CN112607037B - Aircraft engine suspension device - Google Patents
Aircraft engine suspension device Download PDFInfo
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- CN112607037B CN112607037B CN202011491195.6A CN202011491195A CN112607037B CN 112607037 B CN112607037 B CN 112607037B CN 202011491195 A CN202011491195 A CN 202011491195A CN 112607037 B CN112607037 B CN 112607037B
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- 239000000725 suspension Substances 0.000 title claims abstract description 29
- 230000001141 propulsive effect Effects 0.000 claims abstract description 13
- 230000000694 effects Effects 0.000 claims abstract description 11
- 238000009434 installation Methods 0.000 claims abstract description 4
- 230000008093 supporting effect Effects 0.000 claims description 45
- 229910001220 stainless steel Inorganic materials 0.000 claims description 19
- 239000010935 stainless steel Substances 0.000 claims description 19
- 230000003139 buffering effect Effects 0.000 abstract description 13
- 238000000034 method Methods 0.000 abstract description 4
- 238000010521 absorption reaction Methods 0.000 abstract description 3
- 230000001737 promoting effect Effects 0.000 abstract description 2
- 230000000712 assembly Effects 0.000 abstract 1
- 238000000429 assembly Methods 0.000 abstract 1
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000000523 sample Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
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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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
- B64D27/404—Suspension arrangements specially adapted for supporting vertical loads
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The invention discloses an engine suspension device which comprises a wing, wherein suspension assemblies are arranged on the fixing frame and the outer side of an engine. This aircraft engine linkage including the side connecting rod of two horizontal joint's absorption propulsive force, can play horizontal buffering absorption to the propulsive force of engine, the symmetry setting of accessible homonymy slide cartridge and slide bar, make suspension assembly its motion process more steady when horizontal atress, stability when further promoting the buffering, promote the practicality of use, the accessible kelly links to each other with the joint of draw-in groove, and the setting of second spring, make mount and mounting groove can realize quick assembly disassembly, and then promote engine dismouting efficiency, reduce the dismouting degree of difficulty, and then save operating time, and through the setting of first bolt and voussoir, can play the locking effect to the kelly, guarantee the installation steadiness of mount and mounting groove.
Description
Technical Field
The invention relates to the technical field of aircraft engine suspension devices, in particular to an aircraft engine suspension device comprising two transversely-jointed side connecting rods for absorbing propulsive force.
Background
The aircraft is an apparatus flying in the atmosphere or the space outside the atmosphere, and the aircraft is divided into 3 types: aircrafts, spacecrafts, rockets and missiles, which fly in the atmosphere and are called aircrafts such as balloons, airships, airplanes and the like, fly by means of the static buoyancy of air or the aerodynamic force generated by the relative motion of air. Flying in space is called a spacecraft, such as an artificial earth satellite, a manned spacecraft, a space probe, a space shuttle and the like. They are propelled by a launch vehicle to obtain the necessary velocity to enter space and then rely on inertia to make an orbital motion similar to a celestial body, often requiring the use of suspension devices when installed from aircraft engines.
Aircraft engine linkage including the side connecting rod of two horizontal joint's absorption propulsive forces among the prior art, it is not good to play horizontal buffering absorbing effect to the propulsive force of engine, can't reduce its resilience simultaneously, further influence horizontal buffering effect, and it is not steady enough to hang its motion process of subassembly when horizontal atress, stability when further influencing the buffering, reduce the practicality of use, it is inefficient to the engine dismouting simultaneously, the dismouting degree of difficulty is big, and then extension operating time, and can't guarantee the installation steadiness, and can't play the effect of holding to the engine, make its unexpected dislocation easily, reduce flight safety, and then inconvenient people use.
Disclosure of Invention
The invention aims to provide an aircraft engine suspension device comprising two transversely-jointed side connecting rods for absorbing the propulsive force, and aims to solve the problems that the aircraft engine suspension device comprising the two transversely-jointed side connecting rods for absorbing the propulsive force in the prior art in the background art has poor transverse buffering and absorbing effects on the propulsive force of an engine, cannot reduce the rebound of the engine, further influences the transverse buffering effect, has unstable motion process of a suspension assembly when transversely stressed, further influences the stability during buffering, and reduces the use practicability.
