Reciprocating and torsion integrated aviation hydraulic system test device and its use method

Abstract

The invention relates to an integrated reciprocating and torsion aviation hydraulic system test device and its use method, belonging to the field of hydraulic system test technology. A base is provided on one side of the test bench, a placement plate is provided on the base, a hydraulic system guide rod is provided on the placement plate, an inner mounting seat and an outer mounting seat are fixedly connected to the outside of the hydraulic system guide rod, the upper end of the placement plate is screwed to a locking screw, the head end of the locking screw is arranged against the end face of the outer mounting seat, the hydraulic system guide rod is connected to the output shaft of the linear motor, the linear motor is mounted on the motor bracket, and the motor bracket is connected to the other side of the test bench. The present invention can effectively detect the wear, leakage and friction resistance performance of the aviation hydraulic system in the reciprocating and torsion states. The reciprocating and torsion states can be quickly switched, the operation is simple and convenient, and the integration of the two tests is realized, which improves the test efficiency and reduces the test cost. At the same time, it ensures the smooth operation of the motion mechanism during the test and avoids the occurrence of jamming.

Description

Technical Field

[0001] The invention relates to a reciprocating and torsion integrated aviation hydraulic system test device and a use method thereof, belonging to the technical field of hydraulic system testing. Background Art

[0002] Wear, leakage, and friction resistance testing are essential components of the inspection process for aviation hydraulic system products. These tests often require simulating the product's operating conditions under various operating conditions, such as reciprocating or torsional conditions, to ensure its reliability and stability in real-world applications. However, current testing equipment on the market generally faces a limitation: it can only perform either reciprocating or torsional testing. Switching between test types often requires replacing the entire tester, which not only increases the complexity and time required for testing but also introduces additional errors due to frequent equipment changes.

[0003] Furthermore, existing test motion mechanisms, whether performing reciprocating or torsional tests, often have design flaws that can easily lead to jamming. This jamming not only disrupts the smooth progress of the test but can also damage the test equipment, increasing operating costs and maintenance burdens for the company. Summary of the Invention

[0004] In order to solve the problems existing in the background technology, the present invention provides a reciprocating and torsion integrated aviation hydraulic system test device and a use method thereof.

[0005] The cam is fixedly mounted on a support frame, and the cam is secured to a position 56° about the support frame, wherein the cam is secured to a position 56° about the support frame.

[0006] The two outer mounting seats are symmetrically arranged, the inner end of each outer mounting seat is provided with a stepped hole, and the outer end of each outer mounting seat is provided with an outer mounting seat leakage detection groove.

[0007] The left and right ends of the inner mounting seat are provided with an integrally formed stepped shaft, and each of the stepped shafts is gap-inserted into the corresponding stepped hole. The upper end of the inner mounting seat is provided with an oil inlet connected to the cavity therein, and the left and right ends of the inner mounting seat are provided with an inner mounting seat leakage detection groove.

[0008] The limiting mechanism includes a positioning nut and an externally threaded boss; the externally threaded boss is arranged on the upper surface of the stand, the motor bracket is an L-shaped structure, the horizontal plate of the motor bracket is provided with a waist-shaped hole, the externally threaded boss is arranged in the waist-shaped hole, the outer side of the externally threaded boss is threadedly connected to the positioning nut, the positioning nut is used to tighten the motor bracket, and the vertical plate of the motor bracket is fixedly connected to the horizontally arranged linear motor.

[0009] The upper surface of the stand and the motor bracket are provided with corresponding positioning holes, and positioning pins are inserted into the positioning holes.

[0010] The two ends of the upper surface of the base are respectively fixedly connected to the corresponding guide seats, and each of the guide seats is sleeved on the outside of the guide rod of the hydraulic system with a gap.

[0011] An oil leakage collector is provided below the inner mounting seat and the two outer mounting seats, and the oil leakage collector is placed on the base.

[0012] A force sensor is installed between the guide rod of the hydraulic system and the output shaft of the linear motor.

[0013] One end of the force sensor away from the guide rod of the hydraulic system is hinged to one end of the quick-cut connecting rod. The other end of the quick-cut connecting rod is provided with a long waist hole, and the long waist hole is connected to the output shaft of the linear motor.

[0014] A method for using a reciprocating and torsion integrated aviation hydraulic system test device of the present invention comprises the following steps:

[0015] S1: Insert two static seals onto the outer sides of the two stepped shafts of the inner mounting seat through interference fit.

