Shipboard aircraft nose landing gear ejection impact test device and method

Abstract

The invention belongs to the field of shipboard aircraft landing gear tests, and particularly relates to a shipboard aircraft nose landing gear ejection impact test device and method. According to the carrier-based aircraft nose landing gear ejection impact test device, an ejection impact test is carried out on a special test bed, the hanging basket, the balancing weight and the landing gear jointly form an equivalent mass system, the ejection load loading / releasing mechanism simulates an ejector to load an ejection rod, and the containment tensioning mechanism simulates passive loading of a containment rod in the ejection process. According to the invention, the ejection impact condition of the carrier-based aircraft undercarriage can be simulated in a laboratory environment, the ejection impact dynamic response is measured, and a test basis is provided for the development of the carrier-based aircraft undercarriage.

Description

Technical Field

[0001] The present application belongs to the field of carrier-based aircraft landing gear testing, and in particular relates to a carrier-based aircraft front landing gear ejection impact testing device and method. Background Art

[0002] When a carrier aircraft is launched by catapult, due to the drag of the catapult and the thrust of the engine, it will quickly obtain a large taxiing speed in a short period of time, and will successively experience the dynamic response process of ejection impact, such as the release of the check rod, ejection taxiing, and ejection extension. When the aircraft enters the ejection takeoff position and reaches the pre-ejection state, the catapult starts loading to force the check rod to release, and pulls the front landing gear ejection rod to make the aircraft taxi. At the end of the ejection stroke, the front landing gear ejection rod separates from the catapult, and the energy stored in the buffer is released. The front landing gear protrudes, causing the aircraft head to quickly lift up to increase the takeoff angle of attack to obtain additional lift, and then take off smoothly. During the ejection process, the landing gear successively experiences the sudden unloading of the check load and the ejection load, which causes the landing gear to produce a large vibration response in the vertical and heading directions, which is very likely to cause damage to the landing gear structure and affect flight safety.

[0003] At present, there is no mature catapult impact test device and method for the front landing gear of carrier-based aircraft that can simulate the heading speed in China.

[0004] Therefore, it is desired to have a technical solution to overcome or at least alleviate at least one of the above-mentioned defects of the prior art. Summary of the invention

[0005] The purpose of the present application is to provide a carrier-based aircraft front landing gear ejection impact test device and method to solve at least one problem existing in the prior art.

[0006] The technical solution of this application is:

[0007] The first aspect of the present application provides a carrier aircraft front landing gear ejection impact test device, comprising:

[0008] A bottom platform, wherein a receiving groove is provided on the bottom platform, and a rotating flywheel is installed in the receiving groove;

[0009] A test bench, the test bench being mounted on the bottom platform;

[0010] a lifting / releasing mechanism, the lifting / releasing mechanism being mounted on the test bench;

[0011] A hanging basket, the upper end of which is connected to the lifting / releasing mechanism, and a counterweight is installed inside the hanging basket;

[0012] The landing gear comprises a load-bearing strut, a wheel, a launch rod and a check rod, wherein:

[0013] The upper end of the load-bearing support is installed at the lower end of the hanging basket;

[0014] The wheel is mounted on the lower end of the load-bearing support, and the wheel is in contact with the rotating flywheel;

[0015] The ejection rod is mounted on the load-bearing support along the heading direction;

[0016] The check rod is installed on the load-bearing pillar along the reverse direction;

[0017] A hinge force sensor, the hinge force sensor is installed at the installation hinge point between the hanging basket and the landing gear;

[0018] an ejection load loading / releasing mechanism, the ejection load loading / releasing mechanism being mounted on the bottom platform and connected to the ejection rod;

[0019] A check and tensioning mechanism is installed on the bottom platform and is connected to the check and tensioning rod.

[0020] In at least one embodiment of the present application, the test bench includes columns symmetrically arranged on both sides of the accommodating groove, and a crossbeam located above the accommodating groove, and the columns are provided with rolling grooves.

