CN111746805B

CN111746805B - Novel aircraft engine installing support

Info

Publication number: CN111746805B
Application number: CN202010437593.3A
Authority: CN
Inventors: 霍甜; 肖明; 曾晓康; 张文祺; 符徐庆
Original assignee: Zhuoer Aircraft Manufacturing Wuhan Co ltd
Current assignee: Zhuoer Aircraft Manufacturing Wuhan Co ltd
Priority date: 2020-05-21
Filing date: 2020-05-21
Publication date: 2022-02-18
Anticipated expiration: 2040-05-21
Also published as: CN111746805A

Abstract

The invention belongs to the technical field of aircraft equipment installation and discloses a novel aircraft engine installation support. This novel aircraft engine installing support, including installing the base at aircraft nose, positioning mechanism has been installed in the front of base, and supporting mechanism has still been installed in the front of base, has seted up the oil pocket in the base, the screw with the oil pocket intercommunication is seted up to the pedestal roof, and screw female connection has the pressure regulating bolt. This novel aircraft engine installing support adopts the disconnect-type structure to carry out the engine installation, compares with prior art, has avoidd the potential safety hazard that a large amount of welded structure brought, and the firm of engine installation can be ensured on the one hand in frame construction's design simultaneously, and on the other hand provides the protection for the engine, and the installing structure of disconnect-type is also of value to the maintenance that changes the installing support simultaneously, and the part is easily changed, compares in the integral type structure greatly reduced maintenance cost of prior art installing support.

Description

Novel aircraft engine installing support

Technical Field

The invention relates to the technical field of aircraft equipment installation, in particular to a novel aircraft engine installation support.

Background

At present, civil aviation fixed wing aircraft at home and abroad develops more and more rapidly, the aircraft is of a great variety, people also pursue the travelling comfort that is similar to jet-propelled aircraft and brings more and more, however aircraft engine installing support's development is still standing a standstill, installing support adopts ironware welding to form usually among the prior art, this kind of installing support weight is great on the one hand, on the other hand welded structure has also brought potential safety hazard, can produce a large amount of vibrations along with the function of engine, traditional rigid structure receives vibrations to influence great, and vibrations transmission has also brought the hindrance for the travelling comfort promotion of flight to the cockpit.

Disclosure of Invention

The invention aims to provide a novel aircraft engine mounting bracket, which provides a more excellent damping structure, eliminates potential safety hazards caused by vibration of a welding structure and greatly improves driving comfort.

In order to achieve the purpose, the invention is realized by the following technical scheme: the utility model provides a novel aircraft engine installing support, is including installing the base at the aircraft nose, positioning mechanism has been installed in the front of base, and supporting mechanism has still been installed in the front of base, has seted up the oil pocket in the base, the screw with the oil pocket intercommunication is seted up to the pedestal roof, and screw female connection has the pressure regulating bolt.

Preferably, the positioning mechanism comprises four angle steels, mounting holes, an annular groove, sealing washers, a positioning rod and a positioning disc, wherein the four angle steels are fixedly connected to the front surface of the base and are arranged in a matrix manner, the four mounting holes are formed in the front surface of the base, are communicated with the oil cavity and are positioned on the inner sides of the four angle steels, the annular groove is formed in the inner wall of the mounting hole, the sealing washers are arranged in the annular groove and are contacted with the side wall of the annular groove, the positioning rod is inserted in the mounting holes, the positioning disc is arranged on the positioning rod and corresponds to the annular groove, and the positioning disk is pegged graft in the ring channel and contacts with seal ring, utilizes the locating lever of inserting in the oil intracavity to transmit the vibrations that the engine operation is produced, utilizes the hydraulic oil of oil intracavity to cushion vibrations, filters vibrations, weakens vibrations, reduces the engine vibrations and to the influence that fixed wing aircraft cockpit brought, improves pilot's travelling comfort.

Preferably, four the angle steel is adjacent between through connecting rod fixed connection, and the connecting rod is located the angle steel and keeps away from one side of base, and the connecting rod is used for aircraft engine's assistance-localization real-time, can strengthen the structural strength of whole installing support simultaneously.