[0016] S2: Slide one end of the guide rod of the hydraulic system through one of the guide seats and one of the placement plates in sequence;

[0017] S3: Sleeve one of the external mounting seats onto the outside of one end of the guide rod of the hydraulic system;

[0018] S4: A dynamic seal is inserted into the outer side of one end of the guide rod of the hydraulic system;

[0019] S5: Sleeve the inner mounting seat onto the outer side of one end of the guide rod of the hydraulic system;

[0020] S6: Connect the inner mounting seat to the assembled outer mounting seat;

[0021] S7: A dynamic seal is interference fit onto the outer side of one end of the guide rod of the hydraulic system, so that the dynamic seal fits into the end surface of the other stepped shaft of the inner mounting seat;

[0022] S8: Sleeve another outer mounting seat onto the outer side of one end of the hydraulic system guide rod and connect it to the inner mounting seat;

[0023] S9: Slide one end of the hydraulic system guide rod through another placement plate and another guide seat in sequence;

[0024] S10: Install and fix the inner mounting base and the two outer mounting bases;

[0025] S11: Use locking screws to fix the relative positions of the inner mounting base, the two outer mounting bases, and the placement plate;

[0026] S12: Install the linear motor so that the output shaft of the linear motor is coaxial with the guide rod of the hydraulic system;

[0027] S13: Connect the hydraulic system guide rod, force sensor, quick-cut connecting rod and linear motor in sequence;

[0028] S14: Inject high-pressure test oil through the oil inlet of the inner mounting seat;

[0029] S15: The linear motor is started to drive the guide rod of the hydraulic system to rotate to the test requirements. During this period, the leakage detection groove of the outer mounting seat and the leakage detection groove of the inner mounting seat are observed to see if there is oil leakage;

[0030] S16: Disassemble the quick-cut link and the linear motor connection, pull out the positioning pin, and loosen the positioning nut;

[0031] S17: Rotate the motor bracket horizontally 90°, insert the positioning pin, tighten the positioning nut, and reconnect the quick-cut link and linear motor.

[0032] S18: The linear motor is started and drives the hydraulic system guide rod to reciprocate to the test requirements through a preset program. During this period, the leakage detection groove of the outer mounting seat and the leakage detection groove of the inner mounting seat are observed to see if there is oil leakage.

[0033] Compared with the prior art, the present invention has the following beneficial effects:

[0034] The present invention can effectively detect wear, leakage, and friction resistance in aviation hydraulic systems under both reciprocating and torsional conditions. It can quickly switch between the two states, is simple and convenient to operate, and integrates the two tests, improving test efficiency and reducing testing costs. It also ensures smooth operation of the motion mechanism during testing, preventing jamming. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Figure 1 This is a schematic diagram of the structure of the present invention in a torsion state;

[0036] Figure 2 yes Figure 1 sectional view of

[0037] Figure 3 It is a schematic structural diagram of the present invention in a reciprocating state. DETAILED DESCRIPTION

[0038] The technical solutions of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0039] A reciprocating and torsion integrated aviation hydraulic system test device, comprising a base 1, a locking screw 4, a placement plate 5, an outer mounting seat 6, an inner mounting seat 7, a gantry 11, a motor bracket 15 and a linear motor 18; a base 1 is fixed to one side of the upper end of the gantry 11, and two vertically arranged placement plates 5 are fixed to the upper end of the base 1 by corresponding screws 3, and a horizontally arranged hydraulic system guide rod 9 is placed on the upper end of the two placement plates 5, and the outer gap of the hydraulic system guide rod 9 is sleeved with an inner mounting seat 7 and two outer mounting seats 6, and the inner mounting seat 7 is fixed to the upper end of the gantry 11 by corresponding screws 3. The corresponding screws 3 are fixedly installed between the two outer mounting blocks 6. The upper end of each placement plate 5 is threadedly connected to two corresponding locking screws 4. The nail head of each locking screw 4 is placed against the end face of the corresponding outer mounting block 6. The locking screws 4 fix the outer mounting blocks 6, dynamic seals, static seals, and inner mounting block 7 in a specific position. The hydraulic system guide rod 9 is connected to the output shaft of the linear motor 18. The linear motor 18 is fixedly mounted on the motor bracket 15. The linear motor 18 is the power source of the test device, used to provide power for reciprocating and torsional motion. The motor bracket 15 is fixedly connected to the other side of the upper end of the test stand 11 through a limit mechanism.

