CN215048414U

CN215048414U - Lifting mechanism for ultralow-position mounting rack of auxiliary oil tank of machine body

Info

Publication number: CN215048414U
Application number: CN202120672782.9U
Authority: CN
Inventors: 谢明智; 喻峰; 王念伟
Original assignee: SICHUAN HANGTAI AVIATION EQUIPMENT CO Ltd
Current assignee: SICHUAN HANGTAI AVIATION EQUIPMENT CO Ltd
Priority date: 2021-04-01
Filing date: 2021-04-01
Publication date: 2021-12-07
Anticipated expiration: 2031-04-01

Abstract

The utility model provides a lifting mechanism for an ultra-low mounting rack of a fuselage bellytank, which comprises a bracket and two groups of lifting components for supporting the fuselage bellytank, wherein the first lifting component can be telescopically arranged at the first end of the bracket along the length direction of the bracket; the second lifting assembly can be hinged to the bracket in a turnover mode in a vertical plane, and the bracket is provided with a limiting mechanism to prevent the free end of the second lifting assembly from rotating to the position below the plane of the bracket; the utility model discloses an it expandes the subassembly with the second lift when using in the lifting mechanism for the ultralow position mounting bracket of fuselage bellytank, again with first lift the subassembly tensile enough length can, the utility model discloses a lifting mechanism is collapsible folding when not using, reduces the size of a dimension, and tensile expansion can adapt to not equidimension fuselage bellytank during the use, simple structure, convenient to use.

Description

Lifting mechanism for ultralow-position mounting rack of auxiliary oil tank of machine body

Technical Field

The utility model relates to an installation frame field particularly, relates to a lift mechanism that is used for ultralow position mounting bracket of fuselage bellytank.

Background

A secondary fuel tank for loading aviation fuel is generally suspended below the body or wings of the fighter, and special loading and unloading equipment is required for loading and unloading the secondary fuel tank.

The Chinese patent with the application number of 201611217602.8 discloses an aircraft suspension loading and unloading vehicle, wherein the top of a vehicle body is provided with a supporting structure for bearing aircraft suspensions, and the vehicle specifically comprises two groups of supporting pads which are arranged oppositely, the two groups of supporting pads are arranged on a guide rail in a relatively sliding manner so as to support the aircraft suspensions through the two groups of supporting pads, and the supporting pads can better support the aircraft suspensions with different lengths by adopting a slidable design; however, the following disadvantages still exist: the length of the guide rail limits the sliding stroke between the two groups of support pads, and the length of the guide rail needs to be designed to be long enough in order to support longer airplane suspension objects, so that the size of the loading and unloading truck is large, and the equipment is not beneficial to miniaturization and transportation transition; the shorter length of the guide rail will limit the application range of the truck.

In order to solve the contradiction, the lifting mechanism for the ultra-low mounting rack of the auxiliary oil tank of the fuselage is particularly provided.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to overcome the shortcoming of background art, provide a collapsible folding, convenient to carry's a lifting mechanism that is used for super low level mounting bracket of fuselage bellytank.

The embodiment of the utility model discloses a realize through following technical scheme:

the utility model provides a lift mechanism for super low-order mounting bracket of fuselage bellytank, includes bracket and two sets of lift subassemblies that are used for supporting fuselage bellytank, wherein:

the first lifting assembly can be arranged at the first end of the bracket in a telescopic manner along the length direction of the bracket;

the second lifting assembly can be hinged to the bracket in a turnover mode in a vertical plane, and the bracket is provided with a limiting mechanism to prevent the free end of the second lifting assembly from rotating to the position below the plane of the bracket.

Further, the second lifting assembly is hinged to the upper end face of the second end of the bracket, the bracket comprises a bracket body and a supporting section extending to the lower portion of a hinge point of the second lifting assembly and the bracket, and the supporting section is used for supporting the second lifting assembly in an unfolding state.

Furthermore, a supporting piece used for supporting the second lifting assembly in the unfolding state is arranged on the supporting section, the supporting piece vertically penetrates through the supporting section, and the supporting piece is connected with the supporting section through threads, so that the height of the supporting piece can be adjusted up and down.

Furthermore, the first lifting assembly and the second lifting assembly comprise two groups of connecting rods which are arranged in parallel, wherein the second ends of the two groups of connecting rods are connected through a supporting plate;

in the first lifting assembly, the first ends of the two groups of connecting rods are telescopically inserted into the first end of the bracket; in the second lifting assembly, the first ends of the two groups of connecting rods are respectively hinged on the bracket.

Furthermore, in the first lifting assembly, a plurality of through holes are formed in two groups of connecting rods along the length direction, and fasteners capable of penetrating into the through holes are arranged on the bracket and used for locking the telescopic length of the first lifting assembly.