Preferably, four support mechanisms are arranged on the front surface of the base, the four support mechanisms and four angle steels are arranged in a staggered manner, each support mechanism comprises four arc-shaped support plates, support fins and a hydraulic pipe, the four arc-shaped support plates are sequentially arranged and connected through a hinge structure, the arc-shaped support plates on two sides are respectively hinged with the front surface of the base and a connecting rod, strip-shaped holes are formed in the middle of each arc-shaped support plate, the hydraulic pipe is arranged on the front surface of the base and communicated with the oil cavity, the hydraulic pipe is inserted into the four strip-shaped holes, the hydraulic pipe is used as a framework of the support mechanism, when the pressure regulating bolt is screwed down, the pressure in the oil cavity is increased, the hydraulic pipe is supported to keep the shape of the support structure, the arc-shaped support plates on the support structure are used for fixing the engine, the elasticity of the hydraulic pipe is used for absorbing the vibration of the engine, and the four support fins are respectively fixed on two side edges of the two arc-shaped support plates in the middle, the side face of the engine is coated by the structure of the supporting wing piece, and the arc-shaped elastic structure of the engine is used for absorbing vibration.

Preferably, the hydraulic pipe is arc-shaped and is bent towards the center of the base, arc-shaped wrinkles are arranged on one side of the hydraulic pipe close to the middle of the base and between two adjacent arc-shaped supporting plates at equal intervals, the circle center of each arc-shaped wrinkle is overlapped with the axis of the hydraulic pipe, and the arrangement of the arc-shaped wrinkles enables the hydraulic pipe to be complete towards the center of the base when the hydraulic oil pressure in the hydraulic pipe is improved, so that the support for the engine is enhanced.

Preferably, the supporting wing pieces are metal mesh rubber pieces, the supporting wing pieces are bent towards the center direction of the base, the side faces of the engine are coated by the structures of the supporting wing pieces, and the arc-shaped elastic structures of the supporting wing pieces are used for absorbing vibration.

Preferably, the oil cavity and the inside of hydraulic pressure pipe are all filled with hydraulic oil, and the one end that the base was kept away from to the hydraulic pressure pipe is for sealing the form, has all seted up the locating hole on four angle steels, and the inboard of four angle steels all bonds and has had rubber protection pad.

This novel aircraft engine installing support during operation installs the aircraft engine into between four angle steels, utilizes four locating levers to insert the location that the engine was realized to the location screw on the engine, cooperates the locating hole simultaneously and utilizes the bolt fastening engine, rotates pressure regulating bolt regulation oil pocket internal pressure, makes the hydraulic pressure pipe prop up, and the arc backup pad is pressed in four sides of engine, accomplishes the installation, when engine work produces vibrations, is provided by supporting mechanism and the interior hydraulic oil of oil pocket and strains the shock attenuation.

By adopting the technical scheme, the invention has the beneficial effects that:

1. this novel aircraft engine installing support adopts the disconnect-type structure to carry out the engine installation, compares with prior art, has avoidd the potential safety hazard that a large amount of welded structure brought, and the firm of engine installation can be ensured on the one hand in frame construction's design simultaneously, and on the other hand provides the protection for the engine, and the installing structure of disconnect-type is also of value to the maintenance that changes the installing support simultaneously, and the part is easily changed, compares in the integral type structure greatly reduced maintenance cost of prior art installing support.

2. This novel aircraft engine installing support utilizes the design of supporting mechanism and base inner oil pocket, can the efficient absorb the vibrations that the engine function produced, blocks vibrations to the transmission of aircraft cockpit, great improvement the driving experience of driver, improve the travelling comfort that the fixed wing aircraft was taken, utilize the mobility of hydraulic oil to strengthen supporting mechanism's reliability, but quick reset has solved the problem of proposing in the background art.

Drawings

FIG. 1 is a schematic structural view of the present invention;

FIG. 2 is a front view of the present invention;

FIG. 3 is a cross-sectional view taken along line A-A of FIG. 2 in accordance with the present invention;

FIG. 4 is an enlarged view taken at A of FIG. 3 in accordance with the present invention;

FIG. 5 is a cross-sectional view taken along line B-B of FIG. 2 in accordance with the present invention;

FIG. 6 is an enlarged view taken at B of FIG. 5 in accordance with the present invention;

fig. 7 is a cross-sectional view of the oil cavity in the base of the present invention.

