CN114771872B - Static load loading system and method in high-temperature thermal strength test for aerospace plane test - Google Patents
Static load loading system and method in high-temperature thermal strength test for aerospace plane test Download PDFInfo
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- CN114771872B CN114771872B CN202210708790.3A CN202210708790A CN114771872B CN 114771872 B CN114771872 B CN 114771872B CN 202210708790 A CN202210708790 A CN 202210708790A CN 114771872 B CN114771872 B CN 114771872B
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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
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M99/00—Subject matter not provided for in other groups of this subclass
- G01M99/002—Thermal testing
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M99/00—Subject matter not provided for in other groups of this subclass
- G01M99/005—Testing of complete machines, e.g. washing-machines or mobile phones
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M99/00—Subject matter not provided for in other groups of this subclass
- G01M99/007—Subject matter not provided for in other groups of this subclass by applying a load, e.g. for resistance or wear testing
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Abstract
The invention discloses a static load loading system and a method thereof in a high-temperature thermal strength test for testing an aerospace plane, belonging to the technical field of plane testing, wherein the static load loading system comprises a bracket, an actuator clamped on the bracket and a static load loading assembly arranged on the actuator; the bracket comprises a base, a supporting rod clamped on the base and a limiting disc arranged above the base and connected with the supporting rod; the bottom end of the actuator is clamped on the base, and the top end of the actuator penetrates through the limiting disc and is provided with a threaded hole; the static load loading assembly comprises a loading rod, a quartz glass bottom plate and a connecting screw rod, wherein one end of the loading rod is connected with the threaded hole through an external thread connector, the other end of the loading rod is provided with an internal thread counter bore, the quartz glass bottom plate is clamped at the end part of the loading rod, and the connecting screw rod penetrates through the quartz glass plate and is connected with the internal thread counter bore; the static load loading system is reasonable in structural design, reliability and stability of a high-temperature thermal strength test of the aerospace plane can be improved, and loading precision of thermal load in the test process can be improved.
Description
Technical Field
The invention relates to the technical field of airplane testing, in particular to a static load loading system and method in a high-temperature thermal strength test for testing an aerospace airplane.
Background
The airplane high-temperature thermal strength test is a key step of an airplane structure test, the airplane high-temperature thermal strength test can observe and research the mechanical property and the damage resistance of an airplane structure or a member in a thermal environment, a thermal load environment equivalent to the actual flight process needs to be simulated on the ground in the test process, a heat transfer test, a heat prevention and insulation test, an ablation ground simulation test, a creep test and the like of the structure heat transfer characteristic are researched besides static force, power and fatigue tests carried out in the thermal environment, and the heating mode is divided into a convection heating mode and a non-convection heating mode according to the difference of the thermal environment simulation modes.
In the prior art, when an airplane high-temperature thermal strength test is carried out, a jacking type static load loading mode is generally adopted, alloy steel or 304 stainless steel is generally adopted as a joint at the end part of a loading rod, and a layer of high silica fiber cloth is wrapped outside the joint.
However, in the process of the high-temperature hot strength test of the aircraft, the alloy steel or 304 stainless steel joint can shield the radiant heating of the test piece, so after the test is finished, an obvious unheated area can be generated on the surface of the test piece, and the precision of the high-temperature hot strength test of the aircraft is seriously influenced.
Disclosure of Invention
Aiming at the technical problems, the invention provides a static load loading system and a static load loading method in a high-temperature thermal strength test for testing an aerospace plane.
