CN215004048U - Loading force measuring device with pretightening force for installation - Google Patents

Abstract

The utility model discloses a take pretightning force installation to use loading measuring force device, including roof and loading arm-tie, the roof with the loading arm-tie is parallel and links into an integrated entity through the fastener, the vertical installation loading force adjustment mechanism in middle part of roof, just loading force adjustment mechanism's bottom installation force cell sensor. The loading force adjusting mechanism comprises an ejector rod bolt, a third bulge is arranged in the middle of the ejector rod bolt, one end of the ejector rod bolt penetrates through the top plate through a third cylindrical hole, the third bulge interferes with the bottom surface of the top plate, and the other end of the ejector rod bolt is connected with the force measuring sensor through a transfer joint. The utility model discloses comparatively accurate pretightning force can be taken for aircraft cabin lock mounting band, and can used repeatedly to do not participate in mounting structure after supplementary installation is accomplished, make mounting structure simple, economical and practical.

Description

Loading force measuring device with pretightening force for installation

Technical Field

The utility model relates to a mounting tool, especially a take pretightning force installation to use loading measuring force device.

Background

The cabin door lock is used as a mechanical product for keeping the closed state of the cabin door after the cabin door of the aircraft is opened, closed or closed, and plays an important role in ensuring the safe take-off and landing, the task reliability, the flight safety and the like of the aircraft. In recent years, with the higher and higher requirements for high-performance and high-index design of novel airplanes, locking mechanisms such as cabin door locks and cabin door pull rods are developed from traditional simple mechanisms into complex and high-reliability novel mechanical products.

Normal unlocking of aircraft doors has specific requirements on installation pre-tightening force: the pretightening force is too large, the phenomenon that the lock cannot be unlocked easily occurs, the pretightening force is too small, and the opening problem of the cabin door easily occurs.

The installation of aircraft cabin door lock also needs comparatively accurate pretightning force: the proper pretightening force is beneficial to the service life of the cabin door connecting structure, and the rigidity and tightness of the connecting structure can be enhanced; the excessive pretightening force can cause the connection failure, the cabin door lock is difficult to open, and even the connecting bolt is broken; too little pretightning force can make the bolt not hard up again, appears the hatch door aperture problem even, influences structural safety.

At present, the installation of the lock belt pretightening force of the aircraft door usually adjusts the thickness or the compression amount of a sealing batten of the aircraft door, and the corresponding compression amount of the required pretightening force is calibrated by measuring the pretightening force of the lock under the thickness of the specific sealing batten. During real installation, the lock and the sealing pressing strip are adjusted to the required pretightening force to correspond to the calibrated compression amount. The method is used for indirectly carrying out pre-tightening force on the cabin door lock mounting belt, is troublesome and has inaccurate pre-tightening force after mounting.

SUMMERY OF THE UTILITY MODEL

The utility model aims to solve the technical problem that, it is difficult to the not enough of accurate quantization to current aircraft cabin door lock installation pretightning force, provides a take load measuring force device for the pretightning force installation, and it can accurate settlement installation pretightning force to can realize that the hatch door lock takes the pretightning force installation.

For solving the technical problem, the utility model provides a take pretightning force installation to use loading measuring force device, including roof and loading arm-tie, the roof with the loading arm-tie is parallel and links into an integrated entity through the fastener, the vertical installation loading force adjustment mechanism in middle part of roof, just loading force adjustment mechanism's bottom installation force cell sensor.

The utility model discloses usable roof and loading arm-tie will need loading pretightning force device (what adopt in particular embodiment is cabin lock) clamping, and the pretightning force is applyed to roof and the stress surface (what adopt in particular embodiment is the installation crossbeam) that is located the needs loading pretightning force device of force cell sensor bottom simultaneously to rethread loading force adjustment mechanism, reaches the predetermined pretightning force that needs loading pretightning force device until the force cell sensor reading.