In the figure: the device comprises a base 1, a positioning mechanism 2, angle steel 21, a mounting hole 22, an annular groove 23, a sealing washer 24, a positioning rod 25, a positioning disc 26, a supporting mechanism 3, an arc-shaped supporting plate 31, a supporting wing 32, a hydraulic pipe 33, an oil cavity 4, a screw hole 5, a pressure regulating bolt 6, a connecting rod 7, an strip-shaped hole 8, an arc-shaped fold 9, a positioning hole 10 and a rubber protection pad 11.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with 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, rather than all embodiments, and all other embodiments obtained by a person of ordinary skill in the art without creative efforts based on the embodiments of the present invention belong to the protection scope of the present invention.

Referring to fig. 1-7, the present invention provides a technical solution: the utility model provides a novel aircraft engine installing support, is including installing base 1 at the aircraft nose, and positioning mechanism 2 has been installed in base 1's front, and supporting mechanism 3 has still been installed in base 1's front, has seted up oil pocket 4 in the base 1, and screw 5 with 4 intercommunications in oil pocket is seted up to base 1 roof, and 5 female connection in screw have pressure regulating bolt 6.

Positioning mechanism 2 includes four angle steel 21, mounting hole 22, ring channel 23, seal ring 24, locating lever 25 and positioning disk 26, four equal fixed connection of angle steel 21 just are the matrix arrangement in base 1's front, four mounting holes 22 are seted up and are communicate and be located four angle steel 21 inboards in base 1 front and oil pocket 4, ring channel 23 is seted up the inner wall at mounting hole 22, seal ring 24 sets up at ring channel 23 inside and with the contact of ring channel 23 lateral wall, the locating lever 25 is pegged graft in mounting hole 22, positioning disk 26 sets up the position that corresponds ring channel 23 on locating lever 25, and positioning disk 26 pegs graft in ring channel 23 and contact with seal ring 24.

The four angle steels 21 are fixedly connected with each other through the connecting rod 7, and the connecting rod 7 is positioned on one side of the angle steel 21 far away from the base 1.

Four supporting mechanism 3 set up at base 1 openly, and four supporting mechanism 3 and four crisscross arrangements of angle steel 21, supporting mechanism 3 includes four arc backup pad 31, support fin 32 and hydraulic pressure pipe 33, four arc backup pad 31 are arranged in proper order and are connected through hinge structure formation, and the arc backup pad 31 that is located both sides forms articulatedly with base 1 openly and connecting rod 7 respectively, bar hole 8 has all been seted up at four arc backup pad 31 middle parts, hydraulic pressure pipe 33 is installed at base 1 openly and is communicate with 4 in the oil pocket, and hydraulic pressure pipe 33 alternates in four bar holes 8, four support fin 32 are fixed respectively on two arc backup pad 31 both sides limits that are located in the middle of being located.

The hydraulic pipe 33 is arc-shaped and is bent towards the center of the base 1, the hydraulic pipe 33 is close to one side of the middle part of the base 1 and is provided with arc-shaped wrinkles 9 arranged at equal intervals between two adjacent arc-shaped supporting plates 31, and the circle center of the arc-shaped wrinkles 9 is superposed with the axle center of the hydraulic pipe 33.

The supporting fins 32 are made of metal mesh rubber, and the supporting fins 32 are bent toward the center of the base 1.

The inside of oil pocket 4 and hydraulic pressure pipe 33 all is filled with hydraulic oil, and the one end that base 1 was kept away from to hydraulic pressure pipe 33 is for sealing the form, has all seted up locating hole 10 on four angle steel 21, and the inboard of four angle steel 21 all bonds and has rubber protection pad 11.

