阅读说明：本技术 一种机身舱段结构强度试验约束系统 (Engine body cabin section structural strength test constraint system ) 是由 卓轶 魏玉龙 陈莉 孙汉斌 廖江海 于 2020-04-17 设计创作，主要内容包括：本发明属于结构强度试验领域,具体涉及一种机身舱段结构强度试验约束系统。该系统包括承力地坪、M个立柱、M个紧固结构、M个载荷转化机构、固定底座、胶布带、垂向约束机构,固定底座设置在承力地坪上；垂向约束机构设置在固定底座的两端,垂向约束机构通过螺栓与机身舱段连接；M个立柱分别分布在机身舱段的前后航向和左右侧向位置并且立柱的下端固定在承力地坪上；胶布带粘贴在机身舱段的蒙皮端框和两侧；立柱的上端通过紧固结构与载荷转化机构的一端连接；载荷转化机构的另一端与胶布带连接。本发明能提供满足要求的约束,有效降低机身舱段端框和侧壁边界约束载荷,避免边界早于考核区域破坏。(The invention belongs to the field of structural strength tests, and particularly relates to a structural strength test constraint system for a cabin section of a fuselage. The system comprises a bearing terrace, M upright posts, M fastening structures, M load conversion mechanisms, a fixed base, an adhesive tape and a vertical restraint mechanism, wherein the fixed base is arranged on the bearing terrace; the vertical restraint mechanisms are arranged at two ends of the fixed base and are connected with the cabin section of the machine body through bolts; m upright columns are respectively distributed at the front and rear course and the left and right lateral positions of the cabin section of the airplane body, and the lower ends of the upright columns are fixed on a bearing terrace; the adhesive tape is adhered to the skin end frame and two sides of the cabin section of the fuselage; the upper end of the upright post is connected with one end of the load conversion mechanism through a fastening structure; the other end of the load conversion mechanism is connected with the adhesive tape. The invention can provide the constraint meeting the requirement, effectively reduce the constraint load of the boundary of the end frame and the side wall of the cabin section of the airplane body and avoid the damage of the boundary earlier than the check area.)

1. The utility model provides a fuselage cabin section structural strength tests restraint system which characterized in that includes: a bearing terrace, M upright posts, M fastening structures, M load conversion mechanisms, a fixed base, an adhesive tape and a vertical constraint mechanism, wherein M is a positive integer more than or equal to 4,

wherein, the fixed base is fixedly arranged on the bearing terrace;

the vertical constraining mechanisms are fixedly arranged at two ends of the fixed base, hole positions corresponding to the reserved holes of the cabin section of the machine body are arranged on the side faces of the vertical constraining mechanisms, and the vertical constraining mechanisms are connected with the cabin section of the machine body through bolts;

m upright columns are respectively distributed at the front and rear course and the left and right lateral positions of the cabin section of the airplane body, and the lower ends of the upright columns are fixed on a bearing terrace;

the adhesive tape is adhered to the skin end frame and two sides of the cabin section of the fuselage;

the upper end of the upright post is connected with one end of the load conversion mechanism through a fastening structure;

the other end of the load conversion mechanism is connected with the adhesive tape.

2. The system of claim 1, wherein the other end of the load conversion mechanism is connected to the adhesive tape, and comprises:

and (3) enabling the aluminum bar to penetrate through the adhesive tape, and connecting the aluminum bar with the other end of the load conversion mechanism through a steel cable.

3. The system of claim 1, wherein the load transfer mechanism is an N-lever system, wherein the first lever is a single lever, the second lever is two levers, and the nth lever is 2^N-1Two ends of the lever of the previous stage are respectively connected with the middle parts of the two levers of the next stage through connecting pieces.

4. The system of claim 1, wherein the force bearing terrace is uniformly provided with a plurality of inverted T-shaped fixing grooves.

5. The system of claim 1, further comprising spacers disposed at a contact location and a force transmission point location of the stationary base and the fuselage cabin.