[0021] In at least one embodiment of the present application, the lifting / releasing mechanism includes a motor, a wire rope, and an electromagnetic release lock, wherein:

[0022] The motor is fixedly mounted on the crossbeam of the test bench;

[0023] The electromagnetic release lock is connected to the upper end of the hanging basket;

[0024] One end of the steel wire rope is connected to the motor, and the other end is connected to the electromagnetic release lock.

[0025] In at least one embodiment of the present application, rollers are symmetrically arranged on both sides of the hanging basket, and the rollers are cooperatively connected with rolling grooves on the columns.

[0026] In at least one embodiment of the present application, the ejection load loading / releasing mechanism includes an ejection actuator and an ejection rod locking member, and the ejection rod locking member is connected to the ejection rod.

[0027] In at least one embodiment of the present application, the check and tensioning mechanism includes a check and brake cylinder and a check rod locking piece, and the check rod locking piece is connected to the check rod.

[0028] A second aspect of the present application provides a carrier aircraft front landing gear ejection impact test method, based on the carrier aircraft front landing gear ejection impact test device as described above, comprising:

[0029] Step 1: Fix the landing gear to the lower end of the hanging basket through a rigid mounting fixture, and adjust the counterweight so that the quality of the impact test system composed of the landing gear, hanging basket and counterweight meets the test requirements;

[0030] Step 2: Control the lifting / releasing mechanism to rise so that the landing gear leaves the rotating flywheel;

[0031] Step 3: Control the lifting / releasing mechanism to descend so that the landing gear is statically pressed onto the rotating flywheel, control the electromagnetic release lock of the lifting / releasing mechanism to be unlocked, and control the lifting / releasing mechanism to ascend so that the electromagnetic release lock is at a safe height;

[0032] Step 4: Control the ejection load loading / releasing mechanism to lock the ejection rod, and control the check tensioning mechanism to lock the check rod;

[0033] Step 5: Start the rotating flywheel to rotate in the opposite direction, and control the ejection load loading / releasing mechanism and the restraining tensioning mechanism to coordinate the loading to meet the force balance relationship in the horizontal direction;

[0034] Step 6: When the load on the check rod reaches the design load, the check tensioning mechanism is controlled to release the check rod, and the ejection load loading / releasing mechanism continues to load the ejection rod according to the load spectrum. When the rotating flywheel speed reaches the requirement and the load is applied, the ejection load loading / releasing mechanism is controlled to release the ejection rod. At this time, the load on the ejection rod is unloaded, the ejection rod rotates upward quickly to recover, the energy stored in the landing gear buffer is released, and the landing gear protrudes upward;

[0035] Step 7: Synchronously test the ejection impact dynamic response of the landing gear through the hinge force sensor, thereby completing an ejection impact test condition.

[0036] The invention has at least the following beneficial technical effects:

[0037] The carrier-based aircraft front landing gear ejection impact test device of the present application can simulate the carrier-based aircraft landing gear ejection impact in a laboratory environment and measure the ejection impact dynamic response, thereby providing a test basis for the development of the carrier-based aircraft landing gear. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] Figure 1 It is a schematic diagram of a carrier-based aircraft front landing gear ejection impact test device according to one embodiment of the present application.

[0039] in:

[0040] 1- bottom platform; 2- rotating flywheel; 3- test bench; 31- column; 32- crossbeam; 4- lifting / releasing mechanism; 41- motor; 42- wire rope; 43- electromagnetic release lock; 5- hanging basket; 6- counterweight; 7- landing gear; 71- load-bearing pillar; 72- wheel; 73- ejection rod; 74- restraint rod; 8- hinge force sensor; 9- ejection load loading / releasing mechanism; 10- restraint tensioning mechanism. DETAILED DESCRIPTION

[0041] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the embodiment of this application will be described in more detail below in conjunction with the drawings in the embodiment of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described embodiments are part of the embodiments of this application, not all of them. The embodiments described below with reference to the drawings are exemplary and are intended to be used to explain this application, and should not be construed as limitations on this application. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The embodiments of this application are described in detail below in conjunction with the drawings.

