CN113148223B - Installation method for door lock belt pretightening force of aircraft cabin - Google Patents
Installation method for door lock belt pretightening force of aircraft cabin Download PDFInfo
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- CN113148223B CN113148223B CN202110490395.8A CN202110490395A CN113148223B CN 113148223 B CN113148223 B CN 113148223B CN 202110490395 A CN202110490395 A CN 202110490395A CN 113148223 B CN113148223 B CN 113148223B
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- 238000009434 installation Methods 0.000 title claims abstract description 64
- 238000000034 method Methods 0.000 title claims description 17
- 230000007246 mechanism Effects 0.000 claims abstract description 72
- 238000010586 diagram Methods 0.000 description 4
- 230000006835 compression Effects 0.000 description 3
- 238000007906 compression Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000007789 sealing Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 239000000725 suspension Substances 0.000 description 2
- 230000000149 penetrating effect Effects 0.000 description 1
- 230000036316 preload Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transportation (AREA)
- Mechanical Engineering (AREA)
- Body Structure For Vehicles (AREA)
Abstract
The cabin door lock with the cabin door and the installation cross beam are fixedly installed on an aircraft body, a connecting seat which is parallel to the installation cross beam and is separated from the installation cross beam by a certain distance is arranged at the top of the cabin door lock, a compensation mechanism is arranged between the connecting seat and the installation cross beam, and the installation cross beam and the connecting seat are connected through a lock installation pre-tightening force adjusting mechanism with an initial pre-tightening force of 0; a top plate is arranged on the top surface of the mounting cross beam, a loading pull plate is arranged on the bottom surface of the connecting seat, the top plate is parallel to the loading pull plate and is connected into a whole through a fastener, a loading force adjusting mechanism is vertically arranged in the middle of the top plate, a force transducer is arranged at the bottom of the loading force adjusting mechanism, the force transducer is in abutting connection with the mounting cross beam, and the reading of the force transducer reaches a preset lock mounting pretightening force; the adjusting lock is provided with a pretightening force adjusting mechanism, so that the reading of the force transducer is restored to 0; and (3) adjusting the height of the compensation mechanism to enable the compensation mechanism to fill up a gap between the mounting cross beam and the connecting seat.
Description
Technical Field
The invention relates to an installation method of a door lock with pretightening force of an aircraft cabin.
Background
The cabin door lock is used as a mechanical product for keeping the cabin door in a closed state after the cabin door of the aircraft is opened, closed or closed, and plays an important role in ensuring the safety take-off and landing of the aircraft, the reliability of tasks, the safety of flight and the like. With the increasing requirements of high-performance and high-index design of new aircraft in recent years, cabin door locking mechanisms are changed from traditional simple mechanisms into complex and high-reliability new mechanical products.
The normal unlocking of the aircraft door has specific requirements for the installation pretightening force: the phenomenon that the door cannot be opened is easy to occur due to overlarge pretightening force, and the problem of opening of the cabin door is easy to occur due to overlarge pretightening force.
The aircraft cabin door lock also needs more accurate pretightening force during installation: the proper pretightening force is beneficial to the service life of the cabin door connecting structure, and can enhance the rigidity and compactness of the connecting structure; the connection failure caused by excessive pretightening force is difficult to open the cabin door lock, and even the connecting bolt is broken; too small pretightening force can loosen the bolts, even the problem of opening of the cabin door occurs, and the structural safety is affected.
At present, the installation of the pre-tightening force of the cabin door locking belt of the aircraft is usually to adjust the thickness or the compression amount of the cabin door sealing layering, and the pre-tightening force of the lock under the specific sealing layering thickness is measured to calibrate the corresponding compression amount of the pre-tightening force. During real installation, the lock and the sealing pressing strip are adjusted to the required pretightening force corresponding to the calibrated compression amount. The method is to indirectly provide the cabin door lock with the pretightening force, is troublesome, and is inaccurate in pretightening force after installation.
Disclosure of Invention
The invention aims to solve the technical problem that the installation pretightening force of the existing aircraft cabin door lock is difficult to accurately quantify, and provides an installation method of the aircraft cabin door lock with pretightening force, which can accurately adjust and set the installation pretightening force and can realize the installation of the cabin door lock with pretightening force.
