by a certain amount through the compression deformation of the shock absorber. The vibration of the engine and the structure is isolated by the shock absorber.
The foregoing is merely a detailed description of the embodiments of the present invention, and some of the conventional techniques are not detailed. The scope of the present invention is not limited thereto, and any changes or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (9)
1. A pop-up mounting device for a helicopter piston engine comprising: an upper mounting assembly, a main mounting assembly and a bottom mounting assembly;
the upper mounting assembly includes: the connecting rod comprises an upper shock absorber and an upper connecting rod, wherein one end of the upper connecting rod is connected to one end of the upper shock absorber, and the other end of the upper connecting rod is provided with a first mounting hole and a first fastener matched with the first mounting hole;
the main mounting assembly includes: the main mounting assembly is mounted on a structural beam through the main shock absorber, and the second fastener is inserted into the corresponding second mounting hole to fix the main mounting assembly at the gravity center position of the piston engine;
the bottom mounting assembly comprises: the bottom support, weld in the bumper shock absorber casing of bottom support bottom, and set up in third mounting hole on the bottom support, with the third fastener that the third mounting hole one-to-one set up, the bottom installation subassembly is fixed with fuselage structure through running through the screw rod and the bumper shock absorber connecting rod of bumper shock absorber casing, the third fastener inserts in the third mounting hole rather than corresponding, will the bottom installation subassembly is fixed in piston engine's bottom position.
2. A lift-off mounting arrangement for a helicopter piston engine as claimed in claim 1 wherein said upper connecting rod is configured to adjust the fore-aft position of the engine by adjusting the attachment position of a nut on the upper connecting rod.
3. A piston engine prop mounting arrangement according to claim 2, wherein two cylindrical shock absorbing pads are provided in the upper shock absorber for clamping a structural wall between the shock absorbing pads to prevent fore and aft movement of the engine.
4. The lift-off mounting arrangement for a helicopter piston engine of claim 2 wherein said upper link has a knuckle bearing disposed within said first mounting hole and connected to the engine and configured to allow said upper bracket to tilt and move said engine front portion vertically within a predetermined range by rotation of said knuckle bearing and compression deformation of said upper shock absorber.
5. A lift-off mounting arrangement for a helicopter piston engine as defined in claim 1 wherein said second mounting hole comprises two mounting through holes and said second fastener is a bolt disposed in one-to-one correspondence with said second mounting through holes; alternatively, the first and second electrodes may be,
the second mounting hole is a straight-line-shaped mounting through hole, so that the front and back relative positions of the engine and the main mounting assembly are changed within the range limited by the straight-line-shaped mounting through hole.
6. A lift-off mounting arrangement for a helicopter piston engine as defined in claim 1 wherein said body bracket has shock absorber mounting holes formed in each of its ends, said body shock absorber includes a first shock pad positioned above said shock absorber mounting holes, a second shock pad and a third shock pad positioned below said shock absorber mounting holes, said second shock pad having an upper rod body passing through said shock absorber mounting holes and being embedded in said first shock pad, said second shock pad and said third shock pad being adapted to clamp a structural beam between said shock pads to prevent fore and aft movement of the engine.
7. A lift-off mounting arrangement for a helicopter piston engine according to claim 6 wherein said main mounting assembly is configured such that upon compressive deformation of the shock absorber, the main mounting assembly tilts and moves the front of the engine vertically within a predetermined range.
8. The lift-off mounting device for a helicopter piston engine of claim 1 wherein said bottom bracket is a V-shaped bracket, the intersection of said V-shaped bracket is welded to said shock absorber housing, and said third mounting holes are respectively disposed at two ends of said V-shaped bracket which are not welded to said shock absorber housing;
the V-shaped bracket is configured to penetrate through the limit of the screw rod of the shock absorber shell and the shock absorber connecting rod, and the torsion of the engine is prevented.
9. A prop-up mounting arrangement for a helicopter piston engine according to claim 8 wherein the end of said connecting rod that is attached to the airframe structure is provided with a knuckle bearing that is configured to allow rotation of said knuckle bearing to tilt said bottom bracket and move said upper bracket vertically within a predetermined range.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910965668.2A CN110844090B (en) | 2019-10-11 | 2019-10-11 | Supporting type mounting device of piston engine of helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910965668.2A CN110844090B (en) | 2019-10-11 | 2019-10-11 | Supporting type mounting device of piston engine of helicopter |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110844090A true CN110844090A (en) | 2020-02-28 |
| CN110844090B CN110844090B (en) | 2022-11-22 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910965668.2A Active CN110844090B (en) | 2019-10-11 | 2019-10-11 | Supporting type mounting device of piston engine of helicopter |
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| CN110844090B (en) | 2022-11-22 |
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