阅读说明：本技术 一种飞机垂向约束与保护装置 (Vertical restraint of aircraft and protection device ) 是由 郭俊毫 崔明 米征 王孟孟 郭永跃 张永利 于 2020-04-09 设计创作，主要内容包括：本申请属于飞机结构强度试验技术领域,特别涉及一种飞机垂向约束与保护装置,包括由下至上设置的：承力底座；测力传感器,铰接设置在承力底座的顶面；调节螺杆,底端通过调节柱连接至测力传感器顶部；支持杆底座,固定连接至调节螺杆顶端；垂向支持杆,底端固定连接至支持杆底座顶端；起落架接头,底端铰接在垂向支持杆顶端,用于与起落架连接。本申请的飞机垂向约束与保护装置,体积小,占用试验空间小,不会与起落架附近加载点加载装置发生干涉,另外,测力传感器监测值与起落架垂向实际值误差更小,更能准确监测约束点起落架载荷。(The application belongs to the technical field of aircraft structural strength tests, in particular to vertical restraint of aircraft and protection device, include by supreme setting down: a force bearing base; the force sensor is hinged on the top surface of the bearing base; the bottom end of the adjusting screw is connected to the top of the force transducer through an adjusting column; the support rod base is fixedly connected to the top end of the adjusting screw rod; the bottom end of the vertical supporting rod is fixedly connected to the top end of the supporting rod base; and the bottom end of the landing gear joint is hinged to the top end of the vertical supporting rod and is used for being connected with a landing gear. The vertical restraint of aircraft and protection device of this application, it is small, occupation test space is little, can not take place to interfere with near undercarriage loading point loading device, and in addition, force cell sensor monitoring value is littleer with the vertical actual value error of undercarriage, more can accurate monitoring restraint point undercarriage load.)

1. An aircraft vertical restraint and protection device, comprising:

the bearing base (11), the bearing base (11) has parallel top surface and bottom surface;

the bottom of the force measuring sensor (8) is hinged to the top surface of the force bearing base (11), and the rotating axial direction of the force measuring sensor is parallel to the top surface of the force bearing base (11);

the axial bottom end of the adjusting screw rod (5) is fixedly connected to the top of the force measuring sensor (8) through an adjusting column (6), and the axial length of the adjusting screw rod (5) can be adjusted;

the bottom end of the supporting rod base (4) is fixedly connected to the axial top end of the adjusting screw rod (5);

the axial bottom end of the vertical supporting rod (3) is fixedly connected to the top end of the supporting rod base (4);

the bottom end of the landing gear joint (1) is hinged to the top end of the vertical supporting rod (3), the rotating axial direction of the landing gear joint is parallel to the top surface of the bearing base (11), and the landing gear joint (1) is used for being connected with a landing gear.

2. The aircraft vertical restraint and protection device of claim 1, wherein the force-bearing base (11) is in a cross shape and has four force-bearing rod parts (111) extending from the center to four directions, and wherein the aircraft vertical restraint and protection device further comprises:

the auxiliary connecting frame (31) is fixedly arranged on the rod body of the vertical supporting rod (3);

the bottom end of one auxiliary stay bar (12) is hinged with one bearing bar part (111), and the top end of the auxiliary stay bar (12) is hinged with the auxiliary connecting frame (31).

3. The aircraft vertical restraint and protection device according to claim 2, wherein the top of the bearing rod part (111) and the auxiliary connecting frame (31) are provided with bearing double lugs, the two axial ends of the auxiliary stay rod (12) are provided with auxiliary single lugs, and the two axial ends of the auxiliary stay rod (12) are hinged to the bearing double lugs of the bearing rod part (111) and the auxiliary connecting frame (31) through the auxiliary single lugs respectively.

4. An aircraft vertical restraint and protection device according to claim 1 characterized in that the top end of the vertical support rod (3) is provided with an upper single lug (2) and the bottom end of the landing gear joint (1) is provided with two lugs adapted to the upper single lug (2).

5. The aircraft vertical restraint and protection device according to claim 1, characterized in that the top surface of the force bearing base (11) is provided with a bottom double lug (10), and the bottom of the load cell (8) is provided with a lower side single lug (9) matched with the load cell.

6. An aircraft vertical restraint and protection device according to claim 5, characterized in that the bottom of the load cell (8) is axially internally threaded, and the top of the lower lug (9) is provided with an externally threaded stud adapted thereto.