6. The system of claim 5, wherein the spacer is a polyurethane spacer.

7. The system of claim 1, further comprising M force sensors respectively disposed between the fastening structure and the load conversion mechanism.

8. The system of claim 1, wherein the upright is L-shaped steel frame welded by steel channel, and the L-shaped steel frame is provided with inclined supporting rods on the side.

9. The system of claim 1, wherein the upper end of the column is connected to one end of the load conversion mechanism by a fastening structure, comprising:

the upper end of the stand column is provided with two fixed lugs which are fixed on the stand column by adopting foundation bolts, two ends of the fastening structure are respectively provided with a single lug, the two lugs at the upper end of the stand column are connected with the single lug at one end of the fastening structure, and the single lug at the other end of the fastening structure is connected with one end of the load conversion mechanism.

10. The system of claim 1, wherein the fastening structure is a turnbuckle.

Technical Field

The invention belongs to the technical field of structural strength tests, and particularly relates to a structural strength test constraint system for a cabin section of a fuselage.

Background

In the static force/fatigue test of the aircraft fuselage cabin section, the structural strength test of the aircraft fuselage cabin section usually adopts the fixed support/hinged support constraint, when the two constraints are adopted, a test piece of the aircraft fuselage cabin section is generally designed into a form of a test frame and a transition frame, the test frame is the same as the real structure of the aircraft, the test frame is examined in the test, and the transition frame is used as a test constraint boundary and plays a role in constraining and transferring load in the test. The design of the test frame and the transition frame is adopted, so that the processing cost of the test piece and the requirement of a test field are increased.

Disclosure of Invention

The purpose of the invention is as follows: the structural strength test constraint system for the fuselage cabin section is provided, so that boundary constraint required by a structural strength test is provided for a real fuselage cabin section, meanwhile, the processing cost of a fuselage cabin section test piece is effectively reduced, the test space requirement is reduced, the test efficiency is improved, and the design process of the fuselage cabin section is accelerated.

The technical scheme is as follows:

in a first aspect, a structural strength test constraint system for a nacelle section is provided, which includes: a bearing terrace, M upright posts, M fastening structures, M load conversion mechanisms, a fixed base, an adhesive tape and a vertical constraint mechanism, wherein M is a positive integer more than or equal to 4,

wherein, the fixed base is fixedly arranged on the bearing terrace;

the vertical constraining mechanisms are fixedly arranged at two ends of the fixed base, hole positions corresponding to the reserved holes of the cabin section of the machine body are arranged on the side faces of the vertical constraining mechanisms, and the vertical constraining mechanisms are connected with the cabin section of the machine body through bolts;

m upright columns are respectively distributed at the front and rear course and the left and right lateral positions of the cabin section of the airplane body, and the lower ends of the upright columns are fixed on a bearing terrace;

the adhesive tape is adhered to the skin end frame and two sides of the cabin section of the fuselage;

the upper end of the upright post is connected with one end of the load conversion mechanism through a fastening structure;

the other end of the load conversion mechanism is connected with the adhesive tape.

Further, the other end and the adhesive tape of load conversion mechanism are connected, specifically include:

and (3) enabling the aluminum bar to penetrate through the adhesive tape, and connecting the aluminum bar with the other end of the load conversion mechanism through a steel cable.

Further, the load conversion mechanism is an N-level lever system, wherein the first level lever is one lever, the second level lever is two levers, and the Nth level lever is 2^N-1Two ends of the lever of the previous stage are respectively connected with the middle parts of the two levers of the next stage through connecting pieces.

Furthermore, a plurality of inverted T-shaped fixing grooves are uniformly formed in the force bearing terrace.

Furthermore, the device also comprises cushion blocks which are arranged at the contact position of the fixed base and the cabin section of the machine body and the position of a force transmission point.

Further, the cushion block is a polyurethane cushion block.

Further, the load conversion device further comprises M force sensors, and the force sensors are respectively arranged between the fastening structure and the load conversion mechanism.

