CN114527008B - Device and method for simulating loading of folding gravity load of aircraft wing - Google Patents
Device and method for simulating loading of folding gravity load of aircraft wing Download PDFInfo
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- CN114527008B CN114527008B CN202210040525.2A CN202210040525A CN114527008B CN 114527008 B CN114527008 B CN 114527008B CN 202210040525 A CN202210040525 A CN 202210040525A CN 114527008 B CN114527008 B CN 114527008B
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- 238000011068 loading method Methods 0.000 title claims abstract description 101
- 230000005484 gravity Effects 0.000 title claims abstract description 49
- 238000000034 method Methods 0.000 title claims abstract description 28
- 238000004088 simulation Methods 0.000 claims abstract description 24
- 238000012360 testing method Methods 0.000 claims description 59
- 238000004804 winding Methods 0.000 claims description 41
- 230000008569 process Effects 0.000 claims description 21
- 230000008859 change Effects 0.000 claims description 14
- 229910000831 Steel Inorganic materials 0.000 claims description 11
- 239000010959 steel Substances 0.000 claims description 11
- 238000003466 welding Methods 0.000 claims description 8
- 238000013461 design Methods 0.000 abstract description 8
- 230000033001 locomotion Effects 0.000 description 9
- 230000007246 mechanism Effects 0.000 description 5
- 230000005540 biological transmission Effects 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
- G01N3/14—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces generated by dead weight, e.g. pendulum; generated by springs tension
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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
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/02—Details
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention belongs to the technical field of aircraft design, and particularly relates to an aircraft wing folding gravity load simulation loading device and method.
Description
Technical Field
The invention belongs to the technical field of aircraft design, and particularly relates to a device and a method for simulating loading of folding gravity loads of aircraft wings.
Background
The aircraft wing folding system is a special wing component for a fixed-wing aircraft, and can save aircraft carrier deck and aircraft base space by folding wings, so that not only equipment which is necessary for naval carrier aircraft, but also other types of aircraft wing structures can be used for reducing the occupied space of the aircraft in the ground and a storehouse. The folding system for the aircraft wing is generally composed of movable wing sections, a folding mechanism, folding actuators and other parts, and is a power device for driving the movable wing sections of the aircraft wing to fold and unfold. Because the aircraft wing folding process is complex in movement, the wing folding system must overcome resistance and output driving force required by wing folding so as to ensure smooth folding and unfolding of the wing, and therefore, relevant load test tests are required to be carried out, and the working performance of the device is ensured.
In the folding and unfolding process of the aircraft wing, the main load of the folding device is the weight of the wing and the mounting load, the gravity load simulation loading test is usually carried out in the development and production process of the wing folding system, and the deformation and the material stress of structural members are tested, so that the bearing capacity of the folding mechanism and the transmission parts of the folding actuator is correctly evaluated and estimated, and reliable basis is provided for product performance verification and optimized structural design.
The wing folding gravity load simulation loading device in the prior art generally adopts a direct loading mode, a model of a wing folding movable wing section is manufactured according to the proportion of 1:1, weights are hung at the gravity center position of the wing to simulate the wing folding gravity load, and the device has the defects that the structural size is large, the weights easily move and swing along with the movement of the wing in the loading process, the stability and the load simulation precision in the testing process are affected, the gravity load at the vertical position of the wing is difficult to simulate by directly using the loading mode of the weights, and meanwhile, the full-size component of the wing movable wing section is complex in structure, large in size and weight and high in manufacturing cost.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides an airplane wing folding gravity load simulation loading device, which adopts a cam mechanism to change the gravity load generated by loading weights, and accurately simulates the change of the gravity load according to the wing folding position, so that the gravity load at the vertical position of the wing can be simulated, and the device has the advantages of simple structure, compact size, good stability in the test process and high test precision.
In order to achieve the above effects, the technical scheme of the invention is as follows:
the utility model provides an aircraft wing folding gravity load simulation loading device, includes test base, one end is provided with two camshaft supports on the test base, is connected with the camshaft between two camshaft supports, the cam has been cup jointed on the camshaft, be provided with the cable winding reel on the cam, the cable winding reel passes through the loading cable and links to each other with movable wing section component, and the cam is connected with the loading weight through the weight cable, is fixed with movable hinge support on the movable wing section component, and folding hinge round pin axle passes the hinge hole on fixed hinge support and the movable hinge support respectively, makes movable wing section component can rotate around folding hinge axle for test base to simulate the folding and the expansion motion process of wing.
