CN203146568U - Hinge self-adaptive conical connecting assembly - Google Patents

Abstract

The utility model belongs to an aircraft control surface control technology and relates to a hinge self-adaptive conical connecting assembly. The hinge self-adaptive conical connecting assembly comprises a conical bolt, a conical bush, a step washer, a nut and two joints with two mutually intersected lug sheets, wherein the conical bolt comprises a cone, a cylinder, a screw thread and an open pin hole; the cone is a circular truncated cone; the small-diameter end of the cone is connected with the cylinder; the open pin hole is formed in the screw thread; an inner hole of the conical bush is a cylindrical surface; an outer hole of the conical bush is a conical surface; the inner hole is matched with the cylindrical surface of the conical bolt; and the outer hole is matched with a conical hole of the other lug sheet of the double lug joints and is provided with a gap for compensation. According to the hinge self-adaptive conical connecting assembly, the connecting clearance of the hanging joints of the control surface of the aircraft is eliminated and reduced and the connecting rigidity of the hanging joints of the control surface is improved, so that the control rigidity of the control surface is improved, the fluttering index of the aircraft is improved, the maneuverability of the aircraft is improved, and important significance is achieved.

Description

A kind of hinge self adaption taper connection assembly

Technical field

The utility model belongs to the vehicle rudder control technique, relates to a kind of vehicle rudder hinge self adaption taper connection assembly.

Background technique

Landing, the maneuvering flight of most aerospace aircraft or adjust attitude in the air and generally control by rudder face.Rudder face is to be connected with main plane by suspension joint, and handles by booster, and rudder face hangs with the manipulation signal sees Fig. 1.

Rudder face 1, rudder face joint 2, rudder face suspension hinge 3, wing joint 4, main plane 5, main plane booster bearing 6, preceding hinge 7, booster 8, back hinge 9, rudder face booster bearing 10 have been formed rudder face with each link and have been handled closed loop among Fig. 1.、

By improving the mobility that rudder face efficient can improve aircraft, and a kind of effective means that improve rudder face efficient just improve the manipulation rigidity of rudder face.Rudder face is handled the representation of rigidity and is seen formula 1.

$\frac{1}{K}=\frac{1}{K1}+\frac{1}{\mathrm{<figure-callout\; id="2"\; label="K"\; filenames="HDA00003000025700011.png,HDA00003000025700021.png"\; state="\{\{state\}\}">K</figure-callout>}2}+......+\frac{1}{\mathrm{Kn}}$ (formula 1)

K: the manipulation rigidity that rudder face is total

K1, K2 ... Kn: the rigidity of forming each link of series loop of handling closed loop.

From formula 1 as can be seen, improve total rudder face and handle stiffness K, must improve the rigidity of each link, weak link can not be arranged.In each link, rudder face hinge 3 is links important in the rigidity closed loop, the hinge of traditional rudder face suspension joint generally adopts the cylndrical surface to cooperate, because the restriction of manufacturability, installation, working service etc., can there be certain clearance in the hinge at this place, and in use also can this gap constantly be enlarged because of factors such as wearing and tearing, bring adverse influence to handling rigidity.Tradition rudder face suspension joint connects situation as shown in Figure 2.

Fig. 2 rudder face hangs hinge and is made up of wing joint 4, rudder face joint 2, bolt 11, lining 12, nut 13, bearing 14, packing ring 15 etc.Rudder face joint 2 and bearing 14, bearing 14 and bolt 11, wing joint 4 and lining 12 if there is the gap in the surface of contact of lining 12 and bolt 11, all can exert an influence to the rigidity of hinge.Wherein rudder face joint 2 and bearing 14, bearing 14 has relevant standard-required with gap between the bolt 11, can not arbitrarily adjust.And wing joint 4 and lining 12, between lining 12 and the bolt 11 since technology because the restriction of manufacturability, installation and working service etc., can there be certain clearance in the surface of contact at this place, and in use also can this gap constantly be enlarged because of factors such as wearing and tearing.

The model utility content

The purpose of this utility model is: propose a kind of self adaption taper connection assembly that can effectively eliminate the knuckle joint gap, improve the hinge coupling stiffness.

Technical solution of the present utility model is: a kind of hinge self adaption taper connection assembly, comprise taper bolt, taper bush, step packing ring, nut and two joints that have interlaced auricle, wherein, described taper bolt comprises cone, cylindrical body, screw thread, cotter-pin hold; Wherein, cone is Rotary-table, the less end of its diameter and cylindrical body join, and cotter-pin hold is arranged on the screw thread, and the taper bush endoporus is the cylndrical surface, outer hole is conical surface, endoporus and taper bolt the cylndrical surface cooperate, outer hole cooperates with the cone shape hole of another auricle of ears joint, and offers the slit for compensation, described step packing ring is provided with the step projection, is installed on the taper bush.