The technical scheme of the invention is as follows: the static load loading system in the high-temperature thermal strength test for the aerospace plane test comprises a bracket, an actuator movably clamped on the bracket and a static load loading assembly in threaded connection with the actuator; the bracket comprises a base, a plurality of support rods movably clamped on the base and limit discs arranged above the base and respectively fixedly connected with the upper end parts of the support rods; an adjusting groove is horizontally arranged on the base, an adjusting screw rod is rotationally clamped in the adjusting groove, and a micro motor for providing power for the adjusting screw rod is arranged on the upper end face of the base; a strip-shaped through groove is formed in the limiting disc;
the bottom end of the actuator is slidably clamped with a compensation sleeve, the bottom end of the compensation sleeve is movably hinged with a thread moving seat, the actuator is in threaded connection with the adjusting screw rod through the thread moving seat, the top end of the actuator penetrates through the strip-shaped through groove and is provided with a threaded hole, and a rotating shaft rotationally clamped with the inner wall of the strip-shaped through groove is arranged on the side wall of the actuator;
the static load loading assembly comprises a loading rod, a quartz glass bottom plate and a connecting screw rod, wherein one end of the loading rod is provided with an external thread joint in threaded connection with the threaded hole, and the other end of the loading rod is provided with an internal thread counter bore; a through hole penetrates through the center of the quartz glass bottom plate, the upper end surface and the lower bottom surface of the quartz glass bottom plate are respectively provided with a hidden counter bore and a clamping hole which are communicated with the through hole, and the quartz glass bottom plate is movably clamped with one end of the loading rod, which is provided with an internal thread counter bore, through the clamping hole; and the connecting screw rod is inserted into the through hole and then is in threaded connection with the internal thread counter bore, and the top end of the connecting screw rod is positioned inside the hidden counter bore.
Furthermore, a rotating disc is rotatably clamped on the upper end face of the base, the adjusting lead screw and the micro motor are both arranged on the rotating disc, an annular clamping groove is formed in the upper end face of the base and located on the outer side of the rotating disc, and a rotating roller movably clamped with the annular clamping groove is rotatably clamped at the bottom end of each supporting rod; the supporting rod capable of rotating in the annular clamping groove is used for conveniently carrying out multidirectional adjustment on the load loading angle of the actuator, so that the comprehensiveness of a high-temperature thermal strength test in the aerospace plane test can be improved.
Furthermore, the loading rod comprises a high-temperature section and a heat dissipation section fixedly connected with the high-temperature section, the heat dissipation section comprises two connecting discs and a plurality of heat dissipation guide rods uniformly distributed between the two connecting discs, the external thread connector is arranged at the bottom end of the connecting disc far away from the high-temperature section, and the internal thread counter bore is arranged at the top end of the high-temperature section; through setting up the loading pole that is formed by connecting high temperature section and heat dissipation section, utilize the heat dissipation guide arm of heat dissipation section to carry out separation heat dissipation to the heat that the high temperature section produced and handle, avoid high temperature to influence the actuator and exert the static load of test piece.
Furthermore, a limiting sleeve is arranged on the lower bottom surface of the quartz glass bottom plate and positioned outside the clamping hole, a plurality of limiting grooves are uniformly distributed at the lower end of the limiting sleeve, and a plurality of limiting columns movably clamped with the limiting grooves are arranged on the outer wall of the loading rod; the quartz glass bottom plate is provided with the limiting sleeve which can be clamped with the limiting column, so that the stability of the quartz glass plate when the quartz glass plate is connected with the loading rod is improved, and the continuous and efficient performance of a high-temperature thermal strength test in the aerospace plane test is promoted.
Furthermore, a connecting disc is fixedly sleeved outside the external thread joint, and a plurality of rotary locking columns which are rotationally clamped with the connecting disc are uniformly distributed on the lower bottom surface of the connecting disc in the circumferential direction; the top end of the outer side wall of the actuator is provided with an annular boss, a locking sleeve is slidably clamped in the actuator and penetrates through the upper end face of the annular boss, a plurality of arc-shaped locking grooves capable of being movably clamped with the rotary locking column are uniformly distributed in the circumferential direction of the locking sleeve, and a push rod connected with the locking sleeve is slidably clamped on the side wall of the actuator; the clamping effect of utilizing rotatory lock post and locking cover can improve the connection reliability of loading pole and actuator, avoids the loading pole to bear the vibration and drop in lasting static load application process.
Furthermore, a compression spring is arranged between the locking sleeve and the inner wall of the actuator, and the push rod is in threaded connection with the locking sleeve; through setting up compression spring, the locking cover can remove along annular boss under compression spring's effect when loosening the catch bar to final and the automatic joint locking of rotatory lock post, greatly shortened the equipment time of aircraft high temperature heat intensity test in-process system.
