Rear fairing of aircraft suspension device

Abstract

The utility model discloses a rear fairing of an airplane suspension device. The rear fairing is composed of a left lining plate, a right lining plate, a cleaning rod, countersunk rivets, a left hinge, a right hinge, a left corner box, a right corner box, a left rear cover, a right rear cover and a quick-release lock. The left and right lining plates are riveted on the left and right half beams through rivets, the left and right lining plates take beam bodies as supporting surfaces and are connected with the left and right hinges through cleaning rods, the cleaning rods are fixed in butt joint holes of the left and right lining plates and the left and right hinges through countersunk head rivets, and the left rear cover is connected with the right rear cover through a quick-release lock; the left and right corner boxes are riveted at the upper parts of the left rear cover and the right rear cover through rivets; according to the utility model, the rear fairing with a quick-release structure is arranged, so that the interior of the suspension device can be quickly maintained on the premise of ensuring that the suspension device plays a role in pneumatic rectification.

Description

TECHNICAL FIELD

[0001] The utility model relates to aircraft suspension device technical field, especially aircraft suspension device's rear fairing. BACKGROUND

[0002] Suspension device is the bridge between the aircraft and the suspended object, which is generally installed on the wing or the belly of the aircraft, used for suspending, carrying and launching / controlling various suspended objects, as shown in the reference Figure 1 The rear fairing of the suspension device is designed to protect the internal components while effectively reducing air resistance during flight and improving flight efficiency through its specific shape design. Most of the current aircraft suspension device rear fairings are designed as a whole, which is inconvenient to disassemble and maintain, often requiring the disassembly of a standard part around the left and right and up and down, and the entire rear fairing must be removed for maintenance. This aircraft suspension device rear fairing can be quickly maintained through the hinge cover and quick release lock without the need to remove the fairing. SUMMARY

[0003] The utility model aims at providing a kind of aircraft suspension device's rear fairing, for the aerodynamic fairing of suspension device, reduce air resistance, improve flight efficiency;Quick maintenance is realized through hinge cover and quick release lock.

[0004] The above technical purpose of the utility model is realized by the following technical scheme:

[0005] A kind of aircraft suspension device's rear fairing, by left and right lining, through bar, countersunk rivet, left and right hinge, left and right corner box, left rear cover, right rear cover and quick release lock are formed;Left and right lining is riveted on left and right half beam by rivet, left and right lining takes beam body as support surface, is connected with left and right hinge by through bar, and through bar is fixed in the butt joint hole of left and right lining and left and right hinge by countersunk rivet, left rear cover and right rear cover are connected by quick release lock;Left and right corner box is riveted on the upper portion of left rear cover and right rear cover by rivet.

[0006] Further, the left and right lining and the left and right hinge are made of 7050-T7451 aluminum alloy material.

[0007] Further, the left and right hinge has an included angle of 7° with the vertical direction.

[0008] Further, the number of quick release locks is four.

[0009] In conclusion, the utility model has the following beneficial effects: the utility model discloses the rear fairing of quick -detachable structure, and the rear fairing plays the premise of aerodynamic flow under guaranteeing the suspension device, realizes the quick maintenance of the inside of suspension device. BRIEF DESCRIPTION OF DRAWINGS

[0010] Figure 1 It is the structural schematic diagram of suspension device;

[0011] Figure 2 It is the unfolded schematic diagram of rear fairing of the utility model;

[0012] Figure 3 It is the exploded view of rear fairing of the utility model.

[0013] In the drawing, 1, rear fairing;1-1, left and right lining plate;1-2, through bar;1-3, countersunk rivet;1-4, left and right hinge;1-5, left and right corner box;1-6, left rear cover;1-7, right rear cover;1-8, quick -detachable lock;2, left and right half beam;3, rear vertical shaft;4, front vertical shaft;5, hang bomb hook;6, front fairing. DETAILED DESCRIPTION

[0014] The utility model will be further explained in detail below in combination with the drawings, and the technical scheme in the embodiment of the utility model is clearly and completely described, obviously, the described embodiment is only a part of the embodiment of the utility model, not all the embodiment. Based on the embodiment in the utility model, all other embodiments obtained by the ordinary skill in the art without making creative labor belong to the range of protection of the utility model.