[0042] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the scope of protection of the present application.

[0043] The following is combined with Figure 1 This application is described in further detail.

[0044] The first aspect of the present application provides a carrier-based aircraft front landing gear ejection impact test device, comprising: a bottom platform 1, a rotating flywheel 2, a test bench 3, a lifting / releasing mechanism 4, a hanging basket 5, a counterweight 6, a landing gear 7, a hinge force sensor 8, an ejection load loading / releasing mechanism 9 and a restraining tensioning mechanism 10.

[0045] Specifically, Figure 1As shown, a receiving groove is provided on the base platform 1 for installing the rotating flywheel 2. The ground can be used as the base platform 1. The high-speed rotation of the rotating flywheel 2 simulates the speed of the front landing gear relative to the aircraft carrier during the catapult takeoff of the carrier-based aircraft, and the rotating flywheel 2 is required to reach 240km / h within 3s. The rotating flywheel 2 can bear a certain vertical load. The test bench 3 is installed on the bottom platform 1. The test bench 3 can serve as the main installation foundation and load-bearing structure of the catapult impact test device, and provide movement guidance for the hanging basket 5.

[0046] The lifting / releasing mechanism 4 is installed on the test bench 3, and can complete the functions of lifting, dropping and holding the test system. The upper end of the hanging basket 5 is connected to the lifting / releasing mechanism 4, and a counterweight block 6 is installed inside the hanging basket 5. The hanging basket 5 can serve as the installation basis of the landing gear 7 and can move freely vertically along the test bench 3. During the test, the load on the landing gear 7 is transmitted to the test bench 3 through the hanging basket 5. By adding the counterweight block 6, the equivalent mass of the landing gear 7 can be simulated. The hanging basket 5, the counterweight block 6 and the landing gear 7 together constitute an impact test system.

[0047] The landing gear 7 includes a load-bearing column 71, a wheel 72, a ejection rod 73 and a restraining rod 74, wherein the upper end of the load-bearing column 71 is installed on the lower end of the basket 5; the wheel 72 is installed on the lower end of the load-bearing column 71, and the wheel 72 is in contact with the rotating flywheel 2; the ejection rod 73 is installed on the load-bearing column 71 along the heading; and the restraining rod 74 is installed on the load-bearing column 71 along the counter-heading direction.

[0048] The hinge force sensor 8 is installed at the installation hinge of the hanging basket 5 and the landing gear 7, and is used to measure the load of the installation hinge during the ejection impact test.

[0049] The ejection load loading / releasing mechanism 9 is installed on the bottom platform 1, and is connected to the ejection rod 73. The ejection load loading / releasing mechanism 9 is installed in the heading direction, and is used to simulate the loading and rapid release of the traction load of the aircraft ejection rod 73 by the ship-borne ejection shuttle during the ejection takeoff extension test. The ejection load and boundary constraints must be released within 20ms.

[0050] The check and tension mechanism 10 is installed on the bottom platform 1 and connected to the check rod 74. The check and tension mechanism 10 is installed in the reverse heading direction and is used to apply a reverse heading load to the check rod 74, and is used to simulate the application of the check load in the ejection impact test.

[0051] In a preferred embodiment of the present application, the test bench 3 includes columns 31 symmetrically arranged on both sides of the receiving slot, and a crossbeam 32 located above the receiving slot, and a rolling groove is arranged on the column 31. The lifting / releasing mechanism 4 includes a motor 41, a wire rope 42, and an electromagnetic release lock 43, wherein the motor 41 is fixedly mounted on the crossbeam 32 of the test bench 3; the electromagnetic release lock 43 is connected to the upper end of the hanging basket 5; one end of the wire rope 42 is connected to the motor 41, and the other end is connected to the electromagnetic release lock 43. Rollers are symmetrically arranged on both sides of the hanging basket 5, and the rollers are matched and connected with the rolling grooves on the columns 31. The ejection load loading / releasing mechanism 9 includes an ejection actuator and an ejection rod locking member, and the ejection rod locking member is connected to the ejection rod 73. The check and tension mechanism 10 includes a check and tension cylinder and a check rod locking member, and the check rod locking member is connected to the check rod 74.