Furthermore, an inserting hole is formed in the connecting screw, an anti-falling groove is formed in the upper end of the inner wall of the inserting hole, an installation sleeve capable of being movably inserted into the inserting hole is arranged in the inner thread counter bore, a plurality of driving grooves are formed in the side wall of the installation sleeve corresponding to the anti-falling groove in position, a plurality of anti-falling fixture blocks are clamped in the installation sleeve in a rotating mode through driving a rotating rod, and the anti-falling fixture blocks correspond to the anti-falling grooves on the corresponding sides one to one; the lower end of the outer part of each driving rotating rod is sleeved with a driving gear, the bottom in the mounting sleeve is rotatably clamped with a main gear in meshed connection with each driving gear, the bottom end of the main gear is fixedly connected with a pinion, a sector toothed plate in meshed connection with the pinion is movably hinged in the loading rod, a pushing plate fixedly connected with the sector toothed plate penetrates through the side wall of the loading rod, and a sector swinging groove for providing a moving space for the pushing plate is arranged in the loading rod; the fan-shaped toothed plate is shifted by the pushing plate to rotate, the main gear drives each driving gear to rotate under the meshing action of the fan-shaped toothed plate and the auxiliary gear, so that each anti-falling clamping block is clamped with the anti-falling groove in the connecting screw rod after penetrating through the driving groove on the corresponding side in the rotating process of the driving rotating rod, the locking of the connecting screw rod is realized, and the generation of the surface heating defects of the test piece in the high-temperature thermal strength test process of the aerospace plane is avoided.
Furthermore, a fixed disk is sleeved on the outer wall of the base, and a plurality of mounting holes are arranged on the fixed disk in a penetrating manner; the fixing disc is arranged, so that the system and the bearing wall can be fixed conveniently, and the reliability of the system in the operation process is improved.
Further, the loading rod and the connecting screw rod are both made of high-temperature-resistant alloy steel materials; the loading rod and the connecting screw rod which are made of high-temperature-resistant alloy steel materials are used, so that the service lives of the loading rod and the connecting screw rod are prolonged, and the system maintenance cost of the high-temperature thermal strength test of the airplane is reduced.
The invention also provides a static load loading method in the high-temperature thermal strength test for testing the aerospace plane, which comprises the following steps:
s1, respectively connecting the micro motor and the actuator with an external power supply;
s2, adjusting the load loading angle of the actuator according to the loading requirement of the static load in the high-temperature thermal strength test of the aerospace plane, then starting the micro motor, and driving the adjusting screw rod to rotate by using the micro motor, so that the thread moving seat moves in the adjusting groove, the bottom end of the actuator moves along with the thread moving seat under the action of the compensation sleeve, and the top end of the actuator swings in the strip-shaped through groove on the limiting disc;
s3, after the load loading angle of the actuator is adjusted, connecting the loading rod with a threaded hole at the top end of the actuator in a threaded manner by using an external thread connector, then clamping the quartz glass bottom plate at the top end of the loading rod through a clamping hole, finally inserting a connecting screw rod into the through hole and then connecting the connecting screw rod with an internal thread counter bore on the loading rod, and enabling the top end of the connecting screw rod to be positioned in the hidden counter bore;
and S4, starting the actuator, and loading the static load in the high-temperature thermal strength test of the aerospace plane.
Compared with the prior art, the beneficial effects of the invention are embodied in the following points:
firstly, the static load loading system is reasonable in structural design, and the static load application direction of the actuator is adjusted by utilizing the support, so that the loading rod can apply static loads at different angles to the airplane, and the comprehensiveness and reliability of a high-temperature and high-temperature heat strength test in the airplane test are improved;
secondly, the static load loading system utilizes the quartz glass bottom plate as a medium for applying the static load between the loading rod and the test piece, and the quartz glass bottom plate is made of a transparent material, so that the area of an unheated area on the surface of the test piece is effectively reduced in the process of carrying out the high-temperature and high-temperature strength test of the airplane, and the precision of the high-temperature and high-temperature strength test in the airplane test is improved;
thirdly, the static load loading system has the advantages of convenience in adjustment and assembly and low maintenance cost, and the support, the actuator and the static load loading assembly support are high in connection stability, so that reliable equipment support is provided for a high-temperature thermal strength test in an airplane test, and the static load loading system has a promoting significance for testing and researching the safety of the aerospace airplane structure.