Preferably, the loading force adjusting mechanism comprises an ejector rod bolt, a third bulge is arranged in the middle of the ejector rod bolt, one end of the ejector rod bolt penetrates through the top plate through a third cylindrical hole, the third bulge interferes with the bottom surface of the top plate, and the other end of the ejector rod bolt is connected with the force measuring sensor through a transfer joint. The ejector rod bolt is screwed through the fixed top plate and the adapter joint, and two ends of the ejector rod bolt respectively extrude the top plate and the stress surface, so that the pre-tightening force is conveniently applied.

Preferably, the third protrusion is a spherical body, a third spherical recess hole is formed in the bottom of the top plate, and the third protrusion is attached to the third spherical recess hole, so that the ejector bolt is stably connected with the top plate, and the pre-tightening force applied by the ejector bolt can be transmitted to the top plate as far as possible.

Preferably, the loading arm-tie is for there being 4, sets up the second arch on every loading arm-tie outside facing side, and 4 the loading arm-tie end to end, adjacent two in the second protruding card of orientation equidirectional of loading arm-tie goes into the second draw-in groove of a connecting plate, makes 4 the loading arm-tie is injectd in the coplanar.

Preferably, the second protrusion is dovetail-shaped, and the second slot is a dovetail groove matched with the second protrusion.

Preferably, the top plate is provided with an upper ball head connecting bolt through a second cylindrical hole, the loading pulling plate is provided with a lower ball head connecting bolt through a first cylindrical hole, and the upper ball head connecting bolt is connected with the lower ball head connecting bolt through a connecting threaded sleeve.

Preferably, the head of the lower ball head connecting bolt is provided with a first screwing groove, the head of the upper ball head connecting bolt is provided with a second screwing groove, and the screwing directions of the threads at the two ends of the connecting screw sleeve are opposite. When the lower ball head connecting bolt is fixed through the first screwing groove, the upper ball head connecting bolt is fixed through the second screwing groove, and the distance between the top plate and the loading pulling plate can be adjusted by rotating the connecting screw sleeve.

Preferably, the diameter of the first cylindrical hole is larger than the outer diameter of the screw of the lower ball stud, the diameter of the second cylindrical hole is larger than the outer diameter of the screw of the upper ball stud, and the diameter of the third cylindrical hole is larger than the outer diameter of the upper rod part of the ejector bolt, so that the parallelism of the top plate and the loading pulling plate can be conveniently adjusted.

Preferably, the base is arranged at the bottom of the force sensor and is connected with the stress surface through the base, so that the force sensor can be effectively protected. The force sensor is generally a commercial force sensor, one end of which is screwed with the adapter joint and the other end of which is connected with the base.

Preferably, one end of the ejector bolt penetrating through the top plate is a polygonal column so that a wrench can engage with the ejector bolt to screw the ejector bolt.

Preferably, the middle part of the adapter joint is a polygonal column body, screw holes are formed in two ends of the adapter joint, one end of the adapter joint is connected with the force measuring sensor, and the other end of the adapter joint is connected with the ejector rod bolt.

Preferably, the base is a cylinder, one end with the smaller diameter is provided with a screw hole and is in threaded connection with the force measuring sensor, the other end is a disc flat bottom, and when the base is used, the base extrudes a stress surface (an installation cross beam) and pulls a connecting seat of the connecting cabin door lock together with the loading pulling plate, so that a pair of opposite acting forces is formed between the installation cross beam and the connecting seat.

Compared with the prior art, the beneficial effects of the utility model are that:

1. the utility model can provide more accurate pretightening force for the aircraft cabin door lock mounting belt, thereby improving the safe reliability and durability of the aircraft cabin door lock;

2. the utility model discloses loading measuring force device has the controllability, ability used repeatedly to do not participate in mounting structure after supplementary installation is accomplished, make mounting structure simple, and economical and practical.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.

Fig. 1 is a schematic view of an overall aircraft door latch pretension installation structure.

Fig. 2 is a schematic diagram of the compensation mechanism of the present invention.