In order to solve the technical problems, the invention provides an installation method of a door lock belt pretightening force of an aircraft cabin, which comprises the following steps:
a cabin door and a mounting cross beam are fixedly mounted on an aircraft body, a cabin door lock is fixedly mounted on the cabin door, a connecting seat is fixedly arranged at the top of the cabin door lock, the top surface of the connecting seat is parallel to the bottom surface of the mounting cross beam and is separated by a certain distance, a height-adjustable compensation mechanism is arranged between the top surface of the connecting seat and the bottom surface of the mounting cross beam, and the mounting cross beam and the connecting seat are connected into a whole through a lock mounting pre-tightening force adjusting mechanism with an initial pre-tightening force of 0;
a top plate is arranged on the top surface of the mounting cross beam, a loading pull plate is arranged on the bottom surface of the connecting seat, the top plate is parallel to the loading pull plate and is connected into a whole through a fastener, a loading force adjusting mechanism is vertically arranged in the middle of the top plate, a force transducer is arranged at the bottom of the loading force adjusting mechanism, the force transducer is in abutting connection with the top surface of the mounting cross beam, and the reading of the force transducer is a preset lock mounting pretightening force;
adjusting the lock mounting pretightening force adjusting mechanism to enable the reading of the force transducer to be restored to 0;
the height of the compensation mechanism is adjusted, so that the top surface of the compensation mechanism is attached to the mounting cross beam, and the bottom surface of the compensation mechanism is attached to the top surface of the connecting seat;
and removing the top plate, the loading pulling plate, the loading force adjusting mechanism and the force transducer, and thus completing the pretightening force installation of the cabin door lock.
According to the invention, the top plate is arranged on the top surface of the mounting cross beam, the loading pulling plate is arranged on the bottom surface of the cabin door lock connecting seat, the loading force adjusting mechanism and the force transducer are arranged between the top plate and the mounting cross beam, the pre-tightening force required by the installation of the cabin door lock is applied through the loading force adjusting mechanism, the applied pre-tightening force is accurately measured through the force transducer, the installation pre-tightening force can be accurately set during the installation of the cabin door lock, after the installation pre-tightening force is set, the loading force applied by the loading force adjusting mechanism is converted into the connecting force on the connecting bolt between the mounting cross beam and the connecting seat through the lock installation pre-tightening force adjusting mechanism, and the suspension space between the mounting cross beam and the connecting seat is filled through the compensating mechanism, so that the installation with the pre-tightening force of the cabin door lock under the accurate installation pre-tightening force is realized.
Preferably, the lock installation pre-tightening force adjusting mechanism comprises a pre-tightening force adjusting bolt and a pre-tightening force adjusting nut, wherein a screw rod of the pre-tightening force adjusting bolt penetrates through the installation cross beam and the connecting seat and is locked by the pre-tightening force adjusting nut, and when the reading of the force transducer does not reach the preset lock installation pre-tightening force, the pre-tightening force adjusting bolt and the pre-tightening force adjusting nut have no pre-tightening force; and when the reading of the force transducer reaches the preset lock installation pretightening force, adjusting the pretightening force adjusting nut to enable the reading of the force transducer to be recovered to 0.
Preferably, the compensation mechanism comprises a first compensation block and a second compensation block which are opposite and are arranged at a certain distance, opposite surfaces of the first compensation block and the second compensation block are inclined surfaces, the first compensation block and the second compensation block are connected into a whole through a compensation mechanism lateral adjusting bolt and a compensation mechanism lateral adjusting nut, an intermediate compensation block is matched with opposite surfaces of the first compensation block and the second compensation block, and when the compensation mechanism lateral adjusting nut and the compensation mechanism lateral adjusting bolt are adjusted, the first compensation block and the second compensation block are close to each other towards the middle, the intermediate compensation block is forced to axially float along the pretightening force adjusting bolt until the top surface of the intermediate compensation block is attached to the bottom surface of the mounting cross beam.
Preferably, the first compensation block and the second compensation block are respectively vertically provided with a first waist-shaped through hole, the first waist-shaped through holes are parallel to the lateral adjusting bolts of the compensation mechanism, and the mounting cross beam, the first waist-shaped through holes on the first compensation block or the second compensation block and the connecting seat are connected into a whole by the lock mounting pretightening force adjusting mechanism.
Preferably, the opposite surfaces of the first compensation block and the second compensation block are respectively provided with a first bulge, a screw hole is horizontally arranged in the first bulge, the bottom of the middle compensation block is provided with a first clamping groove in clearance fit with the first bulge, and the lateral adjustment bolt of the compensation mechanism horizontally penetrates through the first compensation block and the first bulge thereof and is locked by the lateral adjustment nut of the compensation mechanism after the second compensation block and the first bulge thereof. When the first compensation block inclined plane, the second compensation block inclined plane and the middle compensation block inclined plane slide relatively, the first protrusions of the first compensation block and the second compensation block can move left and right and up and down in the first clamping groove, so that the top surface of the middle compensation block is attached to the bottom surface of the mounting cross beam.