In order to achieve the purpose, the invention provides the following technical scheme: the aircraft engine suspension device comprises two transversely-jointed side connecting rods for absorbing propulsive force, and comprises wings, wherein a mounting groove is mounted at the bottom of each wing, a fixing frame is arranged at the inner wall of the mounting groove in a clearance fit manner, an engine is arranged below the fixing frame, a sliding block is fixedly connected to the top of the engine, and the outer wall of the sliding block is connected with the sliding block at the top of the inner wall of the fixing frame in a sliding manner through a sliding groove.
Preferably, the fixed frame and the outer side of the engine are provided with a suspension assembly;
the suspension assembly comprises a support plate, a slide rod, a slide cylinder, a first spring, a support and a rubber roller;
the supporting plate is fixedly connected to the left side and the right side of the inner wall of the fixing frame, the inner end of the supporting plate is rotatably connected with a sliding rod, the outer wall of the sliding rod is in clearance fit with a sliding barrel, the inner ends of the sliding barrels are movably connected with the upper side and the lower side of the left side and the right side of an engine respectively, a first spring is sleeved on the outer wall of the sliding rod, two ends of the first spring are fixedly connected with the sliding rod and the sliding barrel respectively, a plurality of supports are fixedly connected to the inner end of the sliding rod, rubber rollers are rotatably connected to the inner ends of the supports through one-way bearings, and the outer wall of each rubber roller is tightly abutted to the inner wall of the corresponding sliding barrel.
Preferably, support and rubber roll are annular equidistance and distribute, and the outer wall shape of rubber roll agrees with mutually with the inner wall of slide cartridge.
Preferably, a clamping component is arranged between the mounting groove and the fixing frame;
the clamping component comprises a clamping rod, a clamping groove, a clamping plate, a second spring, a first bolt, a wedge block and a through hole;
the outer wall of kelly and the inner wall clearance fit of through-hole, the through-hole is processed in the left and right sides of mounting groove, the inboard of kelly is equipped with the draw-in groove, the draw-in groove is processed in both ends about the mount, the inner wall of draw-in groove and the inner joint of kelly, the outer wall outside of kelly is equipped with the cardboard, the inner wall of cardboard and the outer wall fixed connection of kelly, the inboard of cardboard is equipped with the second spring, the second spring cup joints in the outer wall of kelly, the inner of second spring respectively with both ends fixed connection about the mounting groove, the outer end of second spring and the inner fixed connection of cardboard, the inside outside of kelly is equipped with first bolt, the outer wall of first bolt and the inside outside threaded connection of kelly, the top of first bolt is equipped with the voussoir, the scarf of voussoir offsets tightly with the top of first bolt, the top of voussoir and the bottom fixed connection of wing.
Preferably, the wedge is disposed corresponding to a position of the first bolt.
Preferably, a supporting component is arranged below the fixing frame;
the supporting assembly comprises a second bolt, a stainless steel supporting rod and an arc-shaped supporting plate;
the inner side of the stainless steel supporting rod is provided with an arc-shaped supporting plate, the outer end of the arc-shaped supporting plate is fixedly connected with the inner end of the stainless steel supporting rod, the inner end of the arc-shaped supporting plate is attached to the bottom of the engine, and the outer side of the stainless steel supporting rod is fixedly connected with the left side and the right side of the bottom of the fixing frame through second bolts.
Preferably, the radian of the inner end of the arc-shaped supporting plate is consistent with that of the outer wall of the engine and is a smooth arc surface.