[0040] The outer mounting seat 6 is an installation and testing device for the hydraulic system seal. The two outer mounting seats 6 are symmetrically arranged. The inner end of each outer mounting seat 6 is provided with a stepped hole, which is used for the installation of dynamic seals and static seals. The outer end of each outer mounting seat 6 is provided with an outer mounting seat leakage detection groove 22.

[0041] The inner mounting seat 7 is an installation and testing device for the hydraulic system seal. The left and right ends of the inner mounting seat 7 are provided with an integrally formed stepped shaft for the installation of static seals. Each of the stepped shafts is inserted into the corresponding stepped hole with a gap. The upper end of the inner mounting seat 7 is provided with an oil inlet 24 connected to the cavity therein. High-pressure test oil is injected from the oil inlet for the sealing performance test of the hydraulic system under a certain pressure; the left and right ends of the inner mounting seat 7 are provided with an inner mounting seat leakage detection groove 23.

[0042] The limiting mechanism includes a positioning nut 12 and an externally threaded boss 19; the externally threaded boss 19 is integrally formed and arranged on the upper surface of the platform 11, and the motor bracket 15 is an L-shaped structure. The horizontal plate of the motor bracket 15 is provided with a waist-shaped hole, and the externally threaded boss 19 is arranged in the waist-shaped hole. The outer side of the externally threaded boss 19 is threadedly connected to the positioning nut 12, and the positioning nut 12 is used to tighten the motor bracket 15. The vertical plate of the motor bracket 15 is fixedly connected to the horizontally arranged linear motor 18 by a motor screw 17, and the waist-shaped hole facilitates arbitrary adjustment of the horizontal angle and horizontal position of the linear motor 18 and the platform 11.

[0043] The upper surface of the stand 11 and the motor bracket 15 are provided with corresponding positioning holes, and positioning pins 16 are inserted into the positioning holes. The positioning pins 16 are used to position the motor bracket 15.

[0044] The two ends of the upper surface of the base 1 are fixedly connected to the corresponding guide seats 2 by corresponding screws 3. Each guide seat 2 is loosely mounted on the outside of the hydraulic system guide rod 9. The guide seat 2 guides the hydraulic system guide rod 9 to prevent the moving structure from getting stuck during dynamic testing.

[0045] An oil leakage collector 8 is provided below the inner mounting seat 7 and the two outer mounting seats 6. The oil leakage collector 8 is placed on the base 1. The oil leakage collector 8 is used to collect leaked oil as a criterion for test results.

[0046] A force sensor 10 is installed between the hydraulic system guide rod 9 and the output shaft of the linear motor 18. The force sensor 10 is a device for measuring the motion resistance of the hydraulic sealing system. It is threadedly connected to the hydraulic system guide rod 9 and moves back and forth and torsional with the hydraulic system guide rod 9 to measure the motion resistance.

[0047] The end of the force sensor 10, remote from the hydraulic system guide rod 9, is hingedly connected to one end of a quick-release link 14 via a pin 13. The other end of the quick-release link 14 is provided with an elongated hole extending through its thickness. This hole is connected to the output shaft of the linear motor 18 via a pin 13. The quick-release link 14 serves as a quick-change device for testing, enabling rapid installation and removal; the pin 13 allows for quick insertion and removal.

[0048] A method for using a reciprocating and torsion integrated aviation hydraulic system test device of the present invention comprises the following steps:

[0049] S1: Insert two static seals 21 onto the outer sides of the two stepped shafts of the inner mounting seat 7 through interference fit.

[0050] S2: Slide one end of the hydraulic system guide rod 9 through one of the guide seats 2 and one of the placement plates 5 in sequence;

[0051] S3: Sleeve one of the outer mounting seats 6 onto the outer side of one end of the hydraulic system guide rod 9;

[0052] S4: A dynamic seal 20 is interference fit onto the outer side of one end of the hydraulic system guide rod 9;

[0053] S5: Sleeve the inner mounting seat 7 onto the outer side of one end of the hydraulic system guide rod 9;

[0054] S6: Connect the inner mounting seat 7 to the outer mounting seat 6 that has been installed;

[0055] S7: A dynamic seal 20 is again inserted through an interference fit on the outer side of one end of the hydraulic system guide rod 9, so that the dynamic seal 20 fits in contact with the end surface of the other stepped shaft of the inner mounting seat 7;

