CN218632647U

CN218632647U - Electrical plug assembly for auxiliary fuel tank of airplane

Info

Publication number: CN218632647U
Application number: CN202222854742.3U
Authority: CN
Inventors: 邓仁俊; 何体财; 郑汉康
Original assignee: Sichuan Aviation Industry Chuanxi Machine Co ltd
Current assignee: Sichuan Aviation Industry Chuanxi Machine Co ltd
Priority date: 2022-10-28
Filing date: 2022-10-28
Publication date: 2023-03-14
Anticipated expiration: 2032-10-28

Abstract

The utility model discloses an aircraft bellytank electric plug assembly, including welded seat (1), base (2), inner tube (5), outer tube (8), plug seat (11) and electric plug (12), welded seat (1) links firmly with aircraft bellytank, welded seat (1) upper end sets up base (2), the nest form is made to base (2) inside, the bulb form that matches with base (2) is made to inner tube (5) lower extreme outer wall, inner tube (5) overcoat outer tube (8), the nest form is made to the upper end inside of outer tube (8), the bulb form that matches with outer tube (8) is made to the lower extreme outer wall of plug seat (1), set up electric plug (12) in the upper end hole of plug seat (1), electric plug (12) top is connected with the socket of wing, the bottom connecting cable of electric plug (12), the cable is worn out from the line through-hole of crossing that base (2) was opened and is connected to the bellytank. This ensures vertical positioning of the electrical plug 12 with the socket.

Description

Electrical plug assembly for auxiliary fuel tank of airplane

Technical Field

The utility model relates to an aircraft bellytank electric plug subassembly especially relates to an aircraft bellytank electric plug subassembly with position compensation function.

Background

In order to increase the oil carrying capacity of the airplane and increase the voyage and the endurance time of the airplane, an auxiliary oil tank is additionally arranged below the wings of the airplane, and the auxiliary oil tank realizes circuit connection and electric signal transmission through an electric plug welded on the auxiliary oil tank. But the welding deformation is large, the distance between each socket between the auxiliary oil tank and the wing is usually large, and the vertical positioning of the electric plug and the socket is not easy to ensure, so that the plugging is difficult or even impossible.

Disclosure of Invention

In order to solve the electric plug that prior art exists and the difficult assurance of the vertical location of socket for the problem of grafting difficult even unable grafting, the utility model provides an aircraft bellytank electric plug subassembly. The utility model discloses an aircraft bellytank electric plug subassembly, a serial communication port, including welded seat, base, inner tube, outer tube, plug seat and electric plug, the welded seat lower extreme link firmly with aircraft bellytank through the welding, welded seat upper end set up inside opening and have the through-hole the base, the inside pore wall of base make into the ball socket form, inner tube lower extreme outer wall make with the inside ball socket form pore wall of base form the ball socket of one-level bulb revolute pair, the outer tube of inner tube overcoat, the inside pore wall of upper end of outer tube make into the ball socket form, the lower extreme outer wall of plug seat make with the inside ball socket form pore wall of outer tube match form the ball socket of second grade bulb revolute pair, the upper end hole of plug seat in set up the electric plug, the electric plug top be connected with the wing socket, the bottom connecting cable of electric plug, the cable pass in proper order the plug seat the outer tube the inner tube with the inside pore cavity of base, follow the base open the through-hole of opening be connected to the bellytank through-hole and wear out to be connected to the bellytank.

Furthermore, a through hole is radially formed in the outer pipe, a section of through groove is axially formed in the inner pipe, a rivet is arranged at one end of the through hole of the outer pipe, and the rivet penetrates through the through groove of the inner pipe and is riveted at the other end of the through hole of the outer pipe.

Furthermore, the inner hole wall of the lower end of the outer pipe is provided with an annular groove, a guide ring I is arranged in the annular groove, the inner hole wall of the upper end of the inner pipe is provided with an annular groove, and a guide ring II is arranged in the annular groove.