Fig. 3 is a diagrammatic and schematic view of the loading force measuring device of the present invention.

Fig. 4 is the structure schematic diagram of the utility model after the installation of the pre-tightening force of the lock of the middle cabin door is completed.

Fig. 5 is a schematic structural view of the mounting beam.

Fig. 6 is a schematic structural diagram of the first compensation block.

Fig. 7 is a schematic structural diagram of a second compensation block.

Fig. 8 is a schematic structural diagram of an intermediate compensation block.

Fig. 9 is a schematic cross-sectional structure of the connection plate.

Fig. 10 is a schematic structural view of a loading pulling plate.

Fig. 11 is a schematic sectional view taken along line a-a of fig. 10.

Fig. 12 is a schematic view of the structure of the lower ball joint screw.

Fig. 13 is a schematic view of the structure of the coupling nut.

Fig. 14 is a structural schematic diagram of an upper ball joint screw.

Fig. 15 is a schematic structural view of the top plate.

Fig. 16 is a schematic sectional view of the top plate a-a.

Fig. 17 is a schematic structural view of the jack bolt.

Fig. 18 is a schematic view of the construction of the adapter.

Fig. 19 is a schematic structural view of the base.

In the figure:

A. and B, loading the force measuring device.

1. The cabin door comprises a cabin door, 2 parts of a lock seat, 3 parts of a cabin door lock, 4 parts of a connecting seat, 5 parts of a mounting cross beam, 5-1 parts of a pre-tightening force adjusting bolt reserved screw hole, 5-2 parts of a cross beam mounting reserved screw hole, 6 parts of a cross beam connecting joint, 7 parts of a cabin door frame, 8 parts of a pre-tightening force adjusting bolt, 9 parts of a compensation mechanism lateral adjusting nut, 10 parts of a first compensation block, 10-1 parts of a first compensation block bottom surface, 10-2 parts of a first waist-shaped through hole, 10-3 parts of a first compensation block inclined surface, 10-4 parts of a first bulge, 10-5 parts of a first compensation block circular screw hole, 11 parts of a second compensation block, 11-1 parts of a second compensation block bottom surface, 11-2 parts of a first waist-shaped through hole, 11-3 parts of a second compensation block inclined surface, 11-4 parts of a first bulge, 11-5 parts of a second compensation block circular screw hole, 12 parts of a compensation mechanism lateral adjusting bolt, 13. the middle compensation block, 13-1, the bottom surface of the middle compensation block, 13-2, the right inclined surface of the middle compensation block, 13-3, a first clamping groove, 13-4, the left inclined surface of the middle compensation block, 13-5, a second waist-shaped through hole, 14, a pre-tightening force adjusting nut, 15, a connecting plate, 15-1, a second clamping groove, 16, a loading pulling plate, 16-1, a second protrusion, 16-2, a first spherical concave hole, 16-3, a first cylindrical hole, 17, a lower ball head connecting bolt, 17-1, the spherical surface of the head of the lower ball head connecting bolt, 17-2, a first screwing groove, 17-3, a thread of the lower ball head connecting bolt, 18, a connecting threaded sleeve, 18-1, a threaded hole in the connecting threaded sleeve, 18-2, a hexahedron in the middle of the connecting threaded sleeve, 18-3, a lower threaded hole in the connecting threaded sleeve, 19, an upper ball head connecting bolt, 19-1, an upper ball head connecting bolt head spherical surface, 19-2, a second screwing groove, 19-3, an upper ball head connecting bolt rod part, 20, a top plate, 20-1, a second spherical recessed hole, 20-2, a second cylindrical hole, 20-3, a third spherical recessed hole, 20-4, a third cylindrical hole, 21, a mandril bolt, 21-1, a mandril bolt hexagonal section square head, 21-2, an upper rod part of the mandril bolt spherical surface, 21-3, a third bulge, 21-4, a mandril bolt screw head, 22, a switching joint, 22-1, a switching joint outer hexagonal section square head, 22-2, a switching joint screw hole, 22-3, a switching joint screw head, 23, a force measuring sensor, 24, a base, 24-1, a base screw hole and 24-2, a base disc.