Furthermore, the upright posts are L-shaped steel frames welded by channel steel, and inclined support rods are further arranged on the side faces of the L-shaped steel frames.

Further, the upper end of stand is connected with one end of load conversion mechanism through fastening structure, specifically includes:

the upper end of the stand column is provided with two fixed lugs which are fixed on the stand column by adopting foundation bolts, two ends of the fastening structure are respectively provided with a single lug, the two lugs at the upper end of the stand column are connected with the single lug at one end of the fastening structure, and the single lug at the other end of the fastening structure is connected with one end of the load conversion mechanism.

Further, the fastening structure is an elastic thread sleeve.

Has the advantages that:

the fuselage cabin section structural strength test constraint system provided by the invention provides constraints meeting structural strength test requirements for a test piece through opposite-pull type course and lateral constraints and vertical constraints on the fixed base aiming at a semi-frame fuselage cabin section test piece, can effectively reduce the boundary constraint load of the fuselage cabin section end frame and the side wall, and avoids the boundary damage earlier than an examination area. The constraint can effectively reduce the processing cost of the test piece of the cabin section of the airplane body, reduce the requirement of test space, improve the test efficiency and help to accelerate the design process of the cabin section of the airplane body.

Drawings

Fig. 1 is a schematic diagram of a structural strength test constraint system of a fuselage cell section according to an embodiment of the invention.

FIG. 2 is a schematic view of vertical restraint of a restraint system according to an embodiment of the invention.

FIG. 3 is a schematic view of a heading constraint of a constraint system according to an embodiment of the invention.

FIG. 4 is a schematic side restraint diagram of a restraint system according to an embodiment of the invention.

The device comprises a machine body cabin section, a force bearing terrace 2, a vertical column 3, fixing double lugs 4, a fastening structure 5, a force sensor 6, a load conversion mechanism 7, a fixing base 8, a cushion block 9, a rubberized fabric belt 10, a vertical constraint mechanism 11, a lever 12 and a steel cable 13.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention are described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the described embodiments are to be considered in all respects only as illustrative and not restrictive, and the scope of the invention is not to be limited thereby. 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 invention. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

In the static force/fatigue test of the aircraft fuselage cabin section, the structural strength test of the aircraft fuselage cabin section usually adopts the fixed support/hinged support constraint, when the two constraints are adopted, a test piece of the aircraft fuselage cabin section is generally designed into a form of a test frame and a transition frame, the test frame is the same as the real structure of the aircraft, the test frame is examined in the test, and the transition frame is used as a test constraint boundary and plays a role in constraining and transferring load in the test. The design of the test frame and the transition frame is adopted, so that the processing cost of the test piece and the requirement of a test field are increased.

The method aims to provide boundary constraint required by a structural strength test for a real fuselage cabin section, effectively reduce the processing cost of a fuselage cabin section test piece, reduce the test space requirement, improve the test efficiency and accelerate the design process of the fuselage cabin section. The invention provides a structural strength test constraint system for a cabin section of a fuselage.

Fig. 1 is a schematic diagram of a structural strength test constraint system of a fuselage cell section according to an embodiment of the invention. As shown in fig. 1, the fuselage cabin structural strength test restraint system includes a bearing terrace 2, a stand column 3, a fixing double lug 4, a fastening structure 5, a force sensor 6, a load conversion mechanism 7, a fixing base 8, a polyurethane cushion block 9, an adhesive tape 10 and a vertical restraint mechanism 11.

Wherein, load terrace 2 can be for evenly being provided with the bearing ground of the type of falling T fixed slot to it is fixed to be convenient for.

The upright posts 3 are L-shaped steel frames welded by channel steel, the lower ends of the upright posts are fixed on a bearing terrace, at least 4 upright posts 3 are respectively connected with the front and rear course and the left and right lateral constraint structures and bear passive loads transmitted by the cabin section of the airplane body, preferably, two upright posts are respectively arranged at the front and rear courses, and one upright post is respectively arranged at the left and right lateral directions, and inclined support rods can be further arranged on the L-shaped steel frame to increase the stability.