Preferably, the first compensation block and the second compensation block are right trapezoid stretching bodies, the middle compensation block is an isosceles trapezoid stretching body, and the base angle of the first compensation block, the base angle of the second compensation block and the vertex angle of the middle compensation block are equal.
Preferably, a second waist-shaped through hole is vertically formed in the middle compensation block, the second waist-shaped through hole is parallel to the lateral adjusting bolt of the compensation mechanism, and the mounting cross beam, the first waist-shaped through hole in the first compensation block or the second waist-shaped through hole in the middle compensation block, and the connecting seat are connected into a whole by the lock mounting pretightening force adjusting mechanism.
Preferably, the loading force adjusting mechanism comprises a push rod bolt, a spherical body is arranged in the middle of the push rod bolt, one end of the push rod bolt penetrates through the top plate, the spherical body is matched with a spherical convex hole formed in the bottom surface of the top plate, the other end of the push rod bolt is connected with the force transducer through a transfer joint, when the top plate and the transfer joint are fixed and the push rod bolt is rotated, two ends of the push rod bolt respectively squeeze the top plate and the mounting cross beam, and opposite forces are generated between the mounting cross beam and the connecting seat. One end of the ejector rod bolt penetrating through the top plate is a polygonal column body, so that a spanner can conveniently engage the ejector rod bolt to screw the ejector rod bolt. The middle part of the adapter is a polygonal column body, screw holes are formed in two ends of the adapter, one end of the adapter is connected with the force transducer, and the other end of the adapter is connected with the ejector rod through bolts. The force transducer is a commercial force transducer, one end of the force transducer is in threaded connection with the adapter, and the other end of the force transducer is connected with the base. The base is a cylinder, one end with a smaller diameter is provided with a screw hole and is in threaded connection with the force transducer, the other end is a disc flat bottom, and when the load pulling plate is used, the base extrudes the installation cross beam and pulls the connecting seat of the connecting cabin door lock together, so that a pair of opposite acting forces are formed between the installation cross beam and the connecting seat.
Preferably, the loading pulling plate is square, and the loading pulling plate has 4, and every loading pulling plate sets up dovetail second arch on the adjacent both sides face outside, and 4 loading pulling plate end to end, adjacent two in the second arch card of orientation same direction of loading pulling plate goes into the dovetail second draw-in groove of a loading pulling plate side cardboard, makes 4 loading pulling plate is limited in the coplanar.
Preferably, the top plate is provided with an upper ball connecting bolt, the loading pull plate is provided with a lower ball connecting bolt, the upper ball connecting bolt is connected with the lower ball connecting bolt through a connecting screw sleeve, threads are respectively arranged at two ends of the connecting screw sleeve, the threads at two ends of the connecting screw sleeve are opposite in rotation direction, and the distance between the lower ball connecting bolt and the upper ball connecting bolt can be adjusted by adjusting the connecting screw sleeve.
Compared with the prior art, the invention has the beneficial effects that:
1. the invention can provide more accurate pretightening force for the aircraft cabin door lock mounting band, thereby improving the safety reliability and durability of the aircraft cabin door lock;
2. the loading force measuring device has adjustability, can be reused, does not participate in the installation structure after auxiliary installation is completed, and is simple in installation structure, 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 that are required in the embodiments or the description of the prior art will be briefly described, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
Fig. 1 is a schematic view of the overall structure of the aircraft door locking strap pretension installation of the present invention.
Fig. 2 is a schematic diagram of a compensation mechanism in accordance with the present invention.
Fig. 3 is a diagrammatic illustration of a load cell of the present invention.
Fig. 4 is a schematic structural view of the cabin door lock with pretension after installation.
Fig. 5 is a schematic view of the structure of the mounting beam.
Fig. 6 is a schematic structural diagram of the first compensation block.
Fig. 7 is a schematic structural diagram of the second compensation block.
Fig. 8 is a schematic structural diagram of the intermediate compensation block.
FIG. 9 is a schematic cross-sectional view of a load plate side card.
Fig. 10 is a schematic view of the structure of the load plate.
Fig. 10-1 is a schematic view of section A-A of fig. 10.
Fig. 11 is a schematic view of the structure of the lower ball screw.
Fig. 12 is a schematic view of the structure of the connecting screw sleeve.
Fig. 13 is a schematic view of the structure of the upper ball screw.
