CN113879560B - Method for measuring movable clearance of inner lock of aircraft actuating cylinder - Google Patents
Method for measuring movable clearance of inner lock of aircraft actuating cylinder Download PDFInfo
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- CN113879560B CN113879560B CN202111343300.6A CN202111343300A CN113879560B CN 113879560 B CN113879560 B CN 113879560B CN 202111343300 A CN202111343300 A CN 202111343300A CN 113879560 B CN113879560 B CN 113879560B
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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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Abstract
The invention discloses a method for measuring the movable clearance of an inner lock of an aircraft actuator cylinder, which has the advantages of simple measurement and real and accurate measurement result. The invention is realized by the following technical scheme: after the actuator cylinder is installed and fixed on a test bed, the actuator cylinder is supplied with pressure, the piston rod is driven to extend to the head or retract to the bottom, the nozzle is opened for pressure relief after the mechanical lock is pushed to be locked, the average variable value of the movable clearance and the pulling deformation of the pulling load are measured under each group of axial pressure load according to the actual working condition of the actuator cylinder, the material variable quantity read by a dial indicator needle is recorded to obtain the total variable quantity of the axial external force working load of the actuator cylinder, whether the actual movable clearance of the mechanical lock in the actuator cylinder is within the allowable value range is calculated, if yes, the adjustment is finished, otherwise, the measurement is continued until the actual movable clearance of the mechanical lock is within the allowable range, the average variable quantity of the axial working pressure and the pulling load of the actuator cylinder is obtained by grouping measurement and averaging, and the accurate clearance quantity is obtained.
Description
Technical Field
The invention relates to the field of locking reliability tests of mechanical locks of aircraft cylinders, in particular to a method for measuring a movable clearance of a built-in mechanical lock of an aircraft cylinder.
Background
The hydraulic actuator cylinder is a power conversion device. The hydraulic energy is converted into mechanical energy, and the driving force is provided for various transportation carriers, test systems and mechanical engineering. The actuator cylinder is an important component part of an aircraft landing gear system and provides a power source for the landing gear and the landing door to be put down and taken up. In the design of the aircraft actuating cylinder, in order to ensure the length of the actuating cylinder rod, the landing gear and the cabin door (guard plate) are locked at the folding or unfolding position to play a role in locking, and the inner lock is arranged inside the actuating cylinder by virtue of the structure of the inner lock, so that a connecting joint and a stress joint are not required to be arranged on a landing gear strut and a machine body independently, and the aircraft actuating cylinder has the advantages of simplifying the structure and saving space. Because if the inner lock is used as the upper lock, a set of manual emergency setting-down system needs to be designed besides a common unlocking device. The reasonable design and selection of the inner lock of the actuating cylinder can improve the working reliability of the landing gear and the retraction and the extension of the cabin door (guard plate), thereby ensuring the safety of taking off and landing of the airplane. In the design of airplanes at home and abroad, most of the internal locks of the actuating cylinders are used as lower locks, namely landing gear and guard plates are locked at the put-down positions. The motion state of a mechanism in the landing gear retraction system of the aircraft can be divided into four stages of relative rest, unlocking, putting in place and locking. Wherein unlocking and locking are of great importance, and the flight safety of the aircraft is affected. Certain hydraulic operating mechanisms on aircraft are required to be reliably fixed in extreme positions to ensure the safety of aircraft flight, ground parking and ground maintenance personnel. If the landing gear is put down, the actuator cylinder is used as a rigid supporting rod to bear the external load transmitted by the landing gear, so a mechanical lock is arranged inside the landing gear actuator cylinder of the aircraft. In a particularly important position, a hydraulic lock is additionally arranged outside the actuating cylinder, and when the mechanical lock fails, the hydraulic lock also acts, which is the redundancy design, so that the safety and the reliability are improved. Parts that are hydraulically operated on board the aircraft are required to be reliably lockable in their extreme positions. For example, both aircraft front doors and nose landing gears require that the ram be able to act as a rigid rod to carry external loads after being lowered or retracted. Some components do not have a separate locating lock, but rely on an internal mechanical lock attached to the ram to maintain their position. Currently, in the design of internal cylinder locks of aircraft landing gear systems, the types of mechanical locks commonly used in cylinder interiors are broadly classified into steel ball locks, snap ring locks, finger locks, collet locks, and the like. Steel ball locks, snap ring locks, and 3 types of internal locks, finger locks (grab locks), are common. The locking force of the steel ball lock is small, and the steel ball lock is convenient to manufacture and install; the snap ring lock has large locking force, high technological requirement, large locking pressure of the finger lock, stability, reliability and high manufacturing and installation difficulty. The length L, outer diameter, inner diameter and contact angle θ of the finger lock have a greater effect on the axial force. The research articles about the design of the internal lock of the aircraft actuator cylinder disclosed at home and abroad are relatively few, so that the designers of each aircraft design institute at home generally refer to the original drawing of the internal lock of the actuator cylinder when the internal lock of the actuator cylinder is designed, and the communication and development of the internal lock of the actuator cylinder are restricted.