Further, the camshaft support is fixed to the test base by bolts.
Further, the movable wing section component is a rigid component formed by welding steel pipes, and the appearance is T-shaped.
Further, the test base other end is provided with two folding actuator installing supports, the both ends of wing folding actuator are fixed on folding actuator installing supports, rotatable rocking arm has on the folding actuator of wing, during operation wing folding actuator passes through motor and transmission system and drives the rocking arm rotation, drive wing folding and expansion at last, the rocking arm tip has a pinhole that is used for connecting the pull rod, the axis collineation of the pinhole on all rocking arms, the front and back both ends of pull rod respectively have a pinhole that the axis is parallel to each other, the connecting pin inserts in the rear end pinhole of pull rod and the pinhole of rocking arm tip simultaneously behind the pull rod, form gyration kinematic pair. The number of rocker arms is 1 to 4.
Further, two folding actuator mounting brackets are bolted to the test base.
Still further, the test base is fixed with 2 to 4 fixed hinge supports, each fixed hinge support is provided with a hinge hole, the axes of the hinge holes on all the fixed hinge supports are collinear, each movable hinge support is provided with a hinge hole, and the axes of the hinge holes on all the movable hinge supports are collinear; the folding hinge pin shaft respectively penetrates through hinge holes on the fixed hinge support and the movable hinge support, so that the movable wing section component rotates around the folding hinge shaft relative to the test base to simulate the folding and unfolding movement process of the wing.
Further, a pull rod support is fixed on the movable wing section component, a pin hole is formed in the end portion of the pull rod support, and a front connecting pin of the pull rod is inserted into the pin hole in the front end of the pull rod and the pin hole in the end portion of the pull rod support at the same time, so that a rotary kinematic pair is formed.
Further, the outline of the outer circle of the cam is a curve with a radius change, the minimum radius of the cam is zero, the surface of the outer circle of the cam is provided with a groove, and the center of the cam is provided with a round hole; the cable winding reel is a cylindrical part, the outer round surface of the cable winding reel is provided with a spiral groove, and the center of the cable winding reel is also provided with a round hole; the cam shaft passes through the round holes in the centers of the cam and the stay rope winding reel and is fixed with the round holes, the middle of the cam shaft is provided with a groove corresponding to the position of the cam, the stay rope winding reel and the cam can rotate around the cam shaft together, two ends of the cam shaft are supported on the cam shaft support, and the cam shaft support is fixed on the test base through bolts.
Further, the loading cable joint is fixed at the lower side of the front end of the movable wing section component, the loading cable is a steel wire rope, one end of the loading cable is fixed on the cable joint, the other end of the loading cable is fixed at the end part of a spiral groove of the cable winding drum and is wound on the cable winding drum, the pulley is disc-shaped, the outer circle of the pulley is provided with a groove, the middle part of the loading cable is arranged in the groove of the pulley, the middle of the pulley is provided with a hole, the loading cable is arranged on the pulley support through the pulley shaft and can freely rotate around the axis, and the pulley support is fixed on the test base through a bolt.
Further, the weight cable is wire rope, one end is fixed in the cam, the groove of cam is arranged in to the anterior segment of weight cable, the other end of weight cable is fixed on the weight couple at loading weight top, during operation loading weight natural sagging, the weight cable is strained under the weight effect of loading weight to apply a moment of torsion for the cam, drive the camshaft rotatory, and drag loading cable through the cable reel and load wing folding device, when the cam rotated the position that the radius is zero, the moment of torsion that the loading weight was applied to the cam was also zero, be equivalent to the vertical position of wing.
The working principle of the aeroplane wing folding gravity load simulation loading device is described as follows.