[0052] The ejection impact test device for the front landing gear of the carrier-based aircraft of the present application is carried out on a dedicated test bench 3. The hanging basket 5, the counterweight block 6 and the landing gear 7 together constitute an equivalent mass system. The ejection load loading / releasing mechanism 9 simulates the loading of the ejector on the ejection rod 73, and the restraint tensioning mechanism 10 simulates the passive loading of the restraint rod 74 during the ejection process.

[0053] Based on the above-mentioned carrier-based aircraft front landing gear ejection impact test device, the second aspect of the present application provides a carrier-based aircraft front landing gear ejection impact test method, comprising the following steps:

[0054] Step 1: Fix the landing gear 7 to the lower end of the hanging basket 5 through a rigid mounting fixture, and adjust the counterweight 6 so that the quality of the impact test system composed of the landing gear 7, the hanging basket 5 and the counterweight 6 meets the test requirements;

[0055] Step 2: Control the lifting / releasing mechanism 4 to rise, so that the landing gear 7 leaves the rotating flywheel 2;

[0056] Step 3: Control the lifting / releasing mechanism 4 to descend so that the landing gear 7 is statically pressed onto the rotating flywheel 2, control the electromagnetic release lock 43 of the lifting / releasing mechanism 4 to be unlocked, and control the lifting / releasing mechanism 4 to ascend so that the electromagnetic release lock 43 is at a safe height;

[0057] Step 4: Control the ejection load loading / releasing mechanism 9 to lock the ejection rod 73, and control the check tensioning mechanism 10 to lock the check rod 74;

[0058] Step 5: Start the rotating flywheel 2 to rotate in the opposite direction, and control the ejection load loading / releasing mechanism 9 and the restraining tensioning mechanism 10 to coordinate the loading to meet the force balance relationship in the horizontal direction;

[0059] Step 6: When the load on the check rod 74 reaches the design load, the check tensioning mechanism 10 is controlled to release the check rod 74, and the ejection load loading / releasing mechanism 9 continues to load the ejection rod 73 according to the load spectrum. When the speed of the rotating flywheel 2 reaches the requirement and the load application is completed, the ejection load loading / releasing mechanism 9 is controlled to release the ejection rod 73. At this time, the load on the ejection rod 73 is unloaded, and the ejection rod 73 rotates upward quickly to recover, and the energy stored in the landing gear buffer is released, and the landing gear 7 protrudes upward;

[0060] Step 7: Synchronously test the ejection impact dynamic response of the landing gear 7 through the hinge force sensor 8, thereby completing an ejection impact test condition.

[0061] The ejection impact test method for the front landing gear of a carrier-based aircraft of the present application is as follows: during the test, the ejection rod 73 and the check rod 74 are coordinated for loading to satisfy the force balance relationship in the horizontal direction, and the rotating flywheel 2 is started when the coordinated loading begins. When the load of the check rod 74 reaches the design load, the check rod 74 is released, and the ejection load loading / releasing mechanism 9 continues to maintain the loading until the dynamic response tends to be stable. When the speed of the rotating flywheel 2 reaches the requirement and the ejection load completes the load application according to the required load spectrum, the ejection load loading / releasing mechanism 9 is controlled to release the ejection rod 73, and the dynamic response of the landing gear system is synchronously tested.

[0062] The carrier-based aircraft front landing gear ejection impact test device and method of the present application can simulate the loading process and dynamic impact response process of the carrier-based aircraft front landing gear ejection in the test room, and its main advantages are as follows:

[0063] a. It can simulate the load on the front landing gear of a carrier-based aircraft during catapult takeoff, and can simulate the heading speed of the landing gear by rotating the flywheel;

[0064] b. It can measure the load at the landing gear installation hinge point of the aircraft's front landing gear during the ejection impact process, providing test data support for the design and verification of the landing gear installation structure.