Drawings
FIG. 1 is a flow chart of a dead load method of the present invention;
FIG. 2 is a longitudinal section of the invention;
FIG. 3 is a front view of the present invention;
FIG. 4 is a top view of the present invention;
FIG. 5 is a schematic view of the connection of the rotary plate of the present invention to a base;
FIG. 6 is an enlarged, fragmentary, schematic view at A of FIG. 2 of the present invention;
FIG. 7 is a schematic view of the rotary lock cylinder of the present invention coupled to a locking sleeve;
FIG. 8 is a schematic structural diagram of the deadweight loading assembly of the present invention;
FIG. 9 is a view of the heat sink guide of the present invention positioned on a connecting disk;
FIG. 10 is a distribution diagram of the anti-falling fixture block of the present invention inside the installation sleeve;
figure 11 is a schematic view of the connection of the toothed sector plate with the pinion of the present invention;
FIG. 12 is an enlarged, fragmentary, schematic view at B of FIG. 8 of the present invention;
FIG. 13 is an enlarged, fragmentary, schematic view at C of FIG. 8 of the present invention;
wherein, 1-bracket, 10-base, 100-regulating groove, 101-regulating screw rod, 102-micro motor, 11-supporting rod, 110-rotating roller, 12-limiting disc, 120-strip through groove, 13-rotating disc, 14-annular clamping groove, 15-fixing disc, 150-mounting hole, 2-actuator, 20-compensation sleeve, 21-thread moving seat, 22-threaded hole, 23-rotating shaft, 24-annular boss, 25-locking sleeve, 250-arc locking groove, 251-push rod, 252-compression spring, 3-static loading component, 30-loading rod, 300-external thread joint, 301-internal thread counter bore, 31-quartz glass base plate, 310-through hole, 311-hidden counter bore, 312-clamping hole, 32-connecting screw rod, 320-plug hole, 321-anti-falling groove, 33-high temperature section, 34-heat dissipation section, 340-connecting disc, 341-heat dissipation guide rod, 35-limiting sleeve, 350-limiting groove, 351-limiting column, 36-connecting disc, 360-rotary locking column, 37-mounting sleeve, 370-driving groove, 371-driving rotating rod, 372-anti-falling clamping block, 373-driving gear, 374-main gear, 3740-auxiliary gear, 375-sector toothed plate, 376-pushing plate and 3760-sector swinging groove.
Detailed Description
Example 1
The static load loading system in the high-temperature thermal strength test for the aerospace plane test, which is shown in fig. 2, 3, 4 and 5, comprises a bracket 1, an actuator 2 movably clamped on the bracket 1 and a static load loading assembly 3 in threaded connection with the actuator 2; the support 1 comprises a base 10, 4 support rods 11 movably clamped on the base 10 and a limiting disc 12 arranged above the base 10 and respectively fixedly connected with the upper end parts of the support rods 11; an adjusting groove 100 is horizontally arranged on the base 10, an adjusting screw 101 is rotatably clamped in the adjusting groove 100, and a micro motor 102 for providing power for the adjusting screw 101 is arranged on the upper end surface of the base 10; a strip-shaped through groove 120 is formed in the limiting disc 12;
as shown in fig. 2, 4 and 6, the bottom end of the actuator 2 is slidably clamped with a compensation sleeve 20, the bottom end of the compensation sleeve 20 is movably hinged with a thread moving seat 21, the actuator 2 is in threaded connection with an adjusting screw 101 through the thread moving seat 21, the top end of the actuator 2 penetrates through a strip-shaped through groove 120 and is provided with a threaded hole 22, and a rotating shaft 23 rotationally clamped with the inner wall of the strip-shaped through groove 120 is arranged on the side wall of the actuator 2; the actuator 2 and the micro motor 102 are both commercially available products and are powered by an external power supply;
as shown in fig. 2, 8, 9 and 12, the static loading assembly 3 includes a loading rod 30, a quartz glass base plate 31 and a connecting screw rod 32, the loading rod 30 includes a high temperature section 33 and a heat dissipation section 34 fixedly connected with the high temperature section 33, the heat dissipation section 34 includes two connecting disks 340 and 7 heat dissipation guide rods 341 uniformly distributed between the two connecting disks 340, the bottom end of the connecting disk 340 far away from the high temperature section 33 is provided with an external screw joint 300, and the top end of the high temperature section 33 is provided with an internal screw counterbore 301; a through hole 310 penetrates through the center of the quartz glass bottom plate 31, a hidden counter bore 311 and a clamping hole 312 which are communicated with the through hole 310 are respectively arranged on the upper end surface and the lower bottom surface of the quartz glass bottom plate 31, and the quartz glass bottom plate 31 is movably clamped with the high-temperature section 33 through the clamping hole 312; the connecting screw rod 32 is inserted into the through hole 310 and then is in threaded connection with the internal thread counter bore 301, the top end of the connecting screw rod 32 is located inside the hidden counter bore 311, and the loading rod 30 and the connecting screw rod 32 are both made of high-temperature-resistant alloy steel materials.