Fig. 14 is a schematic view of the structure of the top plate.
FIG. 15 is a schematic cross-sectional view of top plate A-A.
Fig. 16 is a schematic structural view of the jack bolt.
Fig. 17 is a schematic view of the structure of the adapter.
Fig. 18 is a schematic structural view of the base.
In the figure: A. and B, loading the force measuring device.
1. Cabin door, 2, lock base, 3, cabin door lock, 4, connecting base, 5, mounting cross beam, 5-1, pre-tightening force adjusting bolt pre-reserved screw hole, 5-2, cross beam mounting pre-reserved screw hole, 6, cross beam connecting joint, 7, cabin door frame, 8, pre-tightening force adjusting bolt, 9, compensation mechanism side adjusting nut, 10, first compensation block, 10-1, first compensation block bottom surface, 10-2, first waist type through hole, 10-3, first compensation block inclined surface, 10-4, first bulge, 10-5, first compensation block round screw hole, 11, second compensation block, 11-1, second compensation block bottom surface, 11-2, first waist type through hole, 11-3, second compensation block inclined surface, 11-4, first bulge, 11-5, second compensation block round screw hole, 12, compensation mechanism side adjusting bolt, the hydraulic pressure compensation device comprises a middle compensation block 13-1, a middle compensation block bottom surface 13-2, a right inclined surface of the middle compensation block 13-3, a first clamping groove 13-4, a left inclined surface of the middle compensation block 13-5, a second waist-shaped through hole 14, a pretightening force adjusting nut 15, a loading plate side clamping plate 15-1, a second clamping groove 16, a loading plate 16-1, a second bulge 16-2, a first spherical concave hole 16-3, a loading plate cylindrical hole 17, a lower ball joint bolt 17-1, a lower ball joint bolt head spherical surface 17-2, a lower ball joint bolt head spherical surface square screwing groove 17-3, a lower ball joint bolt screw thread 18, a connecting screw sleeve 18-1, a connecting screw hole on a connecting screw sleeve, and a connecting screw sleeve intermediate hexahedron, 18-3 parts of a connecting screw sleeve lower screw hole, 19 parts of an upper ball connecting bolt, 19-1 parts of an upper ball connecting bolt head spherical surface, 19-2 parts of an upper ball connecting bolt head spherical surface square screwing groove, 19-3 parts of an upper ball connecting bolt rod part, 20 parts of a top plate, 20-1 parts of a top plate matched with an upper ball bolt spherical surface concave hole, 20-2 parts of a top plate matched with an upper ball screw cylindrical hole, 20-3 parts of a top plate matched with a top rod bolt spherical surface concave hole, 20-4 parts of a top plate matched with a top rod bolt spherical surface cylindrical hole, 21 parts of a top rod bolt, 21-1 parts of a top rod bolt hexagonal cross section square head, 21-2 parts of a top rod bolt spherical surface body, 21-4 parts of a top rod bolt screw head, 22-1 parts of a transfer joint, 22-2 parts of a transfer joint screw hole, 22-3 parts of a transfer joint screw head, 23 parts of a load cell, 24 parts of a base, 24-1 parts of a base screw hole, and 24-2 parts of a base disc.
Detailed Description
The invention is further described below in connection with specific preferred embodiments, but it is not intended to limit the scope 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 according 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 the pre-tightening force adjusting device for installing an aircraft cabin door lock of the invention comprises a cabin door 1 and an installation beam 5 which are fixedly connected with an aircraft body, 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 arranged 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 and 5 to 8, the compensation mechanism a includes: 4 pretightening force adjusting bolts 8, a compensating mechanism lateral adjusting nut 9, a first compensating block 10, a second compensating block 11, a compensating mechanism lateral adjusting bolt 12, an intermediate compensating block 13 and 4 pretightening force adjusting nuts 14.