The fastening structure 5 is preferably a connection member whose length is adjusted by turning a screw thread to achieve a fastening action. The fastening structure 5 may be a turnbuckle. The both ends of elasticity swivel nut are connected with force sensor 6 and stand 3 respectively, specifically can be connected with the stand through fixed ears 4 for the monaural of the one end of elasticity swivel nut, and the monaural of the other end of elasticity swivel nut is connected with the ears of the one end of sensor 6, and fastening structure 5 produces the pretightning force when adjusting restraint system length to restriction test piece produces whole displacement when experimental the beginning.

The load conversion mechanism 7 is a device for converting a dispersed load into a concentrated load, or converting a concentrated load into a dispersed load, and includes a lever 12 and a link, as shown in fig. 3. Specifically, the load conversion mechanism 7 is an N-level lever system, in which the first level lever is one lever, the second level lever is two levers, and the nth level lever is 2^N-1Two ends of the lever of the previous stage are respectively connected with the middle parts of the two levers of the next stage through connecting pieces.

The adhesive tape 10 is adhered to the skin end frames and two sides of the cabin section of the fuselage, so that the rigidity of the fuselage is not increased while loads can be transferred.

The load conversion mechanism 7 is arranged on the end frame of the fuselage cabin section 1 and the adhesive tapes 10 adhered on the two sides. The load conversion mechanism is fixed on the upright post 3 through the force sensor 6 and the elastic drop sleeve to form course and lateral opposite-pulling soft constraint. When the displacement of the test piece is verified through the oppositely-pulled soft constraint, the effects of passive load monitoring and test piece protection are simultaneously achieved. The load conversion mechanism 7 is connected with the adhesive tape 10 and the force sensor 6, converts passive loads dispersed on the end frame and the side surface of the machine body into concentrated loads, and realizes connection with the force sensor 6.

And the force sensor 6 is connected with the load conversion mechanism 7 and the elastic thread sleeve 5, and feeds back the magnitude of passive loads of the end frame and the side surface of the machine body during the test.

The fixed base 8 is a steel structure which is processed according to the fuselage cabin section 1, fixed on the bearing terrace 2 and used for fixing the fuselage cabin section 1, a reserved interface is arranged on the fixed base 8 to fix the vertical restraint mechanism 11, and after the reserved hole of the fuselage cabin section 1 is connected with the vertical restraint mechanism 11 through bolts, the reserved hole is fixed on the fixed base 8 to realize vertical restraint of a test piece.

Cushion blocks 9 are arranged on the fixed base 8 and distributed at the contact position and the force transmission point position of the fixed base and the machine body cabin section according to the machine body cabin section, and polyurethane cushion blocks can be used.

The vertical restraint mechanism 11 is a structure connecting the fixed base 8 and the fuselage cabin section 1. The vertical constraint mechanisms are fixedly arranged at two ends of the fixed base, hole positions corresponding to the reserved holes of the cabin section of the machine body are arranged on the side faces of the vertical constraint mechanisms, and the vertical constraint mechanisms are connected with the cabin section of the machine body through bolts.

FIG. 2 is a schematic view of vertical restraint of a restraint system according to an embodiment of the invention. The fixed base 8 is used for placing a test piece, polyurethane cushion blocks are placed on the fixed base according to the contact distribution of the fixed base and the cabin section of the machine body, and the vertical constraint mechanism on the fixed base is connected with a preformed hole in the cabin section of the machine body and used for fixing the test piece to form vertical constraint.

FIG. 3 is a schematic view of a heading constraint of a constraint system according to an embodiment of the invention. An adhesive tape belt is pasted on an end frame of a skin of a cabin section of a fuselage, an aluminum bar is sleeved on the adhesive tape belt, the adhesive tape belt is connected with a load conversion mechanism through the aluminum bar and a steel cable 13, the load conversion mechanism is fixed with a single lug on a force sensor through a bolt, the force sensor is connected with a fastening structure and fixed double lugs through bolts, the fixed double lugs are fixed on a stand column through foundation bolts, the adhesive tape belt and the load conversion mechanism, the sensor, the fastening structure, the fixed double lugs and the stand column form course constraint of a test piece, course displacement of the test piece is limited, course feedback load of the test piece is monitored, and the end frame of the cabin section of the fuselage is protected.