7. The aircraft vertical restraint and protection device according to claim 6, characterized in that the top of the load cell (8) is internally threaded axially, and the bottom of the adjustment column (6) is provided with an adapted external thread; and

the top of the adjusting column (6) is provided with an internal threaded hole along the axial direction, the axial bottom end of the adjusting screw rod (5) is provided with an external thread matched with the adjusting column, and the axial top end of the adjusting screw rod (5) is provided with an external thread opposite to the bottom end in the thread direction; and

the bottom of the supporting rod base (4) is provided with an internal thread hole matched with the external thread at the top end of the adjusting screw rod (5), and the middle of the adjusting screw rod (5) is provided with an external hexagonal head.

8. Aircraft vertical restraint and protection device according to claim 7, characterized in that between the external hexagonal head of the adjusting screw (5) and the supporting rod base (4) at the top end, and between the external hexagonal head of the adjusting screw (5) and the adjusting column (6) at the bottom end, there are respectively provided spiral washers (7).

9. Aircraft vertical restraint and protection device according to claim 7, characterized in that a spiral gasket (7) is provided at the connection of the adjustment column (6) and the load cell (8).

Technical Field

The application belongs to the technical field of aircraft structural strength tests, and particularly relates to a vertical restraint and protection device for an aircraft.

Background

In the structural strength test of the airplane, 6 degrees of freedom of the airplane need to be restrained, wherein the degrees of freedom include 3 vertical degrees of freedom, and the vertical displacement and pitching of the airplane are limited. The vertical restraint mounting portion is mostly located at the landing gear. Crowbar type restraint is used in the existing airplane structural strength test. The crow bar type constraint characteristics are as follows: the undercarriage joint is connected to crow bar one end, is connected through the monaural in the middle of the crow bar with the stand, and the other end passes through the connecting piece to be connected with ground fixing base.

However, crowbar type constraints have at least the following disadvantages: the crowbar type constraint comprises an upright post, a supporting base, a crowbar and the like, occupies a large test field space, and is easy to interfere with loading equipment of a loading point near the undercarriage. In addition, in the test process, if the force measuring sensor needs to be replaced, the crow bar constraint needs to be disengaged, and another set of airplane vertical constraint needs to be designed. Meanwhile, for the working condition test with larger deformation of the undercarriage, the error between the monitoring value of the crowbar type constraint sensor and the true value of the undercarriage is larger.

Disclosure of Invention

In order to solve at least one of the above technical problems, the present application provides an aircraft vertical restraint and protection device.

The application discloses vertical restraint of aircraft and protection device includes:

the bearing base is provided with a top surface and a bottom surface which are parallel to each other;

the bottom of the force sensor is hinged to the top surface of the force bearing base, and the rotating axial direction of the force sensor is parallel to the top surface of the force bearing base;

the axial bottom end of the adjusting screw is fixedly connected to the top of the force transducer through an adjusting column, and the axial length of the adjusting screw can be adjusted;

the bottom end of the support rod base is fixedly connected to the axial top end of the adjusting screw rod;

the axial bottom end of the vertical supporting rod is fixedly connected to the top end of the supporting rod base;

and the bottom end of the landing gear joint is hinged to the top end of the vertical supporting rod, the rotating axial direction of the landing gear joint is parallel to the top surface of the bearing base, and the landing gear joint is used for being connected with a landing gear.

According to at least one embodiment of this application, the messenger base is the cross, has by four messenger pole portions that the center extends to four directions, wherein, the vertical restraint of aircraft and protection device still include:

the auxiliary connecting frame is fixedly arranged on the rod body of the vertical supporting rod;

the bottom end of one auxiliary stay bar is hinged with one bearing rod part, and the top end of the auxiliary stay bar is hinged with the auxiliary connecting frame.

According to at least one embodiment of this application, load pole portion top and all be provided with the load ears on the supplementary link, the axial both ends of supplementary vaulting pole are provided with supplementary monaural, the axial both ends of supplementary vaulting pole respectively through supplementary monaural with load pole portion and the load ears of supplementary link are articulated.

According to at least one embodiment of this application, the top of vertical support pole is provided with the upside monaural, and the bottom that the undercarriage connects is provided with the ears with upside monaural looks adaptation.

According to at least one embodiment of this application, the top surface of bearing base is provided with bottom ears, the load cell bottom is provided with the downside monaural of looks adaptation.