[0056] S8: Put another outer mounting seat 6 on the outside of one end of the hydraulic system guide rod 9 and connect it with the inner mounting seat 7;

[0057] S9: Slide one end of the hydraulic system guide rod 9 through another placement plate 5 and another guide seat 2 in sequence;

[0058] S10: Use screws 3 to fix the inner mounting base 7 and the two outer mounting bases 6;

[0059] S11: Use locking screws 4 to fix the relative positions of the inner mounting seat 7, the two outer mounting seats 6 and the placement plate 5;

[0060] S12: Install the linear motor 18 so that the output shaft of the linear motor 18 is coaxially arranged with the hydraulic system guide rod 9;

[0061] S13: Connect the hydraulic system guide rod 9, force sensor 10, quick-cut link 14 and linear motor 18 in sequence;

[0062] S14: injecting high-pressure test oil through the oil inlet 24 of the inner mounting seat 7;

[0063] S15: The linear motor 18 is started to drive the hydraulic system guide rod 9 to rotate to the test requirement, and during this period, the outer mounting seat leakage detection groove 22 and the inner mounting seat leakage detection groove 23 are observed to see if there is oil leakage;

[0064] S16: Disassemble the connection between the quick-cut link 14 and the linear motor 18, pull out the positioning pin 16, and loosen the positioning nut 12;

[0065] S17: After rotating the motor bracket 1590 degrees horizontally, insert the positioning pin 16, tighten the positioning nut 12, and reconnect the quick-cut link 14 and the linear motor 18. During this period, adjust the vertical position of the linear motor 18 as needed so that the output shaft of the linear motor 18 can be installed in the long waist hole of the quick-cut link 14 through the pin 13, and then tighten the motor screw 17;

[0066] S18: The linear motor 18 is started and drives the hydraulic system guide rod 9 to reciprocate to the test requirements through a preset program. During this period, the outer mounting seat leakage detection groove 22 and the inner mounting seat leakage detection groove 23 are observed to see if there is oil leakage.

[0067] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above and that the invention can be embodied in other forms without departing from the spirit or essential characteristics of the invention. Therefore, the embodiments should be considered in all respects as illustrative and non-restrictive, and the scope of the invention is defined by the appended claims, not the foregoing description, and all variations within the meaning and range of equivalents of the claims are intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim to which it relates.

[0068] In addition, it should be understood that although this specification is described in terms of implementation methods, not every implementation method contains only one independent technical solution. This narrative method of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment can also be appropriately combined to form other implementation methods that can be understood by those skilled in the art.

Claims

1. A reciprocating and torsional integrated aviation hydraulic system test device, characterized by: The invention comprises a base (1), a locking screw (4), a placement plate (5), an outer mounting seat (6), an inner mounting seat (7), a stand (11), a motor bracket (15) and a linear motor (18); a base (1) is fixed to one side of the upper end of the stand (11); two vertically arranged placement plates (5) are fixed to the upper end of the base (1); a horizontally arranged hydraulic system guide rod (9) is placed on the upper ends of the two placement plates (5); an inner mounting seat (7) and two outer mounting seats (6) are sleeved in the outer gap of the hydraulic system guide rod (9); the inner mounting seat (7) is fixedly installed between the two outer mounting seats (6) The upper end of each placement plate (5) is screwed with the corresponding locking screw (4), and the nail head end of each locking screw (4) is respectively set against the end face of the corresponding external mounting seat (6). The hydraulic system guide rod (9) is connected to the output shaft of the linear motor (18), and the linear motor (18) is fixedly mounted on the motor bracket (15). The motor bracket (15) is fixedly connected to the other side of the upper end of the platform (11) through a limiting mechanism. The two external mounting seats (6) are symmetrically arranged, and the inner end of each external mounting seat (6) is provided with a stepped hole, and the outer end of each external mounting seat (6) is provided with an external mounting seat leakage detection The left and right ends of the inner mounting seat (7) are provided with an integrally formed stepped shaft, each of the stepped shafts is respectively inserted into the corresponding stepped hole, the upper end of the inner mounting seat (7) is provided with an oil inlet (24) connected to the cavity therein, and the left and right ends of the inner mounting seat (7) are provided with an inner mounting seat leakage detection groove (23); the limiting mechanism includes a positioning nut (12) and an externally threaded boss (19); the externally threaded boss (19) is provided on the upper surface of the stand (11), the motor bracket (15) is an L-shaped structure, the horizontal plate of the motor bracket (15) is provided with a waist-shaped hole, the externally threaded boss ( 19) is arranged in the waist-shaped hole, and the outer side of the external threaded boss (19) is screwed with the positioning nut (12), and the positioning nut (12) is used to press the motor bracket (15), and the vertical plate of the motor bracket (15) is fixedly connected to the horizontally arranged linear motor (18); a force sensor (10) is installed between the hydraulic system guide rod (9) and the output shaft of the linear motor (18); the end of the force sensor (10) away from the hydraulic system guide rod (9) is hinged to one end of the quick-cut connecting rod (14), and the other end of the quick-cut connecting rod (14) is provided with a long waist hole, and the long waist hole is connected to the output shaft of the linear motor (18).