A simulated loading method for folding gravity load of aircraft wing includes such steps as fixing the test base to the fixed wing segment of aircraft wing, fixing the movable wing segment on the test base, fixing the movable hinge support to the movable wing segment, and connecting the hinge holes of two supports to form rotary kinematic pair. A loading cable connector is fixed at the lower side of the front end of the movable wing section component and is connected with a loading cable, and when the gravity load simulation test of the folding actuator of the aircraft wing is carried out, the loading cable is used for applying load to the folding actuator;
the gravity of loading weight passes through the weight cable and acts on the cam to drive the cable winder through the cam and rotate, drags the load cable through the pulley, the load cable passes through the cable joint on the movable wing section component and applys a moment for the movable wing section component, and applys a load for folding actuator through pull rod and rocking arm, simulate the gravity load of wing folding and unfolding in-process, can adjust the direction of the simulation load that acts on the movable wing section component through the pulley, and the size of load can pass through the design of cam profile curve, through the change of control cam radius, the change rule of gravity load in the folding of aircraft wing with the unfolding in-process accurately.
In particular, when the folding section of the wing movable section is positioned at the vertical position, the working radius corresponding to the cam is zero, and the load generated by the gravity loading weight on the folding actuator is also zero.
Compared with the prior art, the technical scheme of the aircraft wing folding gravity load simulation loading device has the following beneficial effects: through the change of the radius of the stay rope winding reel and the design of mechanism parameters, the tension on the load stay rope is changed according to a set rule, so that the gravity load in the wing folding process can be accurately simulated, the device is compact in structure and high in testing precision, the gravity load at the vertical position of the wing can be simulated, and meanwhile, the transverse movement amount of the weight in the test process is small, and the working stability is good.
Drawings
FIG. 1 is a block diagram of an aircraft wing fold gravity load simulation loading device.
FIG. 2 is a block diagram of a cam, cable spool and camshaft assembly.
The names of the components corresponding to the reference numerals in the above figures are as follows:
1-camshaft, 2-cam, 3-cable reel, 4-camshaft support, 5-bolt, 6-loading cable, 7-loading cable joint, 8-movable wing segment member, 9-movable hinge support, 10-folding hinge pin, 11-fixed hinge support, 12-wing folding actuator, 13-test base, 14-pull rod rear connecting pin, 15-rocker arm, 16-folding actuator mounting bracket, 17-pull rod, 18-bolt, 19-pull rod front connecting pin, 20-pull rod support, 21-bolt, 22-pulley shaft, 23-pulley support, 24-pulley, 25-loading weight, 26-weight hook, 27-weight cable.
Detailed Description
The following description of the present patent refers to the field of 'electric digital data processing'.
Example 1
The invention will be further described with reference to the accompanying drawings and examples, to which it is noted that embodiments of the invention include, but are not limited to.
As shown in fig. 1, the aircraft wing folding gravity load simulation loading device comprises a test base 13, a wing folding actuator 12, a rocker arm 15, a folding actuator mounting bracket 16, a fixed hinge support 11, a movable hinge support 9, a folding hinge pin 10, a movable wing segment component 8, a pull rod 17, a pull rod support 20, a pull rod front connecting pin 19, a pull rod rear connecting pin 14, a loading cable joint 7, a loading cable 6, a pulley 14, a pulley support 23, a pulley shaft 22, a cam shaft 1, a cam shaft support 4, a cable winding drum 3, a cam 2, a loading weight 25, a weight hook 26, a weight cable 27, bolts and other parts.
The test base 13 is a basic component of the whole loading device, the test base 13 is formed by welding square steel pipes and is fixed on the ground, two folding actuator mounting brackets 16 are fixed on the test base 13 through bolts 18, two ends of the wing folding actuator 12 are fixed on the folding actuator mounting brackets 16, swinging arms 15 capable of rotating are arranged on the wing folding actuator 12, the number of the swinging arms 15 is 2, a pin hole for connecting a pull rod 17 is formed in the end part of each swinging arm 15, the axes of the pin holes on the two swinging arms 15 are collinear, pin holes with mutually parallel axes are respectively formed in the front end and the rear end of the pull rod 17, and a connecting pin 14 behind the pull rod is simultaneously inserted into the pin hole at the rear end of the pull rod 17 and the pin hole at the end part of the swinging arm 15 to form a rotary kinematic pair.
The two fixed hinge supports 11 are fixed on the test base by welding, the fixed hinge supports 11 are provided with a hinge hole, and the axes of the hinge holes on the two hinge supports 11 are collinear.