Compared with the prior art, the invention has the beneficial effects that: the aircraft engine suspension device comprises two transversely-jointed side connecting rods for absorbing propulsive force, and is characterized in that the wing, the mounting groove, the fixing frame, the engine, the sliding block, the sliding chute and the suspension assembly are matched, so that when the device is used, the propelling force of the engine can be transversely buffered and absorbed through clearance fit of the sliding cylinder and the sliding rod and arrangement of the first spring, and meanwhile, through arrangement of the one-way bearing, the rubber roller can rub against the inner wall of the sliding cylinder when the first spring rebounds, so that rebounding is reduced, and the transverse buffering effect of the rubber roller is further improved;
by matching the wings, the mounting groove, the fixing frame, the engine, the sliding block, the sliding groove and the suspension assembly, when the device is used, the suspension assembly can move more stably under transverse stress through symmetrical arrangement of the sliding cylinder and the sliding rod on the same side, so that the stability during buffering is further improved, and the use practicability is improved;
through the matching of the wings, the mounting groove, the fixing frame, the engine, the sliding block, the sliding groove and the clamping component, when the device is used, the fixing frame and the mounting groove can be quickly disassembled and assembled through the clamping connection of the clamping rod and the clamping groove, and the arrangement of the second spring, so that the disassembling and assembling efficiency of the engine is improved, the disassembling and assembling difficulty is reduced, the working time is saved, and through the arrangement of the first bolt and the wedge block, the clamping rod can be tightly locked, and the mounting stability of the fixing frame and the mounting groove is ensured;
through wing, mounting groove, mount, engine, slider, spout and the cooperation of holding the subassembly for the device is when using, the setting of accessible arc layer board to and stainless steel branch passes through second bolt fixed connection with the mount, and accessible arc layer board plays the support effect to the engine, avoids its unexpected dislocation, promotes the flight security, and then makes things convenient for people to use.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic structural view of the stainless steel strut, the arc-shaped support plate and the engine of FIG. 1;
FIG. 3 is a schematic diagram of the structure of the engine, the sliding cylinder and the sliding rod in FIG. 1;
FIG. 4 is a schematic structural view of the clamping rod, the clamping groove and the first bolt in FIG. 1;
FIG. 5 is a schematic structural view of the slide cylinder, the slide rod and the first spring of FIG. 2;
fig. 6 is a schematic structural view of the slide cylinder, the slide rod and the first spring in fig. 3.
In the figure: 1. the device comprises a wing, 2, a mounting groove, 3, a fixed frame, 4, an engine, 5, a sliding block, 6, a sliding groove, 7, a suspension component, 701, a support plate, 702, a sliding rod, 703, a sliding cylinder, 704, a first spring, 705, a support, 706, a rubber roller, 8, a clamping component, 801, a clamping rod, 802, a clamping groove, 803, a clamping plate, 804, a second spring, 805, a first bolt, 806, a wedge block, 807, a through hole, 9, a supporting component, 901, a second bolt, 902, a stainless steel support rod, 903 and an arc-shaped supporting plate.
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.
Referring to fig. 1-6, the present invention provides a technical solution: the aircraft engine suspension device comprises two transversely-jointed side connecting rods for absorbing propulsive force, and comprises a wing 1, wherein a mounting groove 2 is installed at the bottom of the wing 1, a fixing frame 3 is arranged at the inner wall clearance fit of the mounting groove 2, an engine 4 is arranged below the fixing frame 3, a sliding block 5 is fixedly connected to the top of the engine 4, the outer wall of the sliding block 5 is in sliding clamping connection with the top of the inner wall of the fixing frame 3 through a sliding groove 6, the sliding groove 6 enables the sliding block 5 to drive the engine 4 to slide in a small range, and a suspension assembly 7 is arranged on the outer sides of the fixing frame 3 and the engine 4.
The suspension assembly 7 comprises a support plate 701, a sliding rod 702, a sliding barrel 703, a first spring 704, a support 705 and a rubber roller 706, the support plate 701 is fixedly connected to the left side and the right side of the inner wall of the fixed frame 3, the inner end of the support plate 701 is rotatably connected with the sliding rod 702, the sliding barrel 703 is in clearance fit with the outer wall of the sliding rod 702, the sliding barrel 703 enables the sliding rod 702 to stretch and retract under stress, the inner ends of the two sliding barrels 703 on the same side are respectively movably connected with the upper side and the lower side of the left side and the right side of the engine 4, the first spring 704 is sleeved on the outer wall of the sliding rod 702, two ends of the first spring 704 are respectively and fixedly connected with the sliding rod 702 and the sliding barrel 703, the first spring 704 gives a restoring force to the sliding rod 702 after stretching, the inner end of the sliding rod 702 is fixedly connected with the plurality of supports 705, the inner ends of the supports are rotatably connected with the rubber roller 706 through one-way bearings, the supports 705 and the rubber roller 706 are distributed in an annular equidistant manner, and the outer wall of the rubber roller 706 is matched with the inner wall of the sliding barrel 703, so that the rubber roller 706 is designed to be more uniform when the rubber roller 703 in friction;
through the matching of the wings, the mounting groove, the fixing frame, the engine, the sliding block, the sliding groove and the suspension assembly, when the device is used, the sliding cylinder is in clearance fit with the sliding rod, the first spring is arranged, the transverse buffering and absorbing effect on the propelling force of the engine can be achieved, and meanwhile through the arrangement of the one-way bearing, the rubber roller can be in friction with the inner wall of the sliding cylinder when the first spring rebounds, so that the rebounding is reduced, and the transverse buffering effect of the rubber roller is further improved;
make the device when using, the symmetry setting of accessible homonymy slide cartridge and slide bar for its motion process is more steady when horizontal atress of suspension assembly, stability when further promoting the buffering promotes the practicality of use.