The first compensation block 10 is a right trapezoid stretching body, a first waist-shaped through hole 10-2 is vertically formed in the first compensation block 10, a first bulge 10-4 with a quadrilateral cross section is arranged on the inclined plane 10-3 of the first compensation block, and a first compensation block round screw hole 10-5 is horizontally formed in the first bulge 10-4. The structure of the second compensation block 11 is the same as that of 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 formed in the middle compensation block 13, and a first clamping groove 13-3 is formed 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 first compensation block bottom surface 10-1 and the second compensation block bottom surface 11-1 are respectively attached to the top plane of the connecting seat 4, the first compensation block inclined surface 10-3 and the second compensation block inclined surface 11-3 are opposite, the middle compensation block right inclined surface 13-2 is matched with the second compensation block inclined surface 11-3, the middle compensation block left inclined surface 13-4 is matched with the first compensation block inclined surface 10-3, the middle compensation block bottom surface 13-1 is attached to the bottom surface of the mounting cross beam 5, and the second compensation block quadrangular section bulge 11-4 and the first bulge 10-4 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 the 4 pretightening force adjusting nuts 14 through screw holes on the connecting seat 4, the first waist-shaped through holes 11-2 of the second compensating block 11 or the first waist-shaped through holes 10-2 of the first compensating block 10, the second waist-shaped through holes 13-5 on the middle compensating block 13 and the pretightening force adjusting bolt reserved screw holes 5-1 (see figure 5) on the mounting cross beam 5. The lateral adjusting bolt 12 of the compensating mechanism is respectively connected with the lateral adjusting nut 9 of the compensating mechanism in a threaded manner through the round screw hole 11-5 (see fig. 7) of the second compensating block and the round screw hole 10-5 (see fig. 6) of the first compensating block, and is used for adjusting the distance between the first compensating block 10 and the second compensating block 11. The included angle (bottom angle) between the second compensation block inclined plane 11-3 (see fig. 7) and the second compensation block bottom plane 11-1 (see fig. 7), the included angle (bottom angle) between the first compensation block inclined plane 10-3 (see fig. 6) and the first compensation block bottom plane 10-1 (see fig. 6), the included angle (top angle) between the middle compensation block right inclined plane 13-2 (see fig. 8), the included angle (top angle) between the middle compensation block left inclined plane 13-4 (see fig. 8) and the middle compensation block bottom plane 13-1 (see fig. 8) are equal, and the first compensation block 10 can slide laterally or axially through the first waist-shaped through hole 10-2 (see fig. 6) and the second compensation block 11 relative to the pretension adjusting bolt 8 arranged in the first waist-shaped through hole 11-2 (see fig. 7), so as to adjust the threaded connection position of the lateral adjusting bolt 12 of the compensation mechanism and the lateral adjusting nut 9, the first compensation block 10, the second compensation block 11 are close or leave, and the middle compensation block 13 is forced to float up and down, so that the purpose of connecting the top plane between the installation beam 5 and the top beam 4 (see fig. 1) is achieved.
As shown in fig. 3, 9-18, the loading force measuring device B includes: the four-ball-joint type loading device comprises 4 loading pull plate side clamping plates 15,4 loading pull plates 16,4 lower ball-joint connecting bolts 17,4 connecting threaded sleeves 18,4 upper ball-joint connecting bolts 19, a top plate 20, a top rod bolt 21, an adapter joint 22, a load cell 23 and a base 24.
One surface of the 4 loading pull plates 16 with the first spherical concave holes 16-2 (see fig. 10) faces downwards, the other surface is attached to the downward surface of the connecting seat 4, wherein the axis of one of the two loading pull plate cylindrical holes 16-3 (see fig. 10) coincides with the axis of one of the upper ball screw cylindrical holes 20-2 (see fig. 15) on the corresponding angle 3×3 (row×column) of the top plate 20, namely, one of the loading pull plate cylindrical holes 16-3 (see fig. 10) coincides with one of the upper ball screw cylindrical holes 20-2 (see fig. 15) in the 3×3 (row×column) array on the corresponding angle of the top plate 20, and the specific two holes are required to be matched according to the size and shape of the bottom surface of the mounting cross beam 5 and the top surface of the connecting seat 4; the loading pull plates 16 are square, and the adjacent two side surfaces of the loading pull plates 16 facing the outside are respectively provided with a dovetail-shaped second bulge 16-1 (see fig. 10), when the loading pull plates are assembled, the dovetail-shaped second clamping grooves 15-1 (see fig. 9) of each loading pull plate side clamping plate 15 are clamped with the second bulges 16-1 (see fig. 10) of the adjacent two loading pull plates 16 facing the same direction, so that the 4 loading pull plates 16 are limited in the same plane; the lower ball-joint bolt rods 17-3 (see fig. 11) of the 4 lower ball-joint bolts 17 pass through the first spherical concave holes 16-2 (see fig. 10) of the 4 loading pull plates 16 and the loading pull plate cylindrical holes 16-3 (see fig. 10) respectively