FIG. 4 is a schematic side restraint diagram of a restraint system according to an embodiment of the invention. The adhesive tape is pasted to side face of the fuselage cabin section, the adhesive tape is connected with the load conversion mechanism through an aluminum bar and a steel cable 13, the load conversion mechanism is fixed with a single lug on the force sensor through a bolt, the force sensor is connected with the fastening structure, the fixed double lugs are connected through a bolt, the fixed double lugs are fixed on the stand through foundation bolts, the adhesive tape is in lateral constraint with the load conversion mechanism, the sensor is connected with the fastening structure, the fixed double lugs are connected through a bolt, the stand forms a test piece, lateral displacement of the test piece is limited, lateral feedback load of the test piece is monitored, and the side wall of the fuselage cabin section is protected.

The fastening structure can tension the lateral restraint system for the elastic falling sleeve, so that the lateral displacement of the test piece at the beginning of the test is limited, and the lateral restraint is formed.

And the force sensor in the lateral constraint structure realizes the monitoring of the lateral feedback load of the test piece.

And the force sensor in the course constraint structure realizes course feedback load monitoring of the test piece.

The course constraint structure reduces the load transmitted to the cabin end frame of the airplane body during the test and protects the test piece.

The lateral constraint structure reduces the load transferred to the side face of the cabin section of the airplane body during the test and protects the test piece.

The invention provides a structural strength test constraint system of a fuselage cabin section, which adopts a fixed base fixed on a bearing terrace to install a test piece, wherein polyurethane cushion blocks (polyurethane cushion plates are arranged at the contact part and the force transmission point of the base and the fuselage cabin section) are distributed on the fixed base according to the frame position of the fuselage cabin section, and a vertical constraint mechanism on the fixed base is connected with a preformed hole on the fuselage cabin section and is used for fixing the test piece. The course and lateral constraint structure is connected through the end frame of the cabin section of the airplane body and the adhesive tape on the side wall, so that the course and lateral displacement of the cabin section of the airplane body is limited, the course and lateral support reaction force of the cabin section of the airplane body during the test is monitored, meanwhile, the safety of the test piece is protected, and the bearing capacity of the test piece is improved. The method comprises the steps of adhering an adhesive tape to the course and the lateral position of a skin of a cabin section of a machine body, connecting the adhesive tape and the lateral position by using a load conversion mechanism to form an adhesive tape-load conversion mechanism, fixing a load conversion mechanism in series with a force sensor and an elastic thread sleeve on a stand column to form lateral and course restraint and monitoring, and effectively reducing the load transmitted to an end frame of the cabin section of the machine body during testing so as to meet the requirement of a structural strength test. Through the vertical direction, the course direction and the lateral direction constraint, the real fuselage cabin section meets the constraint requirement of a structural strength test. Meanwhile, the opposite pulling restraint of the course and the lateral direction can effectively reduce the load transmitted to the end frame and the side face of the cabin section of the airplane body during the test and protect a test piece.

The structural strength test constraint system for the fuselage cabin section can meet the constraint requirement of a structural strength test for the fuselage cabin section without a transition frame. During testing, the system provides boundary constraint meeting testing requirements for the cabin section of the airplane body, simultaneously restrains feedback loads by the course and the lateral feedback loads for real-time monitoring, effectively reduces loads borne by the constraint boundaries such as the end frame and the side wall of the cabin section of the airplane body, reduces the processing cost and the period of a test piece, reduces the requirement of a test space, has the advantages of simplicity in processing the test piece, small requirement of the test space and the like, and is beneficial to accelerating the research and development process of the airplane.