A clamping component 8 is arranged between the mounting groove 2 and the fixing frame 3, the clamping component 8 comprises a clamping rod 801, a clamping groove 802, clamping plates 803, a second spring 804, a first bolt 805, a wedge block 806 and a through hole 807, the outer wall of the clamping rod 801 is in clearance fit with the inner wall of the through hole 807, the through hole 807 is processed at the left side and the right side of the mounting groove 2, the inner side of the clamping rod 801 is provided with the clamping groove 802, the clamping groove 802 is processed at the left end and the right end of the fixing frame 3, the inner wall of the clamping groove 802 is clamped with the inner end of the clamping rod 801, the clamping rod 801 and the clamping groove 802 are arranged to fix the fixing frame 3, the outer side of the outer wall of the clamping rod 801 is provided with the clamping plates 803, the inner wall of the clamping plates 803 is fixedly connected with the outer wall of the clamping rod 801, the inner side of the clamping plates 803 is provided with the second spring 804, the second spring 804 is sleeved on the outer wall of the clamping rod 801, the inner end of the second spring 804 is fixedly connected with the left end and the right end of the mounting groove 2 respectively, the outer end of the second spring 804 is fixedly connected with the inner end of the clamping plate 803, the second spring 804 provides inward force for the clamping rod 801, a first bolt 805 is arranged on the outer side of the inner part of the clamping rod 801, the outer wall of the first bolt 805 is in threaded connection with the outer side of the inner part of the clamping rod 801, a wedge block 806 is arranged at the top of the first bolt 805, the wedge block 806 is arranged corresponding to the position of the first bolt 805, and by the design, when the clamping rod 801 is tightly abutted with the clamping groove 802, the first bolt 805 can be tightly abutted with the inclined plane of the wedge block 806 by rotating, the wedge surface of the wedge block 806 is tightly abutted with the top of the first bolt, and the top of the wedge block 806 is fixedly connected with the bottom of the wing 1;
through the wing, the mounting groove, the mount, the engine, the slider, the cooperation of spout and screens subassembly, make the device when using, the joint of accessible kelly and draw-in groove links to each other, and the setting of second spring, make mount and mounting groove can realize quick assembly disassembly, and then promote engine dismouting efficiency, reduce the dismouting degree of difficulty, and then save operating time, and through the setting of first bolt and voussoir, can play the locking effect to the kelly, guarantee the installation steadiness of mount and mounting groove.
A supporting component 9 is arranged below the fixed frame 3, the supporting component 9 comprises a second bolt 901, a stainless steel supporting rod 902 and an arc supporting plate 903, the arc supporting plate 903 is arranged on the inner side of the stainless steel supporting rod 902, the outer end of the arc supporting plate 903 is fixedly connected with the inner end of the stainless steel supporting rod 902, the radian of the inner end of the arc supporting plate 903 is consistent with that of the outer wall of the engine 4 and is a smooth arc surface, the anti-dislocation effect on the engine 4 can be achieved due to the design, the inner end of the arc supporting plate 903 is attached to the bottom of the engine 4, the outer side of the stainless steel supporting rod 902 is fixedly connected with the left side and the right side of the bottom of the fixed frame 3 through the second bolt 901, and the second bolt 901 plays a mounting role on the stainless steel supporting rod 902;
through wing, mounting groove, mount, engine, slider, spout and the cooperation of holding the subassembly for the device is when using, the setting of accessible arc layer board to and stainless steel branch passes through second bolt fixed connection with the mount, and accessible arc layer board plays the support effect to the engine, avoids its unexpected dislocation, promotes the flight security, and then makes things convenient for people to use.