until the spherical surfaces 17-1 (see fig. 11) of the lower ball-joint bolt heads are attached to the corresponding first spherical concave holes 16-2 (see fig. 10), and the 4 lower ball-joint bolt rods 17-3 (see fig. 11) are screwed with the lower screw holes 18-3 (see fig. 12) of the connecting screw sleeves 18 respectively; the upper screw hole 18-1 (see fig. 12) of the connecting screw sleeve of each connecting screw sleeve 18 is in threaded connection with the upper ball connecting bolt rod part 19-3 (see fig. 13) of the upper ball connecting bolt 19; the upper ball-joint stud shaft 19-3 (see fig. 13) of the upper ball-joint stud 19 engages the upper ball-joint stud spherical concave hole 20-1 (see fig. 15) and the upper ball-joint stud cylindrical hole 20-2 (see fig. 15) through the top plate on the top plate 20 until the upper ball-joint stud head spherical surface 19-1 (see fig. 13) engages the top plate engaging the upper ball-joint stud spherical concave hole 20-1 (see fig. 15); the spherical concave hole 20-1 (see fig. 15) of the upper ball stud matched with the top plate faces away from the cabin door 1, the spherical concave hole 20-3 (see fig. 15) of the upper ball stud matched with the top plate faces the cabin door 1, the hexagonal square head 21-1 (see fig. 16) of the hexagonal cross section of the top stud 21 and the cylindrical hole 20-4 (see fig. 15) of the spherical upper rod part 21-2 (see fig. 16) of the top stud matched with the top stud through the top plate until the spherical body 21-3 (see fig. 16) of the top stud is attached to the spherical concave hole 20-3 (see fig. 15) of the spherical concave hole of the top stud matched with the top plate; the ejector rod bolt screw head 21-4 (see figure 16) is in screw connection with the adapter screw hole 22-2 (see figure 17) in the adapter hexagonal section square head 22-1 (see figure 17) outside the adapter in the adapter 22; the adapter screw head 22-3 (see figure 17) is in screw connection with one end of the force transducer 23; the other end of the force transducer 23 is in threaded connection with a base screw hole 24-1 (see figure 18) in the base 24; the base disc 24-2 (see figure 18) is pressed on the side of the mounting beam 5 facing away from the cabin door 1; the diameter of the loading pulling plate cylinder hole 16-3 (see figure 10) is slightly larger than the outer diameter of the lower ball head connecting bolt rod 17-3 (see figure 11), the diameter of the top plate matched upper ball head screw cylinder hole 20-2 (see figure 15) is slightly larger than the outer diameter of the upper ball head connecting bolt rod part 19-3 (see figure 13), the diameter of the top plate matched top rod screw cylinder hole 20-4 (see figure 15) is slightly larger than the outer diameter of the top rod screw rod part 21-2 (see figure 16), and the parallelism of the top plate 20, the loading pulling plate 16 and the cross beam 5 can be adjusted; the screw thread screwing direction between the connecting screw sleeve 18 and the lower ball connecting bolt 17 is opposite to the screw thread screwing direction between the connecting screw sleeve 18 and the upper ball connecting bolt 19, when the spherical square screwing groove 17-2 (see fig. 11) of the head part of the lower ball connecting bolt and the spherical square screwing groove 19-2 (see fig. 13) of the head part of the upper ball connecting bolt 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 (see fig. 17) outside the adapter is clamped, the hexagonal section square head 21-1 (see fig. 16) of the ejector rod bolt 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 application method of the pre-tightening force adjusting device for installing the aircraft cabin door lock comprises the following steps:
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 arranged 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 installation cross beam 5 and is arranged in a suspending way at a distance (see figure 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, the lateral adjusting bolt 12 is adjusted, and the pretightening force adjusting nut 14 is mounted at the top of the pretightening force adjusting bolt 8 but not screwed, so that no pretightening force is ensured on the pretightening force adjusting bolt 8.
3. The loading force measuring device B is assembled according to the graphical relation of FIG. 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, so that the top plate 20, the loading pull plate 16 and the mounting cross beam 5 are horizontally pressed on the surface of the mounting cross beam 5, which is opposite to the cabin door, the loading pull plate 16 of the loading force measuring device B pulls the connecting seat 4, the hexagonal section square head 22-1 outside the adapter joint and the top plate 20 are fixed, the ejector rod bolt hexagonal section square head 21-1 is screwed, and the force measuring sensor 23 (see FIG. 3) displays that the preset required lock mounting pretightening force value is reached.
4. The preload adjustment nut 14 (see fig. 2) is adjusted until the load cell 23 (see fig. 3) displays zero.
5. And (3) adjusting the compensation mechanism A to fill the suspension space: the lateral adjusting nut 9 of the compensating mechanism and the lateral adjusting bolt 12 of the compensating mechanism are adjusted, so that the first compensating block 10 and the second compensating block 11 are close to each other towards the middle, and the middle compensating block 13 is forced to axially move along the pretightening force adjusting bolt 8 until the top plane of the middle compensating block 13 is attached to the lower surface of the mounting cross beam 5.