The actuating cylinder structure generally comprises an outer cylinder, a piston rod, a piston, a spring, a sealing element, a corresponding locking element (a clamping ring, a steel ball, a finger claw) and the like. The locking and unlocking of the spring structure actuator cylinder inner lock is realized through the contraction of a spring arranged in the actuator cylinder. The inner lock of the actuating cylinder is operated by mainly promoting the snap ring, the steel ball and the finger claw of the core part of the inner lock to move through the expansion and contraction of the spring so as to achieve the purposes of locking and unlocking. Before the snap ring locks, oil enters the left cavity of the actuator cylinder. The piston, the piston rod, the clamping ring and related sealing elements move rightwards together, and the piston rod drives the elastic clamping ring to stretch and slide along the inner surface of the outer cylinder. When the snap ring moves to the inner groove of the outer cylinder, the snap ring expands outwards and is clamped in the groove. At this time, the piston is inserted into the inner diameter of the clamping ring under the extrusion action of the hydraulic pressure and the left end spring thereof, so as to limit the inward contraction of the clamping ring and lock the actuating cylinder at the full extension position of the piston rod. When unlocking is needed, oil enters the cavity of the actuating cylinder through the right side nozzle, the piston is pushed to move left under the action of hydraulic pressure to separate from the clamping ring, the spring is compressed, the clamping ring contracts inwards, and unlocking is realized after the oil is separated from the inner groove of the outer cylinder. Steel ball locks are commonly used in the design of cabin door (guard plate) retraction rams with smaller areas and small bearing pneumatic loads. Before the steel ball lock is locked, oil enters the left cavity of the actuating cylinder, the piston rod and the steel ball move rightwards together, and when the oil contacts with the inclined surface of the special ring, the steel ball is driven to the center under the action of the inclined surface, and the plunger is propped against the steel ball to compress the spring rightwards. At the same time, the steel ball slides along the inclined plane of the plunger and is wedged between the special ring and the plunger, so that the actuator cylinder is in a locking state, and the piston rod is locked in a full-extension position. When unlocking, oil enters the actuating cylinder cavity through the right side nozzle, overcomes the resistance of the spring, makes the piston move left, the steel ball falls into the groove after being separated from the special ring, namely the unlocking is performed, and the piston rod start to retract left. The finger-shaped lock is a split chuck shaped like a finger and is arranged on the piston rod, and the inner wall of the outer cylinder is grabbed under the action of the locking piston, so that locking is realized. Before locking, the locking chuck moves rightwards along with the piston rod, and when passing through the boss on the inner surface of the outer cylinder, the chuck is forced to shrink radially, and the locking chuck moves forwards continuously and pushes against the locking piston. When the clamping head passes over the boss, the clamping head expands to the periphery and falls into the groove of the outer cylinder, and meanwhile, the locking piston stretches into the clamping head under the action of the spring, and the clamping head is locked and cannot move, so that locking is realized. When unlocking, oil enters the actuating cylinder cavity through the right side nozzle, and pushes the locking piston to move rightwards, so that the spring is compressed, and the locking piston is led to exit the separating chuck. Under the action of external load, the separating chuck withdraws from the groove of the outer cylinder to unlock. In the locking process of the inner lock of the actuating cylinder, hydraulic pressure acts on the piston rod assembly, the piston extrudes and pushes the inner lock core piece to the corresponding position, and at the moment, the clamping ring, the unlocking and