Furthermore, the first lifting assembly and the second lifting assembly are respectively provided with a binding band for winding and fixing the auxiliary oil tank of the machine body.

Further, the surface of layer board is provided with the rubber cushion.

The utility model discloses technical scheme has following advantage and beneficial effect at least:

in the lifting mechanism for the ultra-low mounting rack of the auxiliary oil tank of the fuselage, the first lifting component can be telescopically arranged at the first end of the bracket along the length direction of the bracket; the second lifting assembly can be hinged to the bracket in a turnover mode in a vertical plane, and the bracket is provided with a limiting mechanism to prevent the free end of the second lifting assembly from rotating to the position below the plane of the bracket; the subassembly expandes with the second during the use, again with first lifting the subassembly tensile to enough length can, the utility model discloses a lifting mechanism is collapsible folding when not using, reduces the size of a dimension, and tensile expansion can adapt to not equidimension fuselage bellytank during the use, simple structure, convenient to use.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention, and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.

FIG. 1 is a diagram showing a state of the lifting mechanism for the extra-low mounting rack of the auxiliary fuel tank of the fuselage according to the present invention;

FIG. 2 is a schematic structural diagram of a lifting mechanism for an extra-low mounting rack of a fuselage drop tank according to the present invention;

icon: 1-chassis structure, 2-lifting mechanism, 3-lifting mechanism, 30-bracket, 300-bracket body, 301-supporting section, 302-fastener, 303-supporting piece, 31-lifting component, 31 a-first lifting component, 31 b-second lifting component, 310-supporting plate, 3100-connecting buckle, 311-connecting rod, 3110-through hole and 312-binding band.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of embodiments of the present invention, as generally described and illustrated in the figures herein, may be arranged and designed in a wide variety of different configurations.

Thus, the following detailed description of the embodiments of the present invention, presented in the accompanying drawings, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.

Referring to fig. 1 to 2, a lifting mechanism 3 for an ultra-low mounting rack of a fuselage drop tank, wherein the ultra-low mounting rack comprises a chassis structure 1 provided with rollers, a lifting mechanism 2 arranged on the lifting mechanism 2, and a lifting mechanism 3 arranged on the lifting mechanism 2; wherein, elevating system 2 includes but not limited to hydraulic jacking mechanism, cuts fork lift platform or rack and pinion elevating system etc. and elevating system 2 is used for lifting or below lifting mechanism 2, and no longer detailed in this embodiment.

The lifting mechanism 3 comprises a bracket 30 and two groups of lifting components 31 for supporting the auxiliary oil tank of the fuselage, wherein the bracket 30 has various forms, such as an integral flat table top structure or a metal frame structure, and the like, in the embodiment, the bracket 30 comprises two groups of rectangular metal pipes arranged in parallel, such as steel pipes or alloy pipes; the lift assembly 30 comprises a first lift assembly 30a and a second lift assembly 30b, wherein:

the first lifting assembly 31a is telescopically arranged at the first end of the bracket 30 along the length direction of the bracket 30, that is, the first lifting assembly 31a can be telescopically arranged along the first end direction of the bracket 30 to adjust the length; the second lifting assembly 31b can be hinged to the bracket 30 in a turnover manner in a vertical plane, and a limiting mechanism is arranged on the bracket 30 to prevent the free end of the second lifting assembly 31b from rotating below the plane of the bracket 30.

Specifically, in this embodiment, the first lifting assembly 31a and the second lifting assembly 31b each include two sets of connecting rods 311 arranged in parallel, and the connecting rods 311 and the bracket 30 are made of the same material; wherein, on every group lifts the subassembly 31, the second end of two sets of connecting rods 311 passes through the layer board 310 and connects, is equipped with the arc recess on the layer board 310, the arc recess is used for the holding fuselage bellytank, correspondingly, it is fixed all to be equipped with on first lifting subassembly 31a and the second lifting subassembly 31b to be used for the winding bandage 312 of fuselage bellytank, specifically, the both sides of every group layer board 310 respectively are equipped with a set of knot 3100, and bandage 312 adjustable length, and when fixed fuselage bellytank, bandage 312 both ends respectively tie up on connecing knot 3100, the surface of layer board 310 is provided with the rubber cushion layer, forms the buffer protection.

In the first lifting assembly 31a, the first ends of two groups of connecting rods 311 are telescopically inserted into the first end of the bracket 30, that is, each group of connecting rods 311 is respectively inserted into one group of rectangular metal tubes, and the external shapes of the connecting rods 311 match the internal contours of the rectangular metal tubes; a plurality of through holes 3110 are arranged on the two groups of connecting rods 311 along the length direction, a fastening piece 302 capable of being inserted into the through holes 3110 is arranged on the bracket 30, and after the connecting rods 311 are stretched to a proper length, the stretching length of the first lifting assembly 31a is locked by the fastening piece 302.