6. The loading force measuring device B is removed (the door lock mounting structure after removal is shown in figure 4).
While the invention has been described with reference to certain preferred embodiments, it will be understood by those skilled in the art that various changes and modifications may be made and equivalents may be substituted for elements thereof without departing from the scope of the invention. Therefore, any simple modification, equivalent variation and modification of the above embodiments according to the technical substance of the present invention shall fall within the scope of the technical solution of the present invention.
Claims (10)
1. The installation method of the cabin door lock with the pretightening force of the aircraft comprises the steps of fixedly installing a cabin door and an installation beam on an aircraft body, and fixedly installing the cabin door lock on the cabin door, and is characterized by further comprising the following steps:
the top of the cabin door lock is fixedly provided with a connecting seat, the top surface of the connecting seat is parallel to and separated from the bottom surface of the mounting cross beam by a certain distance, a height-adjustable compensation mechanism is arranged between the top surface of the connecting seat and the bottom surface of the mounting cross beam, and the mounting cross beam and the connecting seat are connected into a whole through a lock mounting pre-tightening force adjusting mechanism with an initial pre-tightening force of 0;
a top plate is arranged on the top surface of the mounting cross beam, a loading pull plate is arranged on the bottom surface of the connecting seat, the top plate is parallel to the loading pull plate and is connected into a whole through a fastener, a loading force adjusting mechanism is vertically arranged in the middle of the top plate, a force transducer is arranged at the bottom of the loading force adjusting mechanism, the force transducer is in abutting connection with the top surface of the mounting cross beam, and the reading of the force transducer is a preset lock mounting pretightening force;
adjusting the lock mounting pretightening force adjusting mechanism to enable the reading of the force transducer to be restored to 0;
the height of the compensation mechanism is adjusted, so that the top surface of the compensation mechanism is attached to the mounting cross beam, and the bottom surface of the compensation mechanism is attached to the top surface of the connecting seat;
and removing the top plate, the loading pulling plate, the loading force adjusting mechanism and the force transducer, and thus completing the pretightening force installation of the cabin door lock.
2. The method for installing the door lock belt of the aircraft cabin according to claim 1, wherein the lock installation pretightening force adjusting mechanism comprises pretightening force adjusting bolts and pretightening force adjusting nuts, the pretightening force adjusting nuts are used for locking after screw rods of the pretightening force adjusting bolts penetrate through the installation cross beam and the connecting seat, and when the reading of the force sensor does not reach the preset lock installation pretightening force, the pretightening force adjusting bolts and the pretightening force adjusting nuts are not used for pretightening force.
3. The installation method of the pre-tightening force of the cabin door lock belt of the aircraft according to claim 2, wherein the compensating mechanism comprises a first compensating block and a second compensating block which are oppositely arranged and separated by a certain distance, opposite surfaces of the first compensating block and the second compensating block are inclined surfaces, the first compensating block and the second compensating block are connected into a whole through a compensating mechanism side adjusting bolt and a compensating mechanism side adjusting nut, an intermediate compensating block is matched and arranged on the opposite surfaces of the first compensating block and the second compensating block, and when the compensating mechanism side adjusting nut and the compensating mechanism side adjusting bolt are adjusted, the first compensating block and the second compensating block are close to each other towards the middle, the intermediate compensating block is forced to axially float along the pre-tightening force adjusting bolt until the top surface of the intermediate compensating block is attached to the bottom surface of the installation cross beam; and when the reading of the force transducer reaches the preset lock installation pretightening force, adjusting the pretightening force adjusting nut to enable the reading of the force transducer to be recovered to 0.
4. The installation method of the pre-tightening force of the cabin door lock belt of the aircraft according to claim 3, wherein a first waist-shaped through hole is vertically arranged on the first compensation block and the second compensation block respectively, the first waist-shaped through hole is parallel to the lateral adjusting bolt of the compensation mechanism, and the installation cross beam, the first waist-shaped through hole on the first compensation block or the second compensation block and the connecting seat are connected into a whole by the lock installation pre-tightening force adjusting mechanism.