Furthermore, the outer part of the outer tube is sleeved with a spring, one end of the spring is in surface contact with a step outside the upper end of the outer tube, and the other end of the spring is in surface contact with a step outside the lower end of the inner tube.

Furthermore, a flange is manufactured outside the base, screw through holes are manufactured on the flange, screws penetrate through the base to be connected with the welding seat, the base is connected with the welding seat through the screws, and anti-loosening stainless steel wires are connected among the screws.

Compared with the prior art, the utility model, have following advantage and beneficial effect:

the utility model discloses an aircraft bellytank electric plug assembly, adopt the inner tube to be fixed in the base inside form one-level revolute pair, the plug socket be fixed in the outer tube inside form two-level revolute pair, the fitting surface all designs into spherical inside and outside profile, realizes the circumferential direction and the position compensation of two-level bulb revolute pair; the outer pipe is sleeved into the inner pipe, and the rivet is matched with the through groove to provide guidance for relative movement of the inner pipe and the outer pipe, so that the problem of vertical positioning of the socket is solved. In addition, the spring is arranged outside the outer pipe to provide pretightening force for plugging, so that the phenomenon that the electric plug falls off possibly caused by airplane vibration is effectively avoided; the guide ring I and the guide ring II are arranged between the inner pipe and the outer pipe, so that the stability and the fluency of the relative motion of the inner pipe and the outer pipe are improved, and the mutual abrasion between the metal inner pipe and the metal outer pipe is effectively avoided, thereby increasing the wear resistance of the electric plug assembly; stainless steel wires are wound among the screws for anti-loose treatment, reverse pretightening force is applied to the screws, and the screws are prevented from falling off due to airplane vibration.

Drawings

Figure 1 is a schematic structural view of an aircraft drop tank electrical plug assembly of the present invention.

In the figure: 1. the novel plug comprises a welding seat, a base, a screw, a stainless steel wire, an inner pipe, a guide ring I, a rivet, an outer pipe, a spring, a guide ring II, a plug seat and an electric plug, wherein the welding seat comprises 2 parts of the base, 3 parts of the screw, 4 parts of the stainless steel wire, 5 parts of the inner pipe, 6 parts of the guide ring I, 7 parts of the rivet, 8 parts of the outer pipe, 9 parts of the spring, 10 parts of the guide ring II, 11 parts of the plug seat and 12 parts of the electric plug.

Detailed Description

The present invention will be described in further detail with reference to examples, but the embodiments of the present invention are not limited thereto.

Fig. 1 is an embodiment of aircraft bellytank electric plug assembly of the utility model, a serial communication port, including welding seat 1, base 2, inner tube 5, outer tube 6, plug seat 11 and electric plug 12, 1 lower extreme of welding seat adopt argon arc welding to link firmly with aircraft bellytank, 1 upper end of welding seat set up inside and open and have the through-hole base 2, 2 inside pore walls of base make into the ball socket form, 5 lower extreme outer walls of inner tube make with 2 inside ball socket pore walls of base form the bulb form of one-level bulb revolute pair that matches, inner tube 2 overcoat outer tube 8, the inside pore wall of upper end of outer tube 8 make into the ball socket form, the lower extreme outer wall of plug seat 11 make with the inside ball socket form pore wall of outer tube 8 match form the bulb form of second grade bulb revolute pair, the upper end hole of plug seat 11 in set up electric plug 12, the top of electric plug 12 be connected with the wing, the bottom of electric cable 12 connect in proper order the electric plug seat pass through the electric plug seat 11 pass through the inner tube of base 2 and the through-hole of base 2 open the through-hole of inner tube 2. This ensures that the electrical plug 12 is vertically positioned with respect to the socket.

A through hole is radially formed in the outer pipe 8, a section of through groove is axially formed in the inner pipe 5, a rivet 7 is arranged at one end of the through hole of the outer pipe 8, and the rivet 7 penetrates through the through groove of the inner pipe 5 and is riveted at the other end of the through hole of the outer pipe 8. This provides guidance for the relative movement of the inner tube 5 and the outer tube 8.