In summary, the novel aircraft engine mounting bracket adopts the separated structure to mount the engine, compared with the prior art, potential safety hazards caused by a large number of welding structures are avoided, meanwhile, the design of the frame structure can ensure the firmness of the engine mounting on one hand and provide protection for the engine on the other hand, meanwhile, the separated mounting structure is also beneficial to the maintenance of the mounting bracket, parts are easy to replace, and the maintenance cost is greatly reduced compared with the integrated structure of the mounting bracket in the prior art; by means of the design of the supporting mechanism 3 and the oil cavity 4 in the base 1, vibration generated by the operation of the engine can be efficiently absorbed, the transmission of the vibration to an aircraft cockpit is blocked, the driving experience of a driver is greatly improved, the comfort of taking a fixed-wing aircraft is improved, the reliability of the supporting mechanism 3 is enhanced by the aid of the liquidity of hydraulic oil, the supporting mechanism can be reset quickly, and the problem of the background technology is solved.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that 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

1. The utility model provides a novel aircraft engine installing support, is including installing base (1) at aircraft nose, its characterized in that: the front surface of the base (1) is provided with a positioning mechanism (2), the front surface of the base (1) is also provided with a supporting mechanism (3), an oil cavity (4) is formed in the base (1), the top wall of the base (1) is provided with a screw hole (5) communicated with the oil cavity (4), the screw hole (5) is connected with a pressure regulating bolt (6) in a threaded manner, the positioning mechanism (2) comprises four angle steels (21), mounting holes (22), annular grooves (23), sealing washers (24), positioning rods (25) and positioning discs (26), the four angle steels (21) are all fixedly connected to the front surface of the base (1) and are arranged in a matrix manner, the four mounting holes (22) are formed in the front surface of the base (1) and communicated with the oil cavity (4) and are positioned at the inner sides of the four angle steels (21), the annular grooves (23) are formed in the inner walls of the mounting holes (22), the sealing washers (24) are arranged in the annular grooves (23) and are in contact with the side walls of the annular grooves (23), the locating rod (25) is inserted in the mounting hole (22), the locating disc (26) is arranged on the locating rod (25) and corresponds to the position of the annular groove (23), and the locating disc (26) is inserted in the annular groove (23) and is in contact with the sealing washer (24).

2. A novel aircraft engine mounting bracket according to claim 1, wherein: four angle steel (21) are adjacent to each other through connecting rod (7) fixed connection, and connecting rod (7) are located angle steel (21) and keep away from one side of base (1).

3. A novel aircraft engine mounting bracket according to claim 1, wherein: four supporting mechanism (3) set up openly in base (1), and four supporting mechanism (3) and four angle steel (21) crisscross arrangement, supporting mechanism (3) include four arc backup pads (31), support fin (32) and hydraulic pressure pipe (33), and four arc backup pads (31) are arranged in proper order and are connected through hinge structure formation, and arc backup pad (31) that are located both sides form articulatedly with base (1) front and connecting rod (7) respectively, and bar hole (8) have all been seted up at four arc backup pads (31) middle parts, and hydraulic pressure pipe (33) are installed and are openly and communicate with oil pocket (4) in base (1), and hydraulic pressure pipe (33) alternate in four bar holes (8), and four support fin (32) are fixed respectively and are located two arc backup pad (31) both sides limit in the middle of being located.

4. A novel aircraft engine mounting bracket according to claim 3, wherein: the hydraulic pipe (33) is arc-shaped and is bent towards the center of the base (1), the hydraulic pipe (33) is close to one side of the middle part of the base (1) and is positioned between two adjacent arc-shaped supporting plates (31) to form arc-shaped wrinkles (9) which are arranged equidistantly, and the circle center of each arc-shaped wrinkle (9) is superposed with the axis of the hydraulic pipe (33).

5. A novel aircraft engine mounting bracket according to claim 4, wherein: the supporting wing pieces (32) are metal net rubber pieces, and the supporting wing pieces (32) are bent towards the center direction of the base (1).

6. A novel aircraft engine mounting bracket according to claim 4, wherein: the inside of oil pocket (4) and hydraulic pressure pipe (33) all has filled hydraulic oil, and the one end that base (1) was kept away from in hydraulic pressure pipe (33) is for sealing the form, has all seted up locating hole (10) on four angle steel (21), and the inboard of four angle steel (21) all bonds and has rubber protection pad (11).