Detailed Description

The invention is further described below with reference to specific preferred embodiments, without thereby limiting the scope of protection of the invention.

For convenience of description, the relative positional relationship of the components, such as: the descriptions of the upper, lower, left, right, etc. are described with reference to the layout directions of the drawings in the specification, and do not limit the structure of the present patent.

As shown in fig. 1, an embodiment of an aircraft cabin door lock installation pretightening force adjusting device includes a cabin door 1 fixedly connected with an aircraft body and an installation beam 5, a lock seat 2 is fixedly installed on the cabin door 1, a cabin door lock 3 is installed on the lock seat 2, a connecting seat 4 is fixedly arranged at the top of the cabin door lock 3, the top of the connecting seat 4 is set to be a plane parallel to the bottom surface of the installation beam 5, a compensation mechanism a is arranged between the top plane of the connecting seat 4 and the bottom surface of the installation beam 5, and a loading force measuring device B is detachably installed at the bottom of the connecting seat 4 and the top of the installation beam 5.

As shown in fig. 2, 5 to 8, the compensation mechanism a includes: 4 pretightening force adjusting bolts 8, a compensation mechanism lateral adjusting nut 9, a first compensation block 10, a second compensation block 11, a compensation mechanism lateral adjusting bolt 12, a middle compensation block 13 and 4 pretightening force adjusting nuts 14.

The first compensation block 10 is a right-angle trapezoid stretching body, a first waist-shaped through hole 10-2 is vertically arranged on the first compensation block 10, a first protrusion 10-4 in a quadrilateral cross section shape is arranged on an inclined surface 10-3 of the first compensation block, and a first compensation block circular screw hole 10-5 is horizontally arranged on the first protrusion 10-4. The second compensation block 11 has the same structure as the first compensation block 10. The middle compensation block 13 is an isosceles trapezoid stretching body, a second waist-shaped through hole 13-5 is vertically arranged on the middle compensation block 13, and a first clamping groove 13-3 is arranged in the middle of the middle compensation block 13.

The first compensation block 10 and the second compensation block 11 are oppositely arranged on the top plane of the connecting seat 4, the bottom surface 10-1 of the first compensation block and the bottom surface 11-1 of the second compensation block are respectively attached to the top plane of the connecting seat 4, the inclined surface 10-3 of the first compensation block is opposite to the inclined surface 11-3 of the second compensation block, the right inclined surface 13-2 of the middle compensation block is matched with the inclined surface 11-3 of the second compensation block, the left inclined surface 13-4 of the middle compensation block is matched with the inclined surface 10-3 of the first compensation block, the bottom surface 13-1 of the middle compensation block is attached to the bottom surface of the mounting cross beam 5, and the projection 11-4 of the quadrilateral cross section of the second compensation block and the projection 10-4 of the first compensation block respectively extend into two ends of the first clamping groove 13-3. The four pretightening force adjusting bolts 8 are respectively in threaded connection with 4 pretightening force adjusting nuts 14 through screw holes on the connecting seat 4, a first waist-shaped through hole 11-2 of the second compensating block 11 or a first waist-shaped through hole 10-2 of the first compensating block 10, a second waist-shaped through hole 13-5 on the middle compensating block 13 and a pretightening force adjusting bolt reserved screw hole 5-1 (see fig. 5) on the mounting cross beam 5. The lateral adjusting bolt 12 of the compensating mechanism passes through a circular screw hole 11-5 (see fig. 7) of the second compensating block and a circular screw hole 10-5 (see fig. 6) of the first compensating block respectively and is then in threaded connection with the lateral adjusting nut 9 of the compensating mechanism for adjusting the distance between the first compensating block 10 and the second compensating block 11. The included angle (bottom angle) between the inclined plane 11-3 (shown in figure 7) of the second compensation block and the bottom surface 11-1 (shown in figure 7) of the second compensation block, the included angle (bottom angle) between the inclined plane 10-3 (shown in figure 6) of the first compensation block and the bottom surface 10-1 (shown in figure 6) of the first compensation block, the included angle (top angle) between the right inclined plane 13-2 (shown in figure 8) of the middle compensation block, the left inclined plane 13-4 (shown in figure 8) of the middle compensation block and the bottom surface 13-1 (shown in figure 8) of the middle compensation block are equal, the first compensation block 10 can slide laterally or axially relative to the pre-tightening force adjusting bolt 8 arranged in the first waist-shaped through hole 10-2 (shown in figure 6) of the first compensation block 10 and the second compensation block 11 can slide laterally or axially relative to the pre-tightening force adjusting bolt 8 arranged in the first waist-shaped through hole 11-2 (shown in figure 7) of the first compensation block, and then the screw joint position of the lateral adjusting bolt 12 of the compensation mechanism and the lateral adjusting nut 9 of the compensation mechanism, the first compensation block 10 and the second compensation block 11 are close to or separate from each other, so that the middle compensation block 13 is forced to float up and down, and the purpose of compensating the gap between the bottom surface of the installation beam 5 and the top plane of the connecting seat 4 (shown in figure 1) is achieved.