Example 2
The embodiment describes a loading method of a static loading system in a high-temperature thermal strength test for testing an aerospace plane in embodiment 1, which includes the following steps:
s1, connecting the micro motor 102 and the actuator 2 with an external power supply respectively;
s2, adjusting the load loading angle of the actuator 2 according to the loading requirement of the static load in the aerospace plane high-temperature thermal strength test, then starting the micro motor 102, and driving the adjusting screw 101 to rotate by using the micro motor 102, so that the thread moving seat 21 moves in the adjusting groove 100, at the moment, the bottom end of the actuator 2 moves along with the thread moving seat 21 under the action of the compensation sleeve 20, and the top end of the actuator 2 swings in the strip-shaped through groove 120 on the limiting disc 12;
s3, after the load loading angle of the actuator 2 is adjusted, connecting the loading rod 30 with the threaded hole 22 at the top end of the actuator 2 through the external thread connector 300 in a threaded manner, then clamping the quartz glass bottom plate 31 at the top end of the loading rod 30 through the clamping hole 312, finally inserting the connecting screw rod 32 into the through hole 310 and then connecting the connecting screw rod with the internal thread counter bore 301 on the loading rod 30, and enabling the top end of the connecting screw rod 32 to be located in the hidden counter bore 311;
and S4, starting the actuator 2, and carrying out loading of the static load in the aerospace plane high-temperature thermal strength test.
Example 3
The present embodiment is different from embodiment 1 in that:
as shown in fig. 2 and 5, the upper end surface of the base 10 is rotatably clamped with a rotating disk 13, the adjusting screw 101 and the micro motor 102 are both arranged on the rotating disk 13, an annular clamping groove 14 is arranged on the upper end surface of the base 10 and on the outer side of the rotating disk 13, and the bottom end of each support rod 11 is rotatably clamped with a rotating roller 110 movably clamped with the annular clamping groove 14;
the outer wall of the base 10 is sleeved with a fixed disk 15, and 6 mounting holes 150 are arranged on the fixed disk 15 in a penetrating mode.
Example 4
The present embodiment describes a loading method of a static loading system in a high-temperature thermal strength test for testing an aerospace plane in embodiment 3, which is different from embodiment 2 in that:
in step S2, the base 10 is first fixed on the load-bearing wall by the fixing plate 15, and when the load-loading angle of the actuator 2 is adjusted, the supporting rod 11 is pushed, so that the rotating roller 110 at the bottom end of the supporting rod 11 rotates in the ring-shaped slot 14, and at this time, the actuator 2 rotates synchronously with the supporting rod 11, so as to realize multi-directional adjustment of the static load-loading angle of the actuator 2.
Example 5
The present embodiment is different from embodiment 1 in that:
as shown in fig. 3 and 8, a limiting sleeve 35 is disposed on the lower bottom surface of the quartz glass bottom plate 31 and outside the clamping hole 312, 4 limiting grooves 350 are uniformly distributed on the lower end of the limiting sleeve 35, and 4 limiting posts 351 movably clamped with the limiting grooves 350 are disposed on the outer wall of the loading rod 30.