The movable wing section member 8 is a rigid member formed by welding steel pipes, has a T-shaped appearance, and is fixedly provided with two movable hinge supports 9 in a welding mode, each movable hinge support 9 is provided with a hinge hole, and the axes of the hinge holes on the two movable hinge supports are collinear. The folding hinge pin shafts 10 respectively pass through hinge holes on the fixed hinge support 11 and the movable hinge support 9, so that the movable wing section component 8 can rotate around the folding hinge shafts 10 relative to the test base 13 to simulate the folding and unfolding movement process of the wing.
The pull rod support 20 is fixed on the movable wing section member 8 by welding, the end part of the pull rod support 20 is provided with a pin hole, and the pull rod front connecting pin 19 is simultaneously inserted into the pin hole at the front end of the pull rod 17 and the pin hole at the end part of the pull rod support 20 to form a rotary kinematic pair. When the pull rod 17 is moved by the rocker arm 15 on the wing fold actuator 12, the movable wing section member 8 can rotate about the axis of the fold hinge pin 10 from the horizontal extended position shown in fig. 1 to the vertical position shown in fig. 2.
The structure of the assembly of the cam 2, the stay wire coiling barrel 3 and the cam shaft 1 is shown in fig. 2, the outline of the outer circle of the cam 2 is a curve with radius change, the surface of the outer circle of the cam 2 is provided with a groove, and the assembly is used for accommodating a weight stay wire 27 in the loading process. In order to simulate the condition that the gravity load is zero, the minimum radius of the cam 2 is zero, and the center of the cam 2 is provided with a round hole; the cable winding reel 3 is a cylindrical part, the outer circumferential surface of the cable winding reel 3 is provided with a spiral groove, the center of the cable winding reel 3 is also provided with a round hole, the cam shaft 1 penetrates through the round holes in the centers of the cam 2 and the cable winding reel 3 and is fixed with the round holes, the middle of the cam shaft 1 is provided with a groove relative to the position of the cam 2, the cable winding reel 3 and the cam 2 can rotate around the cam shaft 1 together, two ends of the cam shaft 1 are supported on cam shaft supports 4, and the cam shaft supports 4 are fixed on a test base 13 through bolts 5.
The loading cable joint 7 is fixed at the lower side of the front end of the movable wing section component 8, the loading cable 6 is made of a steel wire rope, one end of the loading cable 6 is fixed on the loading cable joint 7, and the other end of the loading cable is fixed at the end part of the spiral groove of the cable winding drum 3 and is wound on the cable winding drum 3. The pulley 24 is disc-shaped, the outer circle of the pulley 24 is provided with a groove, the middle part of the loading inhaul cable 6 is arranged in the groove of the pulley 24, the middle part of the pulley 24 is provided with a hole, the pulley is arranged on two pulley supports 23 through a pulley shaft 22, the pulley supports 23 can rotate freely around the axis of the pulley shaft 22, and the pulley supports 23 are fixed on the test base 13 through bolts.
The weight cable 27 is made of a steel wire rope, one end of the weight cable 27 is fixed on the cam, the front section of the weight cable 27 is arranged in a groove of the cam 2, the other end of the weight cable 27 is fixed on a weight hook 26 at the top of the loading weight 25, the loading weight 25 naturally sags during operation, the weight cable 27 is tensioned under the weight action of the loading weight 25, a torque is applied to the cam 2, the cam shaft 1 is driven to rotate, and the loading cable 6 is dragged through the cable winding drum 3, so that the application of a simulated gravity load to the aircraft wing folding device is realized.
Example 2
The utility model provides an aircraft wing folding gravity load simulation loading device, includes test base 13, one end is provided with two camshaft supports on the test base 13, is connected with the camshaft between two camshaft supports, the cam has been cup jointed on the camshaft, be provided with the cable winding reel on the cam, the cable winding reel passes through the loading cable and links to each other with movable wing section component, and the cam is connected with the loading weight through the weight cable, is fixed with movable hinge support 9 on the movable wing section component 8, and folding hinge round pin axle 10 passes the hinge hole on fixed hinge support 11 and the movable hinge support 9 respectively, makes movable wing section component 8 can rotate around folding hinge axle for test base 13 to simulate the folding and unfolding motion process of wing.
Further, the camshaft support 4 is fixed to the test base 13 by bolts 5.
Further, the movable wing section member 8 is a rigid member formed by welding steel pipes, and has a T-shaped appearance.