As shown in fig. 3, 9-19, the loading force measuring device B includes: 4 connecting plates 15, 4 loading pull plates 16, 4 lower ball head connecting bolts 17, 4 connecting threaded sleeves 18, 4 upper ball head connecting bolts 19, a top plate 20, a top rod bolt 21, an adapter joint 22, a force measuring sensor 23 and a base 24.

One side of each of the 4 loading pull plates 16 with the first spherical concave holes 16-2 faces downwards, the other side of each loading pull plate is attached to the downward side of the connecting seat 4, the axis of one of the two first cylindrical holes 16-3 is overlapped with the axis of one matched upper ball head screw cylindrical hole 20-2 in 3 x 3 (rows x columns) on the corresponding angle of the top plate 20, namely, one of the first cylindrical holes 16-3 is matched with one upper ball head screw cylindrical hole 20-2 in 3 x 3 (rows x columns) on the corresponding angle of the top plate 20, and the matching of the two specific holes needs to be determined according to the size and the shape of the bottom surface of the mounting cross beam 5 and the top surface of the connecting seat 4; the loading pulling plates 16 are square, two adjacent side surfaces of the loading pulling plates 16 facing to the outside are respectively provided with a dovetail-shaped second protrusion 16-1, and during assembly, the dovetail-shaped second clamping groove 15-1 of each connecting plate 15 is clamped with the second protrusions 16-1 of the two adjacent loading pulling plates 16 in the same direction, so that the 4 loading pulling plates 16 are limited in the same plane; the lower ball joint connecting bolt rods 17-3 of the 4 lower ball joint connecting bolts 17 respectively penetrate through the first spherical recessed hole 16-2 and the first cylindrical hole 16-3 of the 4 loading pull plates 16 until the spherical surface 17-1 of the lower ball joint connecting bolt head is jointed with the corresponding first spherical recessed hole 16-2, and the 4 lower ball joint connecting bolt rods 17-3 are respectively in threaded connection with the lower screw holes 18-3 of the 4 connecting screw sleeves 18; a screw hole 18-1 on the connecting screw sleeve of each connecting screw sleeve 18 is then in threaded connection with an upper ball head connecting bolt rod part 19-3 of an upper ball head connecting bolt 19; the rod part 19-3 of the upper ball head connecting bolt 19 passes through a second spherical recess hole 20-1 and a second cylindrical hole 20-2 on the top plate 20 until the spherical surface 19-1 of the upper ball head connecting bolt head is attached to the second spherical recess hole 20-1; the second spherical sunken hole 20-1 faces back to the cabin door 1, the third spherical sunken hole 20-3 faces towards the cabin door 1, and a hexagonal cross-section square head 21-1 of an ejector rod bolt 21 and a spherical upper rod part 21-2 of the ejector rod bolt pass through a third cylindrical hole 20-4 until a spherical third bulge 21-3 arranged on the ejector rod bolt 21 is attached to a third spherical sunken hole 20-3 arranged on the bottom surface of the top plate 20; the mandril bolt screw head 21-4 is in threaded connection with a changeover joint screw hole 22-2 in a changeover joint square head 22-1 with an outer hexagonal cross section in the changeover joint 22; the adapter connector screw head 22-3 is in threaded connection with one end of the force measuring sensor 23; the other end of the force measuring sensor 23 is in threaded connection with a base screw hole 24-1 in the base 24; the base disc 