Example 6
The present embodiment describes a loading method of a static loading system in a high-temperature thermal strength test for testing an aerospace plane in embodiment 5, which is different from that in embodiment 2 in that:
in step S3, after the quartz glass bottom plate 31 is clamped to the top end of the loading rod 30 through the clamping hole 312, the position-limiting sleeve 35 is movably clamped to the position-limiting post 351 on the outer wall of the loading rod 30 through the position-limiting groove 350 at the lower end thereof.
Example 7
The present embodiment is different from embodiment 1 in that:
as shown in fig. 6, 7 and 8, the connection disc 36 is fixedly sleeved outside the male connector 300, and 8 rotary locking columns 360 which are rotatably clamped with the connection disc 36 are uniformly distributed on the lower bottom surface of the connection disc 36 in the circumferential direction; the top end of the outer side wall of the actuator 2 is provided with an annular boss 24, a locking sleeve 25 is slidably clamped in the actuator 2, the locking sleeve 25 penetrates through the upper end face of the annular boss 24, 8 arc-shaped locking grooves 250 capable of being movably clamped with a rotary locking column 360 are uniformly distributed in the circumferential direction of the locking sleeve 25, and a push rod 251 connected with the locking sleeve 25 is slidably clamped on the side wall of the actuator 2; a compression spring 252 is arranged between the locking sleeve 25 and the inner wall of the actuator 2, and the push rod 251 is in threaded connection with the locking sleeve 25.
Example 8
The present embodiment describes a loading method of a static loading system in a high-temperature thermal strength test for testing an aerospace plane in embodiment 7, which is different from that in embodiment 2 in that:
in step S3, after the loading rod 30 is screwed into the threaded hole 22 at the top end of the actuator 2 through the male connector 300, the pushing rod 251 is loosened, the locking sleeve 25 moves upward along the annular boss 24 under the action of the compression spring 252, and the locking sleeve 25 is automatically locked with the rotary lock cylinder 360 through the arc-shaped locking groove 250 on the locking sleeve 25.
Example 9
The present embodiment is different from embodiment 1 in that:
as shown in fig. 10, 11, 12, and 13, an insertion hole 320 is provided inside the connection screw 32, an anti-falling groove 321 is provided at an upper end of an inner wall of the insertion hole 320, an installation sleeve 37 capable of being movably inserted into the insertion hole 320 is provided inside the female-thread counter bore 301, 3 driving grooves 370 are provided on a side wall of the installation sleeve 37 corresponding to the anti-falling groove 321, 3 anti-falling blocks 372 are rotatably clamped inside the installation sleeve 37 by driving a rotating rod 371, and each anti-falling block 372 corresponds to the anti-falling groove 321 on a corresponding side one by one; the lower end of the outer portion of each driving rotary rod 371 is sleeved with a driving gear 373, the bottom of the mounting sleeve 37 is rotatably clamped with a main gear 374 engaged and connected with each driving gear 373, the bottom of the main gear 374 is fixedly connected with a pinion 3740, the inner portion of the loading rod 30 is movably hinged with a sector toothed plate 375 engaged and connected with the pinion 3740, a pushing plate 376 fixedly connected with the sector toothed plate 375 is arranged on the side wall of the loading rod 30 in a penetrating mode, and a sector swing groove 3760 providing a moving space for the pushing plate 376 is arranged inside the loading rod 30.
Example 10
The present embodiment describes a loading method of a static loading system in a high-temperature thermal strength test for testing an aerospace plane in embodiment 9, which is different from that in embodiment 2 in that:
in step S3, after the connecting screw rod 32 is connected to the female-threaded counterbore 301 of the loading rod 30, the pushing plate 376 is used to toggle the sector-shaped toothed plate 375 to rotate, and the main gear 374 drives each driving gear 373 to rotate by the meshing action of the sector-shaped toothed plate 375 and the secondary gear 3740, so that each anti-falling-off block 372 passes through the driving groove 370 on the corresponding side during the rotation of the driving rotating rod 371 and then is in clamping connection with the anti-falling-off groove 321 on the connecting screw rod 32, thereby locking the connecting screw rod 32.