2. The reciprocating and torsion integrated aviation hydraulic system test device according to claim 1, characterized in that: The upper surface of the stand (11) and the motor bracket (15) are provided with corresponding positioning holes, and positioning pins (16) are inserted into the positioning holes.

3. The reciprocating and torsion integrated aviation hydraulic system test device according to claim 1, characterized in that: Both ends of the upper surface of the base (1) are fixedly connected to corresponding guide seats (2), and each guide seat (2) is sleeved on the outside of the hydraulic system guide rod (9) with a gap.

4. The reciprocating and torsion integrated aviation hydraulic system test device according to claim 1, characterized in that: An oil leakage collector (8) is provided below the inner mounting seat (7) and the two outer mounting seats (6), and the oil leakage collector (8) is placed on the base (1).

5. A method for using the reciprocating and torsion integrated aviation hydraulic system test device according to claim 4, characterized in that: The method comprises the following steps: S1: Insert two static seals (21) respectively on the outer sides of the two stepped shafts of the inner mounting seat (7); S2: Slide one end of the hydraulic system guide rod (9) through one of the guide seats (2) and one of the placement plates (5) in sequence; S3: Sleeve one of the outer mounting seats (6) onto the outer side of one end of the hydraulic system guide rod (9); S4: A dynamic seal (20) is interference fit onto the outer side of one end of the hydraulic system guide rod (9); S5: Sleeve the inner mounting seat (7) onto the outer side of one end of the hydraulic system guide rod (9); S6: Connect the inner mounting seat (7) to the assembled outer mounting seat (6); S7: A dynamic seal (20) is again fitted onto the outer side of one end of the hydraulic system guide rod (9) so that the dynamic seal (20) is fitted onto the end surface of the other stepped shaft of the inner mounting seat (7); S8: Sleeve another outer mounting seat (6) onto the outer side of one end of the hydraulic system guide rod (9), and connect it to the inner mounting seat (7); S9: Slide one end of the hydraulic system guide rod (9) through another placement plate (5) and another guide seat (2) in sequence; S10: Install and fix the inner mounting seat (7) and the two outer mounting seats (6); S11: Use locking screws (4) to fix the relative positions of the inner mounting seat (7), the two outer mounting seats (6) and the placement plate (5); S12: Install the linear motor (18) so that the output shaft of the linear motor (18) is coaxially arranged with the hydraulic system guide rod (9); S13: Connecting the hydraulic system guide rod (9), the force sensor (10), the quick-cut connecting rod (14) and the linear motor (18) in sequence; S14: inject high-pressure test oil through the oil inlet (24) of the inner mounting seat (7); S15: The linear motor (18) is started to drive the hydraulic system guide rod (9) to rotate to the test requirement, and during this period, the outer mounting seat leakage detection groove (22) and the inner mounting seat leakage detection groove (23) are observed to see if there is oil leakage; S16: Disassemble the quick-cut link (14) and the connection of the linear motor (18), pull out the positioning pin (16), and loosen the positioning nut (12); S17: After rotating the motor bracket (15) horizontally by 90 degrees, insert the positioning pin (16), tighten the positioning nut (12), and reconnect the quick-cut link (14) and the linear motor (18); S18: The linear motor (18) is started and drives the hydraulic system guide rod (9) to reciprocate to the test requirements through a preset program. During this period, the outer mounting seat leakage detection groove (22) and the inner mounting seat leakage detection groove (23) are observed to see if there is oil leakage.

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