the finger-shaped claw of the inner lock core piece are clamped under various forces, so that the piston rod is locked at the specified position. The stability of the stress of the core piece directly influences the reliability of the locking operation. In the design process of the landing gear actuating cylinder inner lock, the influence of the change of the contact inclined plane angle theta on the unlocking pressure is avoided. Along with the increase of the angle of the inclined plane, the unlocking pressure of the clamping ring lock and the steel ball lock is also increased continuously. After the angle is larger than 50 degrees, the locking pressure of the snap ring lock rapidly rises, and the unlocking pressure of the steel ball lock increases relatively gently. The main reason for this is that the angle of the contact ramp increases and the compression stroke of the spring increases, which requires a greater unlocking pressure to compress the spring, thereby disengaging the snap ring and steel ball from their respective grooves to unlock the lock. And the unlocking pressure is changed to different degrees along with the increase of the inclined plane angle due to the respective external structural characteristics of the snap ring and the steel ball. The influence of the contact inclined plane angle on the unlocking pressure is small, the clamping ring and the steel ball are easy to fall off from the locking position, and the locking is unstable and unreliable; the contact inclined plane is big, needs very big pressure compression spring that unbuckles, makes snap ring, steel ball drop in the locking position, unbuckles difficulty in addition, wears out, the impact is great to the motion spare part in the actuator cylinder, shortens its life. The unlocking pressure of the actuating cylinder is too small, so that the condition that the actuating cylinder is unlocked due to too large oil return pressure of the system after the actuating cylinder is normally locked can occur; the unlocking pressure of the actuating cylinder is too large, so that unlocking is difficult, and the unlocking pressure of the mechanical lock in the aircraft actuating cylinder influences the reliability of locking the mechanical lock on the gap. The core part of the inner lock of the actuating cylinder is a key part of the inner lock, the accuracy and the reliability of the inner lock are directly affected, the snap ring is required to be unfolded when locked, and the snap ring is required to be contracted when unlocked, so that the material and the structure of the snap ring are required to meet certain elastic requirements. The elasticity of the snap ring structure is deformed by manufacturing a notch on the snap ring structure, the snap ring structure is locked by extrusion of the inclined surface of the outer ring of the snap ring and the corresponding inclined surface of the outer cylinder, and the inclined surface of the inner ring of the snap ring guides the piston to enter the snap ring to expand the snap ring. The outer ring inclined plane is matched with the outer cylinder inclined plane, and the inner ring inclined plane is matched with the piston inclined plane. The steel ball is in point contact when locked, is unstable, is easy to wear under heavy load, and has relatively poor working reliability. It is necessary to prevent microscopic irregularities on the surface other than spherical deviations and waviness from being present in the areas of the plunger cylinder and the special ring in contact with the steel ball, and defects such as cracks, depressions, and corrosion are not allowed. When the movable clearance after the mechanical lock is locked exceeds a specified value, the impact force between the lock ring and the lock groove is overlarge in working, the risk of unlocking exists, when the movable clearance after the mechanical lock is locked is lower than the specified value, the risk that the mechanical lock is self-locking (or the lock ring is blocked) and can not be unlocked is caused, the reliability of locking is required to be met, and the movable clearance amount of the actuator cylinder in the locked state is required to be within the design range of (0.2-0.4) mm, so that the measurement is generally not easy.