Further, two folding actuator mounting brackets 16 are arranged at the other end of the test base 13, two ends of the wing folding actuator 12 are fixed on the folding actuator mounting brackets 16, a rotatable rocker arm 15 is arranged on the wing folding actuator 12, the wing folding actuator 12 drives the rocker arm 15 to rotate through a motor and a transmission system during operation, finally, the wing is driven to fold and unfold, a pin hole for connecting a pull rod 17 is formed in the end part of the rocker arm 15, the axes of the pin holes on all the rocker arms 15 are collinear, a pin hole with mutually parallel axes is formed in the front end and the rear end of the pull rod 17, and a connecting pin 14 behind the pull rod is simultaneously inserted into the pin hole at the rear end of the pull rod 17 and the pin hole at the end part of the rocker arm 15 to form a rotary kinematic pair. The number of rocker arms 15 is 1 to 4.
Further, two folding actuator mounting brackets 16 are secured to the test base 13 with bolts 18.
Still further, the test base 13 is fixed with 2 to 4 fixed hinge supports 11, each fixed hinge support 11 has a hinge hole, the axes of the hinge holes on all the fixed hinge supports 11 are collinear, each movable hinge support 9 has a hinge hole, and the axes of the hinge holes on all the movable hinge supports 9 are collinear; the folding hinge pin 10 passes through hinge holes on the fixed hinge support 11 and the movable hinge support 9 respectively, so that the movable wing section component 8 rotates around the folding hinge shaft relative to the test base 13 to simulate the folding and unfolding movement process of the wing.
Further, a pull rod support 20 is fixed on the movable wing section member 8, a pin hole is formed in the end portion of the pull rod support 20, and a pull rod front connecting pin 19 is inserted into the front end pin hole of the pull rod 17 and the pin hole in the end portion of the pull rod support 20 at the same time to form a rotary kinematic pair.
Further, the outline of the outer circle of the cam 2 is a curve with a radius change, the minimum radius of the cam 2 is zero, the surface of the outer circle of the cam 2 is provided with a groove, and the center of the cam 2 is provided with a round hole; the cable winding reel 3 is a cylindrical part, the outer round surface of the cable winding reel is provided with a spiral groove, and the center of the cable winding reel 3 is also provided with a round hole; the cam shaft 1 passes through the circular holes in the centers of the cam 2 and the cable winding reel 3 and is fixed with the cam 2, the middle of the cam shaft 1 is provided with a groove relative to the position of the cam 2, the cable winding reel 3 and the cam 2 can rotate around the cam shaft 1 together, two ends of the cam shaft 1 are supported on the cam shaft support 4, and the cam shaft support 4 is fixed on the test base 13 through the bolts 5.
Further, the loading cable joint 7 is fixed at the lower side of the front end of the movable wing section member 8, the loading cable 6 is a steel wire rope, one end of the loading cable 6 is fixed on the cable joint, the other end of the loading cable 6 is fixed at the end part of the spiral groove of the cable winding drum 3 and is wound on the cable winding drum 3, the pulley 24 is disc-shaped, a groove is formed in the outer circle of the loading cable, the middle part of the loading cable 6 is arranged in the groove of the pulley 24, a hole is formed in the middle of the pulley 24, the loading cable is installed on the pulley support 23 through the pulley shaft 22 and can rotate freely around the axis, and the pulley support 23 is fixed on the test base 13 through the bolt 21.
Further, the weight guy cable 27 is a steel wire rope, one end is fixed on the cam 2, the front section of the weight guy cable 27 is arranged in a groove of the cam 2, the other end of the weight guy cable 27 is fixed on the weight hook 26 at the top of the loading weight 25, the loading weight 25 naturally sags during operation, the weight guy cable 27 is tensioned under the weight action of the loading weight 25, a torque is applied to the cam 2 to drive the cam shaft 1 to rotate, the loading guy cable 6 is dragged by the guy cable winding drum 3 to load the wing folding device, and when the cam 2 rotates to a position with a radius of zero, the torque applied to the cam 2 by the loading weight 25 is also zero, which is equivalent to the vertical position of the wing.
The working principle of the aeroplane wing folding gravity load simulation loading device is described as follows.