24-2 is pressed on one side of the mounting cross beam 5, which is back to the cabin door 1; the diameter of the first cylindrical hole 16-3 is slightly larger than the outer diameter of the lower ball joint bolt rod 17-3, the diameter of the second cylindrical hole 20-2 is slightly larger than the outer diameter of the upper ball joint bolt rod 19-3, the diameter of the third cylindrical hole 20-4 is slightly larger than the outer diameter of the upper rod part 21-2 of the ejector rod bolt spherical surface, and the parallelism of the top plate 20, the loading pulling plate 16 and the cross beam 5 can be adjusted; the screw thread turning direction between the connecting screw sleeve 18 and the lower ball head connecting bolt 17 is opposite to the screw thread turning direction between the connecting screw sleeve 18 and the upper ball head connecting bolt 19, the head of the lower ball head connecting bolt 17 is provided with a first screwing groove 17-2, the head of the upper ball head connecting bolt 19 is provided with a second screwing groove 19, when the first screwing groove 17-2 and the second screwing groove 19-2 are fixed, the connecting screw sleeve 18 is screwed, and the distance between the mounting cross beam 5 and the connecting seat 4 can be adjusted; the hexagonal section square head 22-1 outside the adapter connector is clamped, the ejector rod bolt hexagonal section square head 21-1 is screwed, the distance between the top plate 20 and the cross beam 5 is adjusted, and a reverse force is formed between the cross beam 5 and the connecting seat 4.

The utility model discloses aircraft hatch door lock installation pretightning force adjusting device's application method includes following step:

1. the cabin door frame 7 and the cross beam connecting joint 6 are fixedly connected with the machine body through the cabin wall, the edge of the cabin door 1 is clamped by the cabin door frame 7, the lock seat 2 is fixedly installed on the cabin door 1, the cabin door 1 is hung on the lock hook of the cabin door lock 3 through the lock seat 2, the lock shell of the cabin door lock 3 is connected with the connecting seat 4, and the top surface of the connecting seat 4 is parallel to the bottom surface of the installing cross beam 5 and is arranged in a suspended mode at a distance (see fig. 1).

2. The pretightening force adjusting bolt 8 (see fig. 2) is connected with the connecting seat 4, the compensating mechanism A and the mounting cross beam 5, adjusts the lateral adjusting bolt 12, and is provided with a pretightening force adjusting nut 14 at the top of the pretightening force adjusting bolt 8 without being screwed, so that no pretightening force is generated on the pretightening force adjusting bolt 8.

3. The loading force measuring device B is assembled according to the graphic relation of figure 3, the top plate 20, the upper ball screw 19, the connecting screw sleeve 18, the lower ball screw 17 and the loading pull plate 16 are adjusted to enable the top plate 20, the loading pull plate 16 and the mounting cross beam 5 to be horizontal, the base 24 is pressed on the side, opposite to the cabin door, of the mounting cross beam 5, the loading pull plate 16 of the loading force measuring device B pulls the connecting seat 4, the outer hexagonal section square head 22-1 of the adapter joint and the top plate 20 are fixed, and the ejector rod bolt hexagonal section square head 21-1 is screwed until the force measuring sensor 23 (shown in figure 3) displays that the preset required locking pre-tightening force value is reached.