According to at least one embodiment of the application, the bottom of the load cell starts with an internal threaded hole along the axial direction, and the top of the lower single lug is provided with an external threaded column matched with the external threaded column.

According to at least one embodiment of the present application, the top of the load cell starts to be internally threaded along the axial direction, and the bottom of the adjusting column is provided with an external thread matched with the external thread; and

the top of the adjusting column is provided with an internal thread hole along the axial direction, the axial bottom end of the adjusting screw is provided with an external thread matched with the adjusting screw, and the axial top end of the adjusting screw is provided with an external thread with the direction opposite to the thread direction of the bottom end of the adjusting screw; and

the bottom of the supporting rod base is provided with an internal thread hole matched with the external thread at the top end of the adjusting screw rod, and the middle of the adjusting screw rod is provided with an external hexagonal head.

According to at least one embodiment of the present application, spiral washers are respectively disposed between the outer hexagonal head of the adjusting screw and the supporting rod base at the top end, and between the outer hexagonal head of the adjusting screw and the adjusting column at the bottom end.

According to at least one embodiment of the present application, a spiral washer is provided at a junction of the adjustment post and the load cell.

The application has at least the following beneficial technical effects:

1) compared with crowbar type restraint, the strut type restraint device has small volume, occupies small test space and cannot interfere with a loading device at a loading point near the undercarriage;

2) compared with crowbar type constraint, the error between the monitoring value of the force measuring sensor and the vertical actual value of the undercarriage is smaller, and the load of the undercarriage at the constraint point can be monitored more accurately.

Drawings

FIG. 1 is a schematic structural view of an aircraft vertical restraint and protection device (not including an auxiliary strut) according to the present application;

FIG. 2 is a schematic view of the vertical restraint and protection device (including the auxiliary stay) of the aircraft of the present application;

FIG. 3 is a diagram comparing the present invention vertical restraint and protection device with the present invention.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.

It should be understood that terms such as "central," "longitudinal," "lateral," "front," "back," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like, which may be referred to in the description of the present application, are used in the orientation or positional relationship indicated in the drawings for convenience in describing the present application and to simplify the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be considered limiting of the scope of the present application.

The aircraft vertical restraint and protection device of the present application is described in further detail below with reference to figures 1-3.

The application discloses vertical restraint of aircraft and protection device can include parts such as load base 11, force cell 8, adjusting screw 5, support rod base 4, vertical support rod 3 and undercarriage joint 1 that set up from bottom to top.

Specifically, the force bearing base 11 has a top surface and a bottom surface which are parallel to each other, and is arranged on a corresponding supporting surface (such as a laboratory floor) through the bottom surface.

The force measuring sensor 8 can be various suitable force measuring sensors known at present, the bottom of the force measuring sensor is hinged to the top surface of the force bearing base 11, and the rotating axial direction of the force measuring sensor is parallel to the top surface of the force bearing base 11.

It should be noted that the bottom of the force measuring sensor 8 may be hinged to the top surface of the force bearing base 11 through a plurality of suitable hinge methods, in an embodiment of the present application, preferably, a bottom double lug 10 is fixedly disposed on the top surface of the force bearing base 11 through bolts, rivets, and the like, and correspondingly, a lower side single lug 9 adapted to the bottom of the force measuring sensor 8 is disposed at the bottom of the force measuring sensor, so as to be hinged through a single double lug connection method.

Further, the lower single lug 9 at the bottom of the load cell 8 can also be fixedly connected in a plurality of suitable manners, in this embodiment, preferably, an inner threaded hole is formed at the bottom of the load cell 8 along the axial direction, and an outer threaded column matched with the bottom of the lower single lug 9 is arranged at the top of the lower single lug 9, so that the load cell can be fixedly connected through threads.

The axial bottom end of adjusting screw 5 is fixedly connected to the top of load cell 8 through adjusting post 6, and adjusting screw 5 can adjust the axial length. The bottom end of the support rod base 4 is fixedly connected to the axial top end of the adjusting screw 5.