A folding gravity load simulation loading method of an aircraft wing is characterized in that a test base 13 corresponds to a fixed wing section of the aircraft wing, a movable wing section component 8 corresponds to a movable wing section of the aircraft wing, a fixed hinge support 11 is fixed on the test base 13, a movable hinge support 9 is fixed on the movable wing section component 8, and a folding hinge shaft is connected with hinge holes of the two supports to form a rotary kinematic pair, so that the movable wing section component 8 can rotate relative to the test base 13, and folding and unfolding processes of the wing are simulated. A loading cable joint 7 is fixed at the lower side of the front end of the movable wing section component 8, a loading cable 6 is connected, and when the gravity load simulation test of the folding actuator 12 of the aircraft wing is carried out, the loading cable 6 is used for applying load to the folding actuator;
the gravity of the loading weight 25 acts on the cam 2 through the weight guy cable 27, the guy cable winding drum 3 is driven to rotate through the cam 2, the load guy cable is dragged through the pulley 24, a moment is applied to the movable wing segment component 8 through a guy cable joint on the movable wing segment component 8, a load is applied to the folding actuator through the pull rod 17 and the rocker arm 15, the gravity load in the folding and unfolding process of the wing is simulated, the direction of the simulated load acting on the movable wing segment component 8 can be regulated through the pulley 24, the size of the load can be regulated through the design of the profile curve of the cam 2, and the change rule of the gravity load in the folding and unfolding process of the wing of the aircraft can be accurately controlled through the change of the radius of the cam 2.
In particular, when the folding section of the wing movable section is in the vertical position, the working radius corresponding to the cam 2 is zero, and the load generated by the gravity of the loading weight 25 on the folding actuator is also zero.
Compared with the prior art, the technical scheme of the aircraft wing folding gravity load simulation loading device has the following beneficial effects: through the change of the radius of the guy cable winding drum 3 and the design of mechanism parameters, the tension on the load guy cable is changed according to a set rule, so that the gravity load in the wing folding process can be accurately simulated, the device is compact in structure and high in testing precision, the gravity load at the vertical position of the wing can be simulated, and meanwhile, the transverse movement amount of the weight in the test process is small, and the working stability is good.
The present invention is well achieved in accordance with the embodiments described above. It should be noted that, on the premise of the above structural design, even if some insubstantial changes or color rendering are made on the basis of the present invention, the essence of the adopted technical scheme is still the same as that of the present invention, so that the technical scheme is also within the protection scope of the present invention.
Claims (7)
1. An aircraft wing folding gravity load simulation loading device is characterized in that: the test base (13) is characterized in that two cam shaft supports are arranged at one end of the test base (13), a cam shaft is connected between the two cam shaft supports, a cam is sleeved on the cam shaft, a cable winding drum is arranged on the cam, the cable winding drum is connected with a movable wing section component through a loading cable, the cam is connected with a loading weight through a weight cable, a movable hinge support (9) is fixed on the movable wing section component (8), and a folding hinge pin shaft (10) respectively penetrates through hinge holes in the fixed hinge support (11) and the movable hinge support (9) to enable the movable wing section component (8) to rotate around the folding hinge shaft relative to the test base (13);
two folding actuator mounting brackets (16) are arranged at the other end of the test base (13), two ends of the wing folding actuator (12) are fixed on the folding actuator mounting brackets (16), a rotatable rocker arm (15) is arranged on the wing folding actuator (12), a pin hole for connecting a pull rod (17) is formed at the end part of the rocker arm (15), the axes of the pin holes on all the rocker arms (15) are collinear, a pin hole with the parallel axes is formed at the front end and the rear end of the pull rod (17), and a connecting pin (14) behind the pull rod is simultaneously inserted into the pin hole at the rear end of the pull rod (17) and the pin hole at the end part of the rocker arm (15) to form a rotary kinematic pair;
the outer circle profile of the cam (2) is a curve with radius change, the minimum radius of the cam (2) is zero, the outer circle surface of the cam (2) is provided with a groove, and the center of the cam (2) is provided with a round hole; the cable winding reel (3) is a cylindrical part, the outer circumferential surface of the cable winding reel is provided with a spiral groove, and the center of the cable winding reel (3) is also provided with a round hole; the cam shaft (1) penetrates through round holes in the centers of the cam (2) and the stay wire winding reel (3) and is fixed with the cam (2), a groove is formed in the middle of the cam shaft (1) relative to the cam (2), the stay wire winding reel (3) and the cam (2) can rotate around the cam shaft (1) together, two ends of the cam shaft (1) are supported on cam shaft supports (4), and the cam shaft supports (4) are fixed on a test base (13) through bolts (5);
the loading cable joint (7) is fixed at the lower side of the front end of the movable wing section component (8), the loading cable (6) is a steel wire rope, one end of the loading cable is fixed on the loading cable joint (7), the other end of the loading cable is fixed at the end part of the spiral groove of the cable winding drum (3) and is wound on the cable winding drum (3), the pulley (24) is disc-shaped, a groove is formed in the outer circle of the pulley, the middle part of the loading cable (6) is arranged in the groove of the pulley (24), a hole is formed in the middle of the pulley (24), the loading cable is installed on the pulley support (23) through the pulley shaft (22) and can rotate freely around the axis, and the pulley support (23) is fixed on the test base (13) through the bolt (21).