Claims (8)
1. The static load loading system in the high-temperature thermal strength test for the aerospace plane test is characterized by comprising a support (1), an actuator (2) movably clamped on the support (1) and a static load loading assembly (3) in threaded connection with the actuator (2); the support (1) comprises a base (10), a plurality of support rods (11) movably clamped on the base (10) and a limiting disc (12) arranged above the base (10) and respectively fixedly connected with the upper end parts of the support rods (11); an adjusting groove (100) is horizontally arranged on the base (10), an adjusting screw rod (101) is rotationally clamped in the adjusting groove (100), and a micro motor (102) for providing power for the adjusting screw rod (101) is arranged on the upper end face of the base (10); a strip-shaped through groove (120) is formed in the limiting disc (12);
the bottom end of the actuator (2) is connected with a compensation sleeve (20) in a sliding and clamping mode, the bottom end of the compensation sleeve (20) is movably hinged with a thread moving seat (21), the actuator (2) is in threaded connection with an adjusting lead screw (101) through the thread moving seat (21), the top end of the actuator (2) penetrates through the strip-shaped through groove (120) and is provided with a threaded hole (22), and a rotating shaft (23) which is connected with the inner wall of the strip-shaped through groove (120) in a rotating and clamping mode is arranged on the side wall of the actuator (2);
the static load loading assembly (3) comprises a loading rod (30), a quartz glass bottom plate (31) and a connecting screw rod (32), wherein one end of the loading rod (30) is provided with an external thread joint (300) in threaded connection with the threaded hole (22), and the other end of the loading rod is provided with an internal thread counter bore (301); a through hole (310) penetrates through the center of the quartz glass bottom plate (31), a hidden counter bore (311) and a clamping hole (312) which are communicated with the through hole (310) are respectively formed in the upper end surface and the lower bottom surface of the quartz glass bottom plate (31), and the quartz glass bottom plate (31) is movably clamped with one end, provided with an internal thread counter bore (301), of the loading rod (30) through the clamping hole (312); the connecting screw rod (32) is inserted into the through hole (310) and then is in threaded connection with the internal thread counter bore (301), and the top end of the connecting screw rod (32) is positioned in the hidden counter bore (311);
load pole (30) including high temperature section (33) and with high temperature section (33) fixed connection's heat dissipation section (34), heat dissipation section (34) include two connect disc (340) and several evenly distributed two connect heat dissipation guide arm (341) between disc (340), external screwed joint (300) set up and are keeping away from high temperature section (33) connect disc (340) bottom, internal thread counter bore (301) set up on high temperature section (33) top.
2. The static loading system for the high-temperature thermal strength test of the aerospace plane test is characterized in that a rotating disc (13) is rotatably clamped on the upper end face of the base (10), the adjusting lead screw (101) and the micro motor (102) are arranged on the rotating disc (13), an annular clamping groove (14) is formed in the upper end face of the base (10) and located on the outer side of the rotating disc (13), and a rotating roller (110) movably clamped with the annular clamping groove (14) is rotatably clamped at the bottom end of each supporting rod (11).
3. The static loading system for the high-temperature thermal strength test of the aerospace plane test according to claim 1, wherein a limiting sleeve (35) is arranged on the lower bottom surface of the quartz glass bottom plate (31) and outside the clamping hole (312), a plurality of limiting grooves (350) are uniformly distributed at the lower end of the limiting sleeve (35), and a plurality of limiting columns (351) movably clamped with the limiting grooves (350) are arranged on the outer wall of the loading rod (30).
4. The static load loading system in the high-temperature thermal strength test for the test of the aerospace plane as claimed in claim 1, wherein a connecting disc (36) is fixedly sleeved outside the male connector (300), and a plurality of rotary lock columns (360) which are rotatably clamped with the connecting disc (36) are uniformly distributed on the lower bottom surface of the connecting disc (36) in the circumferential direction; actuator (2) lateral wall top is provided with annular boss (24), and the inside slip joint of actuator (2) has locking cover (25), locking cover (25) can run through annular boss (24) up end, the circumference evenly distributed of locking cover (25) have the several can with arc locking groove (250) of rotatory lock post (360) activity joint, slip joint has catch bar (251) of being connected with locking cover (25) on the actuator (2) lateral wall.
5. The system for loading the static load in the high-temperature heat intensity test for the test of the aerospace plane as claimed in claim 4, wherein a compression spring (252) is arranged between the locking sleeve (25) and the inner wall of the actuator (2), and the push rod (251) is in threaded connection with the locking sleeve (25).