Likewise, the adjustment screw 5 may be fixedly connected to the load cell 8 in any suitable manner, as well as in any suitable length adjustment configuration. In the embodiment, preferably, the top of the force measuring sensor 8 starts to be provided with an internal threaded hole along the axial direction, and the bottom of the adjusting column 6 is provided with an external thread matched with the external thread so as to be connected in a threaded fit manner; an internal thread hole is formed in the top of the adjusting column 6 along the axial direction, an adaptive external thread is arranged at the axial bottom end of the adjusting screw rod 5, so that the adjusting column is connected in a thread fit mode, and an external thread opposite to the bottom end thread direction is arranged at the axial top end of the adjusting screw rod 5; and the bottom end of the supporting rod base 4 is provided with an internal thread hole matched with the external thread at the top end of the adjusting screw rod 5, and the middle part of the adjusting screw rod 5 is provided with an outer hexagonal head, so that the aim of adjusting the distance between the top supporting rod base 4 and the bottom adjusting column 6 is fulfilled by rotating the outer hexagonal head.

Further, spiral washers 7 may be respectively disposed between the outer hexagonal head of the adjusting screw 5 and the supporting rod base 4 at the top end, between the outer hexagonal head of the adjusting screw 5 and the adjusting column 6 at the bottom end, and at the connection between the adjusting column 6 and the load cell 8, to increase the stability of the structural connection.

The axial bottom end of the vertical supporting rod 3 is fixedly connected to the top end of the supporting rod base 4 through a bolt; the bottom end of the landing gear joint 1 is hinged to the top end of the vertical supporting rod 3, the rotating axial direction of the landing gear joint is parallel to the top surface of the force bearing base 11, and the landing gear joint 1 is used for being connected with a landing gear.

Similarly, in this embodiment, it is preferable that the upper-side monaural 2 is provided at the top end of the vertical support rod 3, and the bottom end of the landing gear joint 1 is provided with two ears adapted to the upper-side monaural 2, so that the landing gear joint is hinged by a single-double ear structure.

Further, in the aircraft vertical restraint and protection device of the present application, the force bearing base 11 may be in various suitable shapes, in this embodiment, preferably, the force bearing base 11 is in a cross shape, and has four force bearing rod parts 111 extending from the center to four directions; at this time, the aircraft vertical restraining and protecting device of the present application further includes an auxiliary connecting frame 31 and four auxiliary stay bars 12 to play an auxiliary supporting role (in the form shown in fig. 2) in a long-term shutdown state or when the load cell needs to be replaced.

Specifically, the auxiliary connecting frame 31 is fixedly arranged on the 3 rod bodies of the vertical supporting rod and is provided with 4 bearing double lugs, and similarly, the top of the bearing rod part 111 is provided with the bearing double lugs; furthermore, auxiliary single lugs are arranged at two axial ends of the auxiliary stay bar 12, the bottom end of one auxiliary stay bar 12 is hinged with two lugs of one bearing bar part 111 through the single lug, and the single lug at the top end of the auxiliary stay bar 12 is hinged with the corresponding bearing two lugs of the auxiliary connecting frame 31.

To sum up, the vertical restraint of aircraft of application and protection device compares with prior art and has following advantage or positive effect at least:

1) compared with crowbar type restraint, the strut type restraint device has small volume, occupies small test space and cannot interfere with a loading device at a loading point near the undercarriage;

2) 4 auxiliary support rods are designed, and the auxiliary support rods are installed in a long-term shutdown state, so that the constraint stability is enhanced, and the airplane protection effect is achieved;

3) when the force transducer needs to be replaced, 4 auxiliary stay bars are installed to realize the function (at the moment, the length of the auxiliary stay bar is adjusted until the load value of the force transducer is 0, the force transducer is detached, and a new force transducer is installed), a set of new vertical constraint does not need to be additionally designed, the design workload is reduced, and the operation is convenient;

4) compared with crowbar type constraint, the error between the monitoring value of the force measuring sensor and the vertical actual value of the undercarriage is smaller, and the load of the undercarriage at the constraint point can be monitored more accurately.

Wherein, as shown in fig. 3 (the left side is crow bar formula restraint, and the right side is the vaulting pole formula restraint of this application), the principle that this application can more accurate monitoring restraint point undercarriage load is as follows:

the stay bar type constraint Y is 2.7 meters, if a crowbar type constraint is adopted, the Y is 0.8 meter; under the condition that the undercarriage deforms X, the deformation angle of the brace type restraint relative to the crowbar type restraint is small, and the error is smaller; wherein, the deformation angle is: tan θ is X/Y, load cell feedback value: f_Monitoring＝F_{Landing gear vertical orientation}*cosθ。

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.