[0015] A rear fairing of aircraft suspension device, as shown in Figure 2 And Figure 3 It is mainly composed of left and right lining plate 1-1, through bar 1-2, countersunk rivet 41-3, left and right hinge 1-4, left and right corner box 1-5, left rear cover 1-6, right rear cover 1-7 and quick -detachable lock 1-8. Main function is to carry out aerodynamic flow to the appearance of suspension device, reduces air resistance, opens after using maintenance, and it is convenient to operate the internal equipment.

[0016] Further, the left and right lining plates 1-1 are riveted on the left and right half beams by rivets, the beam body is used as a supporting surface, and the through bar 1-2 is connected with the left and right hinges 1-4, in order to prevent the through bar 1-2 from falling off, the countersunk rivets 1-3 are used to fix the through bar 1-2 in the butt joint holes of the left and right lining plates 1-1 and the left and right hinges 1-4, the left rear cover 1-6 is connected with the right rear cover 1-7 through quick-release locks 1-8, the left and right corner boxes 1-5 are used to prevent the left rear cover 1-6 and the right rear cover 1-7 from deforming, and are riveted on the upper parts of the left rear cover 1-6 and the right rear cover 1-7. Figure 2 When the quick-release locks 1-8 are removed, the left rear cover 1-6 is opened around the through bar 1-2, as shown in FIG. 2, and the internal equipment can be maintained, and the reassembling steps are opposite to the above.

[0017] Further, the left rear cover 1-7 and the right rear cover 1-7 are made of 2A12-O-δ1.5 material and are formed by sheet metal bending, the lining plates and the hinge parts are made of 7050-T7451 high-strength aluminum alloy and are formed by numerical control machining, the left and right rear covers are connected by four small force-bearing quick-release locks, the quick-release locks are removed to open the maintenance covers (the left rear cover 1-7 and the right rear cover 1-7) to the two sides, the internal equipment and the aircraft interface plug are maintained, the hinge is designed to have a 7° angle with the vertical direction, and the maintenance covers (the left rear cover 1-7 and the right rear cover 1-7) are not interfered with the aircraft wing structure when being opened.

[0018] The specific embodiment is only an explanation of the utility model, and is not a limitation of the utility model, and the person skilled in the art can make a modification without creative contribution according to the needs after reading the specification, but as long as the modification is within the scope of the claims of the utility model, it is protected by the patent law.

Claims

1. An aft fairing for an aircraft suspension device, characterized by: It is composed of left and right lining plates (1-1), through bar (1-2), countersunk rivet (1-3), left and right hinges (1-4), left and right corner boxes (1-5), left rear cover (1-6), right rear cover (1-7) and quick release lock (1-8); the left and right lining plates (1-1) are riveted on the left and right half beams (2) by rivets, the left and right lining plates (1-1) take the beam body as the supporting surface, are connected with the left and right hinges (1-4) through the through bar (1-2), and the through bar (1-2) is fixed on the left and right lining plates (1-1) and the left and right hinges (1-4) through the countersunk rivet (1-3) In the butt joint hole, the left rear cover (1-6) and the right rear cover (1-7) are connected through the quick release lock (1-8); the left and right corner boxes (1-5) are riveted on the upper parts of the left rear cover (1-6) and the right rear cover (1-7) by rivets.

2. An afterbody fairing for an aircraft suspension assembly according to claim 1, wherein: The left and right lining plates (1-1) and the left and right hinges (1-4) are made of 7050-T7451 aluminum alloy material.

3. An afterbody fairing for an aircraft suspension assembly according to claim 1, wherein: The left and right hinges (1-4) have an included angle of 7° with the vertical direction.

4. An afterbody fairing for an aircraft suspension assembly according to claim 1, wherein: The number of the quick release locks (1-8) is four.

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