The cone end face of described taper bolt is provided with anti-sway motion block, matches with antihunting boss on being arranged on the joint auricle, and during installation, the two compresses fixing mutually.

Have in the middle of the cone of taper bolt and be deep into cylindrical auxiliary hole.

The cone match tapering of taper bolt is preferably between 20 °～24 °, and tolerance should control 3 ' in.

Two joints that have interlaced auricle are respectively wing joint and rudder face joint.

The beneficial effects of the utility model are: the utility model hinge self adaption taper connection assembly is by the design to taper hole, taper bolt, the conical surface lining conical surface and slit, even in course of working, produce the situation of certain limit error, still can guarantee normal the cooperation and use, have adaptivity preferably.After using the long period section, if matching part is because the gap appears in wearing and tearing etc., can guarantee the cooperation of the conical surface again by adjusting the position of nut, eliminate the gap.The anti-sway motion block of taper bolt end simultaneously cooperates with antihunting boss on the joint to prevent the relative telemechanical of taper bolt between bolt hole, to reduce wear.And working service is convenient, and is similar with the dismounting of plain bolt nut, need not special tool equipment, simultaneously simple in structure, the reliability height.Can be used for most rudder face joints that are articulated and connected that adopt in addition, also can be used for other the joint that is articulated and connected, such as being articulated and connected of hatch door, have adaptability preferably.

Therefore the utility model is eliminated and is reduced vehicle rudder suspension joint joint gap, alleviate rudder face and hang the problem that rigidity is handled in the influence of gluded joint joint gap, be a kind of effective solution and technology that improves vehicle rudder suspension joint coupling stiffness, can improve the coupling stiffness of rudder face suspension joint greatly, thereby improve the manipulation rigidity of rudder face, improve the flutter index of aircraft, improve the mobility of aircraft, have bigger actual application value.

Description of drawings

Fig. 1 is that rudder face hangs and the manipulation schematic representation;

Fig. 2 is that a kind of prior art rudder face hangs the hinge structure schematic representation;

Fig. 3 is the structural representation of the utility model hinge self adaption taper connection assembly;

Fig. 4 is hinge self adaption taper connection components parts explosion;

Fig. 5 is the structural drawing of taper bolt;

Fig. 6 is that schematic representation is implemented in the installation of the utility model hinge self adaption taper connection assembly; Wherein, hinge, 10-rudder face booster bearing, 11-bolt, 12-lining, 13-nut, 14-bearing, 15-packing ring, 16-taper bolt, 17-taper bush, 18-step packing ring, 19-nut, the 20-conical surface, 21-cylndrical surface, 22-screw thread, 23-cotter-pin hold, the anti-sway motion block of 24-, 25-auxiliary hole, 26-antihunting boss behind 1-rudder face, 2-rudder face joint, 3-rudder face suspension hinge, 4-wing joint, 5-main plane, 6-main plane booster bearing, the preceding hinge of 7-, 8-booster, the 9-.

Embodiment

Below in conjunction with accompanying drawing the utility model is elaborated.

Please consult Fig. 3 and Fig. 4 simultaneously, Fig. 3 is the structural representation of the utility model hinge self adaption taper connection assembly, and Fig. 4 is hinge self adaption taper connection components parts explosion.The utility model hinge self adaption taper connection assembly comprises wing joint 4, rudder face joint 2, taper bolt 16, taper bush 17, step packing ring 18, nut 19.

See also Fig. 5, it is the structural drawing of taper bolt.Described taper bolt 16 is cores of this cover link, is used for substituting the plain bolt of traditional Placement, partly is made up of cone 20, cylindrical body 21, screw thread 22, cotter-pin hold 23, anti-sway motion block 24, auxiliary hole 25 etc.Wherein, cone 20 is Rotary-table, and the less end of its diameter and cylindrical body 21 join, and awl auxiliary hole 25 is arranged in the middle of the cone, and is deep into cylindrical body.Cotter-pin hold 23 is arranged on the screw thread 22, and anti-sway motion block 24 is arranged on the cone end face.

And described wing joint 4 and rudder face joint 2 are provided with interlaced attachment lug, and wing joint 4 attachment lugs are provided with antihunting boss 26.Offer on the taper bush 17 for the slit that compensation is installed, it is socketed on the cylindrical body 21 of taper bolt.Step packing ring 18 is provided with the step projection, with installing and fixing of better fit taper bush 17 and taper bolt.