In this embodiment, when the aircraft engine suspension device including two transversely-jointed side links for absorbing thrust is used, the fixing frame 3 is firstly inserted into the mounting groove 2, the inward force is applied to the clamping rod 801 through the second spring 804, so that the clamping rod 801 can be embedded into the clamping groove 802, and further a quick mounting effect is achieved on the fixing frame 3 and the engine 4, and meanwhile, the first bolt 805 is rotated to abut against the wedge surface of the wedge 806, so that the fixing frame 3 can be fastened with the mounting groove 2, when the engine is started, the rubber roller 706 can rotate when the sliding rod 702 is inserted into the sliding cylinder 703, and rubs against the inner wall of the sliding cylinder 703 when sliding out, so as to weaken springback, greatly improve starting stability, and reduce the influence of the thrust on an engine mounting structure, and meanwhile, through the arrangement of the second bolt 901, the arc-shaped supporting plate 903 can be driven by the stainless steel supporting rod 902 to be placed below the engine 4, and further a supporting effect on the engine 4 is achieved, and convenience is achieved for people.
In the description of the present invention, it is to be understood that the terms "coaxial", "bottom", "one end", "top", "middle", "other end", "upper", "one side", "top", "inner", "front", "center", "both ends", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention.
In the present invention, unless otherwise explicitly stated or limited, the terms "mounted," "disposed," "connected," "fixed," "screwed" and the like are to be understood broadly, for example, as being fixedly connected, detachably connected, or integrated; can be mechanically or electrically connected; the terms may be directly connected or indirectly connected through an intermediate, and may be communication between two elements or interaction relationship between two elements, unless otherwise specifically limited, and the specific meaning of the terms in the present invention will be understood by those skilled in the art according to specific situations.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (2)
1. Aircraft engine suspension device, including wing (1), its characterized in that: the wing structure is characterized in that a mounting groove (2) is mounted at the bottom of the wing (1), a fixing frame (3) is in clearance fit with the inner wall of the mounting groove (2), an engine (4) is arranged below the fixing frame (3), a sliding block (5) is fixedly connected to the top of the engine (4), and the outer wall of the sliding block (5) is in sliding clamping connection with the top of the inner wall of the fixing frame (3) through a sliding groove (6);
a suspension component (7) is arranged on the outer sides of the fixed frame (3) and the engine (4);
the suspension assembly (7) comprises a support plate (701), a sliding rod (702), a sliding cylinder (703), a first spring (704), a bracket (705) and a rubber roller (706);
the supporting plate (701) is fixedly connected to the left side and the right side of the inner wall of the fixing frame (3), the inner end of the supporting plate (701) is rotatably connected with a sliding rod (702), the outer wall of the sliding rod (702) is in clearance fit with sliding cylinders (703), the inner ends of the two sliding cylinders (703) on the same side are respectively movably connected with the upper side and the lower side of the left side and the right side of the engine (4), the outer wall of the sliding rod (702) is sleeved with a first spring (704), the two ends of the first spring (704) are respectively fixedly connected with the sliding rod (702) and the sliding cylinders (703), the inner end of the sliding rod (702) is fixedly connected with a plurality of supports (705), the inner end of each support (705) is rotatably connected with a rubber roller (706) through a one-way bearing, and the outer wall of each rubber roller (706) is abutted against the inner wall of each sliding cylinder (703);
the support (705) and the rubber roller (706) are distributed in an annular and equidistant mode, and the shape of the outer wall of the rubber roller (706) is matched with the inner wall of the sliding cylinder (703);
a clamping component (8) is arranged between the mounting groove (2) and the fixing frame (3);
the clamping component (8) comprises a clamping rod (801), a clamping groove (802), a clamping plate (803), a second spring (804), a first bolt (805), a wedge block (806) and a through hole (807);