2. An aircraft wing fold gravity load simulation loading device according to claim 1, wherein: the camshaft support (4) is fixed on the test base (13) through bolts (5).
3. An aircraft wing fold gravity load simulation loading device according to claim 1, wherein: one end of a weight inhaul cable (27) is fixed in the cam (2) and is arranged in a groove of the cam (2), and the other end of the weight inhaul cable (27) is fixed on a weight hook (26) at the top of the loading weight (25).
4. An aircraft wing fold gravity load simulation loading device according to claim 1, wherein: the movable wing section component (8) is a rigid component formed by welding steel pipes, and the appearance is T-shaped.
5. An aircraft wing fold gravity load simulation loading device according to claim 1, wherein: a fixed hinge support (11) is fixed on the test base (13), a hinge hole is formed in each fixed hinge support (11), the axes of the hinge holes in all the fixed hinge supports (11) are collinear, a hinge hole is formed in each movable hinge support (9), and the axes of the hinge holes in all the movable hinge supports (9) are collinear; the folding hinge pin shaft (10) respectively passes through hinge holes on the fixed hinge support (11) and the movable hinge support (9) to enable the movable wing section component (8) to rotate around the folding hinge shaft relative to the test base (13).
6. An aircraft wing fold gravity load simulation loading device according to claim 1, wherein: a pull rod support (20) is fixed on the movable wing section component (8), a pin hole is formed in the end portion of the pull rod support (20), and a pull rod front connecting pin (19) is inserted into the front end pin hole of the pull rod (17) and the pin hole in the end portion of the pull rod support (20) at the same time to form a rotary kinematic pair.
7. A loading method of a loading device according to any one of claims 1-6, wherein: the method comprises the following steps:
the test base (13) corresponds to a fixed wing section of the aircraft wing, the movable wing section component (8) corresponds to a movable wing section of the aircraft wing, the fixed hinge support (11) is fixed on the test base (13), the movable hinge support (9) is fixed on the movable wing section component (8), and the hinge holes of the two supports are connected by the folding hinge shaft to form a rotary kinematic pair, so that the movable wing section component (8) can rotate relative to the test base (13) to simulate the folding and unfolding processes of the wing; a loading cable joint (7) is fixed at the lower side of the front end of the movable wing section component (8), a loading cable (6) is connected, and when the gravity load simulation test of the folding actuator (12) of the aircraft wing is carried out, the loading cable (6) is used for applying load to the folding actuator;
the gravity of the loading weight (25) acts on the cam (2) through the weight inhaul cable (27), the cable winding drum (3) is driven to rotate through the cam (2), the loading inhaul cable (6) is dragged through the pulley (24), the loading inhaul cable (6) applies a moment to the movable wing section component (8) through the loading inhaul cable connector (7) on the movable wing section component (8), a load is applied to the folding actuator through the pull rod (17) and the rocker arm (15), the gravity load in the wing folding and unfolding process is simulated, the direction of the simulated load acting on the movable wing section component (8) can be adjusted through the pulley (24), the size of the load can be designed through the profile curve of the cam (2), and the change rule of the gravity load in the wing folding and unfolding process of an aircraft can be accurately simulated through the change of the radius of the control cam (2).
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| CN114705473B (en) * | 2022-06-07 | 2022-08-26 | 中国飞机强度研究所 | Airplane vibration superposition fatigue strength testing system and low-rigidity load applying method thereof |
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