4. Pretension adjustment nut 14 (see fig. 2) is adjusted until load cell 23 (see fig. 3) shows a value of zero.

5. Adjusting the compensation mechanism A, filling the suspension space: and adjusting a lateral adjusting nut 9 of the compensation mechanism and a lateral adjusting bolt 12 of the compensation mechanism to enable the first compensation block 10 and the second compensation block 11 to be close to the middle, and forcing the middle compensation block 13 to axially move along the pretightening force adjusting bolt 8 until the top plane of the middle compensation block 13 is attached to the lower surface of the mounting cross beam 5.

6. The load cell B is removed (the hatch lock mounting structure after removal is shown in fig. 4).

The above description is only for the specific embodiments of the present invention, but the scope of the present invention is not limited thereto, and those skilled in the art can utilize the technical content disclosed above to make many possible variations and modifications to the technical solution of the present invention, or to modify equivalent embodiments with equivalent variations, without departing from the scope of the technical solution of the present invention. Therefore, any simple modification, equivalent change and modification made to the above embodiments by the technical entity of the present invention should fall within the protection scope of the technical solution of the present invention.

Claims (9)

1. The loading force measuring device with the pretightening force for installation comprises a top plate and a loading pull plate, and is characterized in that the top plate and the loading pull plate are parallel and are connected into a whole through a fastener, a loading force adjusting mechanism is vertically installed in the middle of the top plate, and a force measuring sensor is installed at the bottom of the loading force adjusting mechanism.

2. The loading force measuring device with pretightening force installation according to claim 1, wherein the loading force adjusting mechanism comprises a push rod bolt, a third protrusion is arranged in the middle of the push rod bolt, one end of the push rod bolt penetrates through the top plate through a third cylindrical hole, the third protrusion interferes with the bottom surface of the top plate, and the other end of the push rod bolt is connected with the force measuring sensor through an adapter joint.

3. The loading force measuring device with pretightening force installation function of claim 2, wherein the third protrusion is a spherical body, a third spherical recess hole is formed in the bottom of the top plate, and the third protrusion is attached to the third spherical recess hole.

4. The loading force measuring device with the pretightening force installation function according to claim 1, wherein the number of the loading pulling plates is 4, a second protrusion is arranged on the side surface of each loading pulling plate facing to the outside, the 4 loading pulling plates are connected end to end, and the second protrusions facing to the same direction of two adjacent loading pulling plates are clamped into a second clamping groove of one connecting plate, so that the 4 loading pulling plates are limited in the same plane.

5. The loading force measuring device with pretightening force installation according to claim 4, wherein the second protrusion is dovetail-shaped, and the second clamping groove is a dovetail groove matched with the second protrusion.

6. The loading force measuring device with pretightening force installation according to claim 2, wherein an upper ball head connecting bolt is installed on the top plate through a second cylindrical hole, a lower ball head connecting bolt is installed on the loading pulling plate through a first cylindrical hole, and the upper ball head connecting bolt is connected with the lower ball head connecting bolt through a connecting threaded sleeve.

7. The loading force measuring device with pretightening force installation function according to claim 6, wherein the head of the lower ball head connecting bolt is provided with a first screwing groove, the head of the upper ball head connecting bolt is provided with a second screwing groove, and the thread directions of the threads at the two ends of the connecting threaded sleeve are opposite.

8. The load cell force measuring device with preload setting as claimed in claim 6, wherein said first cylindrical bore has a diameter larger than an outer diameter of a screw of said lower ball stud, said second cylindrical bore has a diameter larger than an outer diameter of a screw of said upper ball stud, and said third cylindrical bore has a diameter larger than an outer diameter of an upper rod portion of said ejector stud.

9. The load-measuring device with preload mounting as claimed in any one of claims 1 to 8, wherein a base is provided at the bottom of said load cell.

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