The prior measuring method for measuring the movable clearance of the mechanical lock in the actuating cylinder is to use a dial indicator to measure, after the piston rod stretches out and is locked, the dial indicator is regulated on the piston rod, so that a dial indicator measuring rod is propped against the end face of the outer cylinder fixing nut, a certain compression value is kept, then a certain external force is applied along the axial direction of the piston rod, the piston rod is pushed in and pulled out, and the movable clearance of the lock clearance is measured by the dial indicator, wherein the movable range of the piston rod is measured. The method has low detection precision, inaccurate measurement result and low reliability, and the measurement result contains deformation of internal parts of the actuator cylinder, such as a lock ring, an adjusting washer, a piston rod, a piston and the like.
Disclosure of Invention
The invention aims to provide a measuring method which is simple in measurement, accurate in measurement result and capable of truly reflecting the movable clearance amount of a mechanical lock in an actuator cylinder aiming at the defects of the existing measuring method.
The above object of the invention is achieved by a method for measuring the clearance between the lock and the lock in an aircraft cylinder, comprising the steps of:
step 1: after the actuating cylinder is installed and fixed on the test bed, the test bed is started to supply pressure to the nozzle which is put down or taken up of the actuating cylinder, the piston rod is driven to extend to the head or retract to the bottom, the nozzle is opened for decompression after the mechanical lock is pushed to lock, and the dial indicator is fixed at the position specified by the piston rodThe end cover of a dust ring is arranged at the extending end of the actuator cylinder by a branch meter measuring rod, the reading of a gauge needle is adjusted to be zero scale, working pressure loads are respectively applied along the axial direction of a piston rod of the actuator cylinder according to the actual working condition of the actuator cylinder, the axial working pressure load X of the actuator cylinder is divided into a plurality of groups, the working pressure loads are applied by the consistent external force ballast load level difference of each group, the average change value of a movable clearance under each group of axial pressure loads is measured, the change value of the reading of the gauge needle under each group of axial working pressure loads is respectively recorded, and the ballasting deformation amount of average materials under each group of axial working pressure loads of the actuator cylinder is obtained 1 And the pull load deformation of the average material under each group of axial working pull loads of the actuator cylinder is delta 2 ；
Step 2: the method comprises the steps of executing axial working pulling load on an actuator cylinder, dividing the axial working pulling load Y of the actuator cylinder into a plurality of groups, respectively applying external force pulling load with consistent level difference of each group along the axial direction of a piston rod of the actuator cylinder, and respectively recording the change quantity of the meter pointer reading under each group of axial working pulling load;
step 3: according to the axial external force compression load X and the external force pulling load Y applied along the axial direction of the piston rod of the actuator cylinder, the total amount of the movable clearance under the axial external force load is measured 3 Recording the material change of the dial indicator needle reading to obtain the total change of the axial external force working load of the actuator cylinder 3 And calculating whether the actual movable clearance delta of the mechanical lock in the actuator cylinder is in the allowable value range, if yes, ending, otherwise, decomposing and checking, selecting a gasket for adjustment, continuing measurement until the actual movable clearance delta of the mechanical lock is in the allowable value range, and carrying out grouping measurement and averaging on the actual movable clearance delta to obtain the average deformation of the actuator cylinder under the axial working pressure and the pulling load, thereby obtaining the accurate clearance.
Compared with the prior art, the invention has the following beneficial effects:
the invention increases the material deformation of the parts and components in the measuring actuator cylinder when measuring the movable clearance of the mechanical lock in the actuator cylinder, and adopts the measuring method that the average deformation of the axial working pressure and the pulling load of the actuator cylinder is obtained by grouping the measurement and averaging the measurement according to the actual working condition of the actuator cylinder and the pressing and pulling load, and the measuring is simple and the measuring result is accurate. When the axial working pressure load X of the actuator cylinder is divided into a plurality of groups in a bisecting way, the number of the groups can be flexibly selected according to the actual condition of the load, the rigid regulation of 10 groups is not needed, the determination of the coefficient lambda in the formula for calculating the actual clearance delta is easy, and the coefficient lambda is equal to the bisecting number of the axial working load of the actuator cylinder, so that the simple measuring method is realized.