6. The static load loading system in the high-temperature thermal strength test for the test of the aerospace plane as claimed in claim 1, wherein an insertion hole (320) is formed in the connecting screw (32), an anti-drop groove (321) is formed in the upper end of the inner wall of the insertion hole (320), a mounting sleeve (37) capable of being movably inserted into the insertion hole (320) is formed in the inner threaded counter bore (301), a plurality of driving grooves (370) are formed in the side wall of the mounting sleeve (37) corresponding to the anti-drop groove (321), a plurality of anti-drop fixture blocks (372) are rotationally clamped in the mounting sleeve (37) through driving rotating rods (371), and the anti-drop fixture blocks (372) correspond to the anti-drop grooves (321) on the corresponding sides one to one; all the cover of the outside lower extreme of each drive bull stick (371) is equipped with drive gear (373), and the bottom rotates the joint in installation sleeve (37) have with each main gear (374) that drive gear (373) meshing is connected, main gear (374) bottom fixedly connected with pinion (3740), loading arm (30) inside activity hinge have with sector toothed plate (375) that pinion (3740) meshing is connected, run through on loading arm (30) lateral wall be provided with sector toothed plate (375) fixed connection's pushing ram (376), loading arm (30) inside be provided with for the sector swing groove (3760) that pushing ram (376) provided the removal space.
7. The static loading system for the high-temperature thermal strength test of the aerospace plane test according to claim 1, wherein a fixed plate (15) is sleeved on the outer wall of the base (10), and a plurality of mounting holes (150) are formed in the fixed plate (15) in a penetrating mode.
8. The method for loading the static loading system in the high-temperature heat intensity test for the test of the aerospace plane according to any one of claims 1 to 7, comprising the following steps:
s1, connecting the micro motor (102) and the actuator (2) with an external power supply respectively;
s2, adjusting the load loading angle of the actuator (2) according to the loading requirement of a static load in a high-temperature thermal strength test of the aerospace plane, then starting the micro motor (102), and driving the adjusting screw rod (101) to rotate by using the micro motor (102), so that the thread moving seat (21) moves in the adjusting groove (100), at the moment, the bottom end of the actuator (2) moves along with the thread moving seat (21) under the action of the compensation sleeve (20), and the top end of the actuator (2) swings in the strip-shaped through groove (120) on the limiting disc (12);
s3, after the load loading angle of the actuator (2) is adjusted, connecting the loading rod (30) with a threaded hole (22) at the top end of the actuator (2) in a threaded manner by using an external thread connector (300), then clamping the quartz glass bottom plate (31) at the top end of the loading rod (30) through a clamping hole (312), finally inserting the connecting screw rod (32) into the through hole (310) and then connecting the connecting screw rod with an internal thread counter bore (301) on the loading rod (30), and enabling the top end of the connecting screw rod (32) to be located inside the hidden counter bore (311);
s4, starting the actuator (2), and loading the static load in the high-temperature thermal strength test of the aerospace plane.
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| CN110411722A (en) * | 2019-07-26 | 2019-11-05 | 中国航发沈阳发动机研究所 | A kind of structural static and fatigue experimental device |
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| CN104019970B (en) * | 2014-05-20 | 2016-05-11 | 北京航空航天大学 | A kind of pilot system of testing helicopter tail rotor fatigue behaviour |
| CN106240841B (en) * | 2016-07-07 | 2019-01-18 | 中国飞机强度研究所 | A kind of gear test loading device |
| CN106347635B (en) * | 2016-11-01 | 2018-01-02 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of plane lease loads loading device |
| CN210761369U (en) * | 2019-09-29 | 2020-06-16 | 深圳市赛为智能股份有限公司 | Many rotor unmanned aerial vehicle testing arrangement |
| US11460373B2 (en) * | 2020-09-04 | 2022-10-04 | Pratt & Whitney Canada Corp. | Portable test stand for aircraft engines |
| CN214029205U (en) * | 2020-12-21 | 2021-08-24 | 重庆恩斯特龙通用航空技术研究院有限公司 | Full-mechanical static test device suitable for light-duty general aircraft |
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