In the second lifting assembly 31b, the first ends of two groups of connecting rods 311 are respectively hinged to the bracket 30, and the second lifting assembly 31b is hinged to the upper end surface of the second end of the bracket 30, in this embodiment, the first ends of each group of connecting rods 311 are respectively hinged to the upper end surface of one group of rectangular metal tubes;

in addition, the bracket 30 includes a bracket body 300 and a support section 301 extending to a position below a hinge point of the second lifting assembly 31b and the bracket 30, the support section 301 is used for supporting the second lifting assembly 31b in an unfolded state, a support member 303 used for supporting the second lifting assembly 31b in the unfolded state is arranged on the support section 301, the support member 303 vertically penetrates through the support section 301, and the support member 303 and the support section 301 are connected through a thread, so that the height of the support member 303 can be adjusted up and down, the second lifting assembly 31b can be finely adjusted and supported through the support member 303, and in this embodiment, a knob is further arranged at the lower end of the support member 303 so as to be adjusted.

It should be noted that, compare in setting up first lifting assembly 31a or second lifting assembly 31b simultaneously at the both ends of bracket 30, set up simultaneously that first lifting assembly 31a needs bracket 30 to have sufficient length so that all retractable bracket 30 of two sets of first lifting assembly 31a in, and set up simultaneously that second lifting assembly 31b needs bracket 30 to have sufficient length so that can turn over simultaneously, the utility model discloses an among the lifting mechanism 3 of the ultralow position mounting bracket of fuselage bellytank, adopt one end to set up the first lifting assembly 31a of telescopic and the second lifting assembly 31b that the other end can turn over, when reducible bracket 30's length, guarantee as far as that lifting mechanism 3 has longer adjustable stroke.

The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes will occur to those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. The utility model provides a lift mechanism for super low level mounting bracket of fuselage bellytank which characterized in that, includes bracket (30) and two sets of lift subassembly (31) that are used for supporting fuselage bellytank, wherein:

the first lifting assembly (31a) can be arranged at the first end of the bracket (30) in a telescopic manner along the length direction of the bracket (30);

the second lifting assembly (31b) can be hinged to the bracket (30) in a turnover mode in a vertical plane, and a limiting mechanism is arranged on the bracket (30) to prevent the free end of the second lifting assembly (31b) from rotating to the position below the plane of the bracket (30).

2. The lifting mechanism for the ultra-low mounting rack of the auxiliary fuel tank of the fuselage according to claim 1, characterized in that:

the second lifting assembly (31b) is hinged to the upper end face of the second end of the bracket (30), the bracket (30) comprises a bracket body (300) and a supporting section (301) extending to the lower portion of a hinge point of the second lifting assembly (31b) and the bracket (30), and the supporting section (301) is used for supporting the second lifting assembly (31b) in an unfolded state.

3. The lifting mechanism for the ultra-low mounting rack of the auxiliary fuel tank of the fuselage according to claim 2, characterized in that:

the supporting section (301) is provided with a supporting piece (303) used for supporting a second lifting assembly (31b) in an unfolding state, the supporting piece (303) vertically penetrates through the supporting section (301), and the supporting piece (303) is in threaded connection with the supporting section (301), so that the height of the supporting piece (303) can be adjusted up and down.

4. The lifting mechanism for the ultra-low mount of the auxiliary fuel tank on the fuselage according to claim 1, 2 or 3, characterized in that:

the first lifting assembly (31a) and the second lifting assembly (31b) respectively comprise two groups of connecting rods (311) which are arranged in parallel, wherein the second ends of the two groups of connecting rods (311) are connected through a supporting plate (310);

in the first lifting assembly (31a), the first ends of two groups of connecting rods (311) are telescopically inserted into the first end of the bracket (30); in the second lifting assembly (31b), the first ends of two groups of connecting rods (311) are respectively hinged on the bracket (30).

5. The lifting mechanism for the ultra-low mounting rack of the auxiliary fuel tank of the fuselage according to claim 4, is characterized in that:

in first lifting assembly (31a), all be provided with a plurality of through-holes (3110) along length direction on two sets of connecting rod (311), be equipped with fastener (302) that can alternate in through-hole (3110) on bracket (30) for the locking the flexible length of first lifting assembly (31 a).

6. The lifting mechanism for the ultra-low mount of the auxiliary fuel tank on the fuselage according to claim 1, 2 or 3, characterized in that: and the first lifting assembly (31a) and the second lifting assembly (31b) are respectively provided with a binding band (312) for winding and fixing the auxiliary oil tank of the machine body.

7. The lifting mechanism for the ultra-low mounting rack of the auxiliary fuel tank of the fuselage according to claim 4, is characterized in that: the surface of the supporting plate (310) is provided with a rubber cushion layer.