See also Fig. 6, it is the installation enforcement schematic representation of the utility model hinge self adaption taper connection assembly.During as installed, described taper bolt 16 passes the attachment lug of wing joint 4 and rudder face joint 2, and its cylindrical body is socketed on the taper bush 17, and step packing ring 18 is pressed in the taper bush 17, further lock then by nut 19 lockings, and by construction opening pin on cotter-pin hold 23.The antihunting boss 26 that is arranged on simultaneously on the wing joint attachment lug props up anti-sway motion block 24, thereby avoids the swing of taper bolt, to reduce wear.

In concrete enforcement, at first need according to requirements such as load, materials, determine the size of taper bolt auricle by means such as calculating, such as auricle thickness, conical surface angle is (generally by 22 °～24 °, tolerance was by 1 minute) and frame tripe, the diameter of bolt etc., and then the parameter of definite slotted liner bushing, step packing ring, nut etc.When determining above-mentioned part Coefficient, the conical surface that must guarantee the conical surface of the conical surface, taper bush of taper bolt and auricle fit fully (the assurance applying is more than 70% at least).

Must guarantee also during installation that the conical surface of the conical surface, taper bush of taper bolt and the conical surface of auricle fit (guaranteeing at least to fit more than 70%) fully, to reach the purpose of eliminating the gap.And should with having of taper bolt anti-sway motion block 24 while being installed in the corresponding joint auricle that has antihunting boss 26, in use can not rotate with the assurance taper bolt.In addition, nut should have enough screw-down torques, and the construction opening pin, to guarantee the applying of the conical surface.

The conical surface of taper bolt is used for and an auricle hole of ears joint cooperates (also needing to make the conical surface with the conical surface coupling of taper bolt), the taper bush endoporus is the cylndrical surface, outer hole is conical surface, endoporus and taper bolt the cylndrical surface cooperate, outer hole cooperates with the cone shape hole of another auricle of ears joint, taper bush has and cracks, a certain amount of compensation can be provided, with the conical surface that guarantees it and taper bolt and the intact applying of cone shape hole of auricle, and still can self adaption there is certain error in the cone shape hole size in manufacture process after guarantee the cooperation of the conical surface.During installation by step back-up ring and nut and cotter pin with taper bolt, the taper bush axial locking along taper bolt, make the conical surface and the cylndrical surface of the taper bush that cracks closely cooperates, to reach the purpose of eliminating the gap.Through overtesting and analysis, the cone match tapering of taper bolt is preferably between 20 °～24 °, and tolerance should control 3 ' in.If in addition service time longer, the cone match position gap occurs because wearing and tearing wait, and can guarantee the cooperation of the conical surface again by adjusting the position of nut, eliminates the gap.

In addition, the utility model hinge self adaption taper connection assembly is not limited to the connection between wing joint and the hatch door joint, also can be applicable to the connection between other joints of being with attachment lugs.

The utility model is eliminated and is reduced vehicle rudder suspension joint joint gap in sum, alleviate rudder face and hang the problem that rigidity is handled in the influence of gluded joint joint gap, be a kind of effective solution and technology that improves vehicle rudder suspension joint coupling stiffness, can improve the coupling stiffness of rudder face suspension joint greatly, thereby improve the manipulation rigidity of rudder face, improve the flutter index of aircraft, improve the mobility of aircraft, have bigger actual application value.

Claims (5)

1. hinge self adaption taper connection assembly, it is characterized in that: comprise taper bolt [16], taper bush [17], step packing ring [18], nut [19] and two joints that have interlaced auricle, wherein, described taper bolt [16] comprises cone [20], cylindrical body [21], screw thread [22], cotter-pin hold [23]; Wherein, cone [20] is Rotary-table, the less end of its diameter and cylindrical body [21] join, and cotter-pin hold [23] is arranged on the screw thread [22], and taper bush [17] endoporus is the cylndrical surface, outer hole is conical surface, endoporus and taper bolt the cylndrical surface cooperate, outer hole cooperates with the cone shape hole of another auricle of ears joint, and offers the slit for compensation, described step packing ring [18] is provided with the step projection, is installed on the taper bush [17].

2. hinge self adaption taper connection assembly according to claim 1, it is characterized in that: the cone end face of described taper bolt is provided with anti-sway motion block [24], match with the antihunting boss [26] on being arranged on the joint auricle, during installation, the two compresses fixing mutually.

3. hinge self adaption taper connection assembly according to claim 2 is characterized in that: have in the middle of the cone of taper bolt and be deep into cylindrical auxiliary hole [25].

4. hinge self adaption taper connection assembly according to claim 3, it is characterized in that: the cone match tapering of taper bolt is preferably between 20 °～24 °, and tolerance should control 3 ' in.

5. hinge self adaption taper connection assembly according to claim 4, it is characterized in that: two joints that have interlaced auricle are respectively wing joint [4] and rudder face joint [2].

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