When the invention calculates the clearance delta of the mechanical lock in the actuator cylinder, the total variation delta of the axial working load of the actuator cylinder is calculated 3 Subtracting the component material deformation (lambda) caused by the total axial working load of the actuator cylinder 1 △ 1 +λ 2 △ 2 ) Thus, accurate clearance amount is obtained, and the measured data can truly reflect the movable clearance amount of the mechanical lock in the actuator cylinder. The flight safety of the aircraft is ensured.
Drawings
The accompanying drawings are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification.
FIG. 1 is a schematic illustration of the flow of measurement of lock clearance in an aircraft cylinder according to the present invention.
In order to further explain the concept of the present invention, a front guard plate actuator of a certain type will be described in detail, but the present invention is not limited thereto.
Detailed Description
See fig. 1. According to the invention, the following steps are used:
step 1: after the actuator cylinder is installed and fixed on the test bed, the test bed is started to press the nozzle which is put down or taken up of the actuator cylinder, the piston rod is driven to extend to the head or retract to the bottom, the nozzle is opened and depressurized after the mechanical lock is pushed to be locked, the dial indicator is fixed on the position specified by the piston rod, the dial indicator measuring rod is propped against the end cover of the dust ring which is installed at the extending end of the actuator cylinder, the reading of the gauge needle is adjusted to be zero scale, the working pressure load is respectively applied along the axial direction of the piston rod of the actuator cylinder according to the actual working condition of the actuator cylinder, the axial working pressure load X of the actuator cylinder is divided into a plurality of groups by halving the working pressure load X of each groupThe uniform external force ballasting load level difference applies working pressure load, the average change value of the movable clearance under each group of axial pressure load is measured, the change value of gauge needle reading under each group of axial working pressure load is recorded respectively, and the ballasting deformation of the average material under each group of axial working pressure load of the actuator cylinder is obtained 1 And the pull load deformation of the average material under each group of axial working pull loads of the actuator cylinder is delta 2 ；
Step 2: the method comprises the steps of executing axial working pulling load on an actuator cylinder, dividing the axial working pulling load Y of the actuator cylinder into a plurality of groups, respectively applying external force pulling load with consistent level difference of each group along the axial direction of a piston rod of the actuator cylinder, and respectively recording the change quantity of the meter pointer reading under each group of axial working pulling load;
step 3: according to the axial external force compression load X and the external force pulling load Y applied along the axial direction of the piston rod of the actuator cylinder, the total amount of the movable clearance under the axial external force load is measured 3 Recording the material change of the dial indicator needle reading to obtain the total change of the axial external force working load of the actuator cylinder 3 And calculating whether the actual movable clearance delta of the mechanical lock in the actuator cylinder is in the allowable value range, if yes, ending, otherwise, decomposing and checking, selecting a gasket for adjustment, continuing measurement until the actual movable clearance delta of the mechanical lock is in the allowable value range, and carrying out grouping measurement and averaging on the actual movable clearance delta to obtain the average deformation of the actuator cylinder under the axial working pressure and the pulling load, thereby obtaining the accurate clearance.
In an alternative embodiment, preparation is first made prior to the test: the dirt and oil trace on the surface of the actuator cylinder are wiped off by using the clean white silk cloth dipped with No. 180 aviation washing gasoline. The surface of the product is not damaged or scratched in the cleaning process.
And (3) mounting and fixing: the tool is used for installing the actuating cylinder on the test bed and fixing the actuating cylinder firmly, the upper nozzle and the lower nozzle of the actuating cylinder are respectively connected with the oil way of the test bed, and the dial indicator is fixed on the piston rod of the actuating cylinder, so that the measuring rod of the dial indicator is propped against the end cover.
Test run:
(1) Starting the test bed, controlling the test bed to put down the nozzle to supply pressure (not more than 15 MPa) to the actuator cylinder so that the piston rod extends out of the head, locking, and then opening the nozzle to release pressure.