the outer wall of the clamping rod (801) is in clearance fit with the inner wall of a through hole (807), the through hole (807) is processed on the left side and the right side of the mounting groove (2), a clamping groove (802) is arranged on the inner side of the clamping rod (801), the clamping groove (802) is processed on the left end and the right end of the fixing frame (3), the inner wall of the clamping groove (802) is clamped with the inner end of the clamping rod (801), a clamping plate (803) is arranged on the outer side of the outer wall of the clamping rod (801), the inner wall of the clamping plate (803) is fixedly connected with the outer wall of the clamping rod (801), a second spring (804) is arranged on the inner side of the clamping plate (803), the second spring (804) is sleeved on the outer wall of the clamping rod (801), the inner end of the second spring (804) is fixedly connected with the left end and the right end of the mounting groove (2), the outer end of the second spring (804) is fixedly connected with the inner end of the clamping plate (803), a first bolt (805) is arranged on the outer side of the inner side of the clamping rod (801), a first bolt (805) is connected with the outer wall of the clamping rod (801), the outer side of the clamping rod (805), a top of the first bolt (806) is tightly connected with the top of the wedge (806), and the top of the wedge (806);
the wedge block (806) is arranged corresponding to the position of the first bolt (805);
a supporting component (9) is arranged below the fixing frame (3);
the supporting assembly (9) comprises a second bolt (901), a stainless steel supporting rod (902) and an arc-shaped supporting plate (903);
an arc-shaped supporting plate (903) is arranged on the inner side of the stainless steel supporting rod (902), the outer end of the arc-shaped supporting plate (903) is fixedly connected with the inner end of the stainless steel supporting rod (902), the inner end of the arc-shaped supporting plate (903) is attached to the bottom of the engine (4), and the outer side of the stainless steel supporting rod (902) is fixedly connected with the left side and the right side of the bottom of the fixing frame (3) through second bolts (901);
firstly, insert mounting bracket (3) in mounting groove (2), give kelly (801) inward power through second spring (804), make kelly (801) can inlay in draw-in groove (802), and then play quick installation effect to mounting bracket (3) and engine (4), the wedge surface of rotating first bolt (805) and voussoir (806) supports tightly simultaneously, can make mounting bracket (3) and mounting groove (2) fasten, when the engine starts, through the clearance fit of slide cartridge (703) and slide bar (702), and the setting of first spring (704), can transversely absorb its propulsive force, and simultaneously, through the setting of one-way bearing, make rubber roller (706) rotatable when slide bar (702) inserts slide cartridge (703), rub with slide cartridge (703) inner wall during the roll-off, and then weaken resilience, promote the start stability greatly, reduce its propulsive force to the influence of engine mounting structure, and simultaneously, through the setting of second bolt (901), accessible stainless steel branch (902) is arranged in and then is played the engine supporting plate (903) and is held conveniently, it is used, it is convenient to hold in the engine (4) below.
2. The aircraft engine suspension arrangement of claim 1, wherein: the radian of the inner end of the arc-shaped supporting plate (903) is consistent with that of the outer wall of the engine (4), and the arc-shaped supporting plate is a smooth arc surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011491195.6A CN112607037B (en) | 2020-12-17 | 2020-12-17 | Aircraft engine suspension device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011491195.6A CN112607037B (en) | 2020-12-17 | 2020-12-17 | Aircraft engine suspension device |
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| Publication Number | Publication Date |
|---|---|
| CN112607037A CN112607037A (en) | 2021-04-06 |
| CN112607037B true CN112607037B (en) | 2022-10-14 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011491195.6A Active CN112607037B (en) | 2020-12-17 | 2020-12-17 | Aircraft engine suspension device |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2939409B1 (en) * | 2008-12-08 | 2011-02-11 | Airbus France | FIXING SYSTEM BETWEEN TWO COMPONENTS SUCH AS AN AIRCRAFT ENGINE AND ITS ATTACHING MACHINE |
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|---|---|---|---|---|
| US3006587A (en) * | 1956-11-12 | 1961-10-31 | Snecma | Suspension device for jet propulsion units |
| JPH11310199A (en) * | 1998-04-28 | 1999-11-09 | Hiroyoshi Mori | Helicopter |
| CN107380460A (en) * | 2016-03-15 | 2017-11-24 | 空中客车运营简化股份公司 | Engine pack and aircraft for aircraft |
| CN206275299U (en) * | 2016-12-21 | 2017-06-27 | 嘉兴兴发箱包有限公司 | A kind of novel multi-use case and bag |
| CN109209677A (en) * | 2017-06-29 | 2019-01-15 | 空中客车运营简化股份公司 | Turbofan and aircraft |
| CN206929306U (en) * | 2017-07-20 | 2018-01-26 | 俞鉴卿 | A kind of double-track cam for feeding machine |
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