The inner hole wall of the lower end of the outer pipe 8 is provided with an annular groove, a guide ring I6 is arranged in the annular groove, the inner hole wall of the upper end of the inner pipe 5 is provided with an annular groove, and a guide ring II 10 is arranged in the annular groove. Therefore, the relative motion stability of the inner pipe 5 and the outer pipe 8 is improved, and the abrasion between the metal inner pipe 5 and the metal outer pipe 8 is effectively avoided.

The outer part of the outer pipe 8 is sleeved with a spring 9, one end of the spring 9 is in surface contact with a step surface on the outer part of the upper end of the outer pipe 8, and the other end of the spring 9 is in surface contact with a step surface on the outer part of the lower end of the inner pipe 5. Therefore, the scalability of the electric plug 12 is realized, the rigid butt joint of the electric plug 12 is solved, the pretightening force is provided for the plug, and the phenomenon that the electric plug 12 falls off possibly caused by the vibration of the airplane is effectively avoided.

The base 2 is externally provided with a flange, the flange is provided with a through hole for passing a wire, the flange is provided with a screw through hole, a screw 3 penetrates through the base 2 to be connected with the welding seat 1, the base 2 is fixedly connected with the welding seat 1 through the screw 3, and a plurality of screws 3 are connected with a plurality of anti-loosening stainless steel wires 4. The stainless steel wire gives the screw 3 a reverse pretightening force, so that the screw 3 is prevented from falling off due to airplane vibration.

Claims

1. An aircraft drop tank electrical plug assembly, comprising: the aircraft wing joint comprises a welding seat (1), a base (2), an inner tube (5), an outer tube (8), a plug seat (11) and an electric plug (12), wherein the lower end of the welding seat (1) is fixedly connected with an aircraft auxiliary oil tank through welding, the base (2) with a through hole formed inside is arranged at the upper end of the welding seat (1), the hole wall inside the base (2) is made into a ball socket shape, the outer wall of the lower end of the inner tube (5) is made into a ball socket shape matched with the ball socket hole wall inside the base (2) to form a first-level ball head revolute pair, the outer tube (8) is sleeved outside the inner tube (5), the hole wall inside the upper end of the outer tube (8) is made into a ball socket shape, the outer wall of the lower end of the plug seat (11) is made into a ball socket shape matched with the ball socket hole wall inside the outer tube (8) to form a second-level revolute pair, the electric plug (12) is arranged in an inner hole at the upper end of the plug seat (11), the top end of the electric plug (12) is connected with a socket of a wing, and the electric cable penetrates through the through hole of the inner tube (2) and the inner tube (5) and the through hole of the base (2).

2. An aircraft drop tank electrical plug assembly as claimed in claim 1, wherein: the rivet is characterized in that a through hole is radially formed in the outer pipe (8), a section of through groove is axially formed in the inner pipe (5), a rivet (7) is arranged at one end of the through hole of the outer pipe (8), and the rivet (7) penetrates through the through groove of the inner pipe (5) and is riveted at the other end of the through hole of the outer pipe (8).

3. An aircraft drop tank electrical plug assembly as claimed in claim 2, wherein: the inner hole wall of the lower end of the outer pipe (8) is provided with an annular groove, a guide ring I (6) is arranged in the annular groove, the inner hole wall of the upper end of the inner pipe (5) is provided with an annular groove, and a guide ring II (10) is arranged in the annular groove.

4. An aircraft drop tank electrical plug assembly as claimed in claim 3, wherein: the outer portion of the outer tube (8) is sleeved with a spring (9), one end of the spring (9) is in surface contact with a step face on the outer portion of the upper end of the outer tube (8), and the other end of the spring (9) is in surface contact with a step face on the outer portion of the lower end of the inner tube (5).

5. An aircraft drop tank electrical plug assembly as claimed in claim 4, wherein: base (2) outside system have the flange, the screw via hole is made to the flange, screw (3) pass base (2) with welded seat (1) connect, base (2) pass through screw (3) with welded seat (1), it is a plurality of screw (3) between even have locking stainless steel wire (4) of using.