5. The installation method of the pre-tightening force of the cabin door lock belt of the aircraft according to claim 3, wherein first protrusions are respectively arranged on opposite surfaces of the first compensation block and the second compensation block, screw holes are horizontally arranged in the first protrusions, first clamping grooves which are in clearance fit with the first protrusions are formed in the bottoms of the middle compensation blocks, and the lateral adjustment bolts of the compensation mechanism horizontally penetrate through the first compensation block and the first protrusions thereof, and are locked by the lateral adjustment nuts of the compensation mechanism after the second compensation block and the first protrusions thereof.
6. The installation method of the pre-tightening force of the cabin door lock belt of the aircraft according to claim 3, wherein the first compensation block and the second compensation block are right trapezoid stretching bodies, the middle compensation block is an isosceles trapezoid stretching body, and the base angle of the first compensation block and the base angle of the second compensation block are equal to the top angle of the middle compensation block.
7. The installation method of the pre-tightening force of the cabin door lock belt of the aircraft according to claim 3, wherein a second waist-shaped through hole is vertically arranged on the middle compensation block, the second waist-shaped through hole is parallel to the lateral adjusting bolt of the compensation mechanism, and the installation cross beam, the first waist-shaped through hole on the first compensation block or the second compensation block, the second waist-shaped through hole of the middle compensation block and the connecting seat are connected into a whole by the lock installation pre-tightening force adjusting mechanism.
8. The installation method of the pre-tightening force of the cabin door lock belt of the aircraft according to claim 1, wherein the loading force adjusting mechanism comprises a push rod bolt, a spherical body is arranged in the middle of the push rod bolt, one end of the push rod bolt penetrates through the top plate, the spherical body is matched with a spherical convex hole arranged on the bottom surface of the top plate, the other end of the push rod bolt is connected with the force sensor through an adapter connector, and when the top plate and the adapter connector are fixed and the push rod bolt is rotated, two ends of the push rod bolt respectively squeeze the top plate and the installation cross beam to enable opposite force to be generated between the installation cross beam and the connecting seat.
9. The method for installing the door lock belt pretightening force of the cabin of the aircraft according to claim 1, wherein the loading pull plates are square, 4 loading pull plates are arranged, dovetail-shaped second protrusions are arranged on two adjacent lateral surfaces of each loading pull plate facing to the outer side, the 4 loading pull plates are connected end to end, the second protrusions of two adjacent loading pull plates facing to the same direction are clamped into dovetail-shaped second clamping grooves of a clamping plate on the lateral surface of one loading pull plate, and the 4 loading pull plates are limited in the same plane.
10. The method for installing the door lock belt pretightening force of the cabin of the aircraft according to claim 1, wherein an upper ball connecting bolt is installed on the top plate, a lower ball connecting bolt is installed on the loading pulling plate, the upper ball connecting bolt is connected with the lower ball connecting bolt through a connecting screw sleeve, threads are respectively arranged at two ends of the connecting screw sleeve, and the threads of the threads at two ends of the connecting screw sleeve are opposite in screwing direction.
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| CN202110490395.8A CN113148223B (en) | 2021-05-06 | 2021-05-06 | Installation method for door lock belt pretightening force of aircraft cabin |
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| CN202110490395.8A CN113148223B (en) | 2021-05-06 | 2021-05-06 | Installation method for door lock belt pretightening force of aircraft cabin |
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| CN113148223A CN113148223A (en) | 2021-07-23 |
| CN113148223B true CN113148223B (en) | 2023-11-28 |
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| Application Number | Title | Priority Date | Filing Date |
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| FR3043058A1 (en) * | 2015-11-03 | 2017-05-05 | Latecoere | AIRCRAFT EMERGENCY EXIT DOOR WITH INTEGRATED MECHANISMS AND METHOD OF OPENING / CLOSING SUCH A DOOR |
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| GB868390A (en) * | 1958-07-04 | 1961-05-17 | Vickers Aircraft Holdings Ltd | Improvements in doors for pressurized fuselages of aircraft |
| DE19730918A1 (en) * | 1997-07-18 | 1999-01-21 | Daimler Benz Aerospace Airbus | Aircraft cabin door locking system |
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| CN203497167U (en) * | 2013-08-30 | 2014-03-26 | 中航飞机起落架有限责任公司 | Link mechanism of undercarriage and cabin door |
| CN103982101A (en) * | 2014-05-16 | 2014-08-13 | 上海宇航***工程研究所 | Locking-unlocking screw and cabin door unlocking device |
| EP3401208A1 (en) * | 2017-05-10 | 2018-11-14 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | An aircraft door with at least one weight compensation device |
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| Publication number | Publication date |
|---|---|
| CN113148223A (en) | 2021-07-23 |
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