(2) Applying 750N axial outward force compressive load to the cylinder, zeroing the gauge needle reading, and then applying 1500N, 3000N, 4500N, 6000N, 7500N, 9000N, 10500N, 12000N, 13500N, 15000N axial compressive load, respectively, which can be divided into X 1 、X 2 、X 3 、X 4 、X 5 、X 6 、X 7 、X 8 、X 9 、X 10 The group forces, each group of forces allows deviation of +/-5%, the variation of the gauge needle reading is recorded respectively, then the variation of the actuator cylinder is averaged to obtain the deformation delta of the actuator cylinder under 1500N pressure load 1 ；
(3) Applying 750N axial pull load to the actuator cylinder, zeroing the gauge hand reading, and then applying 1500N, 3000N, 4500N, 6000N, 7500N, 9000N, 10500N, 12000N, 13500N, 15000N axial external force pull load, which can be divided into Y 1 、Y 2 、Y 3 、Y 4 、Y 5 、Y 6 、Y 7 、Y 8 、Y 9 、Y 10 The load force of each group, the allowable deviation of each load force of each group is +/-5%, the variation of the gauge needle reading is recorded respectively, then the variation of the actuator cylinder is averaged to obtain the variation delta of the actuator cylinder under the tensile load of 1500N 2 ；
(4) Applying 15000N compressive load and 15000N tensile load to the actuator cylinder respectively to obtain the change total amount delta of the meter reading 3 ；
(5) Based on the axial compression and tension loads of the cylinders divided into 10 groups, the actual clearance delta= of the mechanical lock inside the cylinder is calculated 3 -(λ 1 △ 1 +λ 2 △ 2 ) Whether or not the allowable value is: obtaining an accurate value of the clearance amount within the range of 0.2-0.4 mm, wherein lambda 1 For bisecting group number, lambda, of axial working pressure load X of the actuator cylinder 2 The number of bisectors of the pull load Y for axial operation of the actuator cylinder.
And (3) carrying out qualification criterion in the range of measuring the clearance between 0.2 and 0.4mm, selecting a gasket with the thickness of 1 to 3mm for adjustment, and if the criterion is qualified, completing the measurement of the clearance between the inner lock and the movable clearance, otherwise, carrying out decomposition inspection and re-measurement.
The invention is not limited to the specific embodiments described above. The invention extends to any novel one, or any novel combination, of the features disclosed in this specification, as well as to any novel one, or any novel combination, of the steps of the method or process disclosed. It is intended that insubstantial changes or modifications from the invention as described herein be covered by the claims below, as viewed by a person skilled in the art, without departing from the true spirit of the invention.
Claims (7)
1. The method for measuring the movable clearance of the lock in the aircraft actuator cylinder is characterized by comprising the following steps of:
step 1: after the actuator cylinder is installed and fixed on the test bed, the test bed is started to supply pressure to the lower nozzle or the upper nozzle of the actuator cylinder, the piston rod is driven to extend to the head or retract to the bottom, the mechanical lock is pushed to lock, the nozzle is opened and depressurized after the locking, the dial indicator is fixed on the position specified by the piston rod, the end cover of the dust ring is arranged at the extending end of the actuator cylinder by the dial indicator measuring rod, the reading of the needle is adjusted to zero scale, the axial working pressure load X of the actuator cylinder is divided into a plurality of groups by bisecting the axial working pressure load X of the actuator cylinder according to the actual working condition of the actuator cylinder, the working pressure load is applied to the axial working pressure rod along the axial direction of the piston rod of the actuator cylinder, the average change value of the movable clearance under each group of the axial working pressure load is measured, the change value of the reading of the needle under each group of the axial working pressure load is recorded respectively, and the ballasting deformation amount of the average material under each group of the axial working pressure load of the actuator cylinder is acquired 1 ；
Step 2: the axial working pulling load is implemented on the actuator cylinder, the axial working pulling load Y of the actuator cylinder is divided into a plurality of groups in a bisection mode, external force pulling loads with consistent step differences of each group are respectively applied along the axial direction of a piston rod of the actuator cylinder, the change quantity of the meter pointer reading under each group of axial working pulling load is respectively recorded, and the pulling load deformation quantity delta of the average material under each group of axial working pulling load of the actuator cylinder is obtained 2 ；
Step 3: according to the axial external force compression load X and the external force pulling load Y applied along the axial direction of the piston rod of the actuator cylinder, the total amount of the movable clearance under the axial external force load is measured 3 Record the readings of dial indicatorsThe material change quantity is used for obtaining the total change quantity delta of the axial external force working load of the actuator cylinder 3 And calculating whether the actual movable clearance delta of the mechanical lock in the actuator cylinder is in the allowable value range, if yes, ending, otherwise, decomposing and checking, selecting a gasket for adjustment, continuing measurement until the actual movable clearance delta of the mechanical lock is in the allowable value range, and carrying out grouping measurement and averaging on the actual movable clearance delta to obtain the average deformation of the actuator cylinder under the axial working pressure and the pulling load, thereby obtaining the accurate clearance.
2. A method of measuring lock clearance in an aircraft ram as claimed in claim 1, wherein: starting the test bed, controlling the test bed to put down the nozzle to the actuator cylinder for pressure not exceeding 15MPa, enabling the piston rod to extend out of the head, locking, and then opening the nozzle for pressure relief.
3. A method of measuring lock clearance in an aircraft ram as claimed in claim 2, wherein: applying 750N axial outward force compressive load to the cylinder, zeroing the gauge needle reading, and then applying 1500N, 3000N, 4500N, 6000N, 7500N, 9000N, 10500N, 12000N, 13500N, 15000N axial compressive load, respectively, which can be divided into X 1 、X 2 、X 3 、X 4 、X 5 、X 6 、X 7 、X 8 、X 9 、X 10 The group forces, each group of forces allows deviation of +/-5%, the variation of the gauge needle reading is recorded respectively, then the variation of the actuator cylinder is averaged to obtain the deformation delta of the actuator cylinder under 1500N pressure load 1 。
4. A method of measuring lock clearance in an aircraft ram as claimed in claim 3, wherein: applying 750N axial pull load to the actuator cylinder, zeroing the gauge hand reading, and then applying 1500N, 3000N, 4500N, 6000N, 7500N, 9000N, 10500N, 12000N, 13500N, 15000N axial external force pull load, which can be divided into Y 1 、Y 2 、Y 3 、Y 4 、Y 5 、Y 6 、Y 7 、Y 8 、Y 9 、Y 10 Force of each groupThe allowable deviation of each loading force is +/-5%, the variation of the meter needle reading is recorded respectively, then the variation of the actuator cylinder is averaged to obtain the pull load deformation delta of the actuator cylinder under the 1500N pull load 2 。
5. The method for measuring the lock clearance in an aircraft actuator cylinder as claimed in claim 4, wherein: applying 15000N compressive load and 15000N tensile load to the actuator cylinder respectively to obtain the change total amount delta of the meter reading 3 。
6. The method for measuring the lock clearance in an aircraft actuator cylinder as claimed in claim 5, wherein: based on the axial compression and tension loads of the cylinders divided into 10 groups, the actual clearance delta= of the mechanical lock inside the cylinder is calculated 3 -（λ 1 △ 1 ＋λ 2 △ 2 ) Whether or not the allowable value is: obtaining an accurate value of the clearance amount within the range of 0.2-0.4 mm, wherein lambda 1 For bisecting group number, lambda, of axial working pressure load X of the actuator cylinder 2 The number of bisectors of the pull load Y for axial operation of the actuator cylinder.
7. The method for measuring the lock clearance in an aircraft actuator cylinder as claimed in claim 6, wherein: and (3) carrying out qualification criterion in the range of measuring the clearance between 0.2 and 0.4mm, selecting a gasket with the thickness of 1 to 3mm for adjustment, and if the criterion is qualified, completing the measurement of the clearance between the inner lock and the movable clearance, otherwise, carrying out decomposition inspection and re-measurement.
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