[0065] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A carrier-based aircraft front landing gear ejection impact test device, characterized in that: include: A bottom platform (1), wherein a receiving groove is provided on the bottom platform (1), and a rotating flywheel (2) is installed in the receiving groove; A test bench (3), wherein the test bench (3) is installed on the bottom platform (1); A lifting / releasing mechanism (4), wherein the lifting / releasing mechanism (4) is mounted on the test bench (3); A hanging basket (5), the upper end of which is connected to the lifting / releasing mechanism (4), and a counterweight (6) is installed inside the hanging basket (5); A landing gear (7), the landing gear (7) comprising a load-bearing support (71), a wheel (72), a catapult rod (73) and a check rod (74), wherein: The upper end of the load-bearing support (71) is mounted on the lower end of the hanging basket (5); The wheel (72) is mounted on the lower end of the load-bearing support (71), and the wheel (72) is in contact with and connected to the rotating flywheel (2); The ejection rod (73) is mounted on the load-bearing pillar (71) along the heading direction; The check rod (74) is installed on the load-bearing pillar (71) along the reverse direction; A hinge force sensor (8), the hinge force sensor (8) being installed at a hinge point between the hanging basket (5) and the landing gear (7); An ejection load loading / releasing mechanism (9), wherein the ejection load loading / releasing mechanism (9) is mounted on the bottom platform (1), and the ejection load loading / releasing mechanism (9) is connected to the ejection rod (73); A check and tensioning mechanism (10), wherein the check and tensioning mechanism (10) is installed on the bottom platform (1), and the check and tensioning mechanism (10) is connected to the check rod (74).

2. The ejection impact test device for the front landing gear of a carrier aircraft according to claim 1, characterized in that: The test bench (3) comprises columns (31) symmetrically arranged on both sides of the receiving groove, and a crossbeam (32) located above the receiving groove, and rolling grooves are arranged on the columns (31).

3. The ejection impact test device for the front landing gear of a carrier aircraft according to claim 2, characterized in that: The lifting / releasing mechanism (4) comprises a motor (41), a steel wire rope (42) and an electromagnetic release lock (43), wherein: The motor (41) is fixedly mounted on a crossbeam (32) of the test bench (3); The electromagnetic release lock (43) is connected to the upper end of the hanging basket (5); One end of the steel wire rope (42) is connected to the motor (41), and the other end is connected to the electromagnetic release lock (43).

4. The ejection impact test device for the front landing gear of a carrier aircraft according to claim 3, characterized in that: Rollers are symmetrically arranged on both sides of the hanging basket (5), and the rollers are matched and connected with rolling grooves on the columns (31).

5. The ejection impact test device for the front landing gear of a carrier aircraft according to claim 4, characterized in that: The ejection load loading / releasing mechanism (9) comprises an ejection actuator and an ejection rod locking piece, and the ejection rod locking piece is connected to the ejection rod (73).

6. The ejection impact test device for the front landing gear of a carrier aircraft according to claim 5, characterized in that: The check and tension mechanism (10) comprises a check and brake cylinder and a check rod locking piece, wherein the check rod locking piece is connected to the check rod (74).

7. A carrier aircraft front landing gear ejection impact test method, based on the carrier aircraft front landing gear ejection impact test device according to claim 6, characterized in that: include: Step 1: fix the landing gear (7) to the lower end of the hanging basket (5) by a rigid mounting fixture, and adjust the counterweight (6) so that the quality of the impact test system composed of the landing gear (7), the hanging basket (5) and the counterweight (6) meets the test requirements; Step 2: Control the lifting / releasing mechanism (4) to rise so that the landing gear (7) leaves the rotating flywheel (2); Step 3: Control the lifting / releasing mechanism (4) to descend so that the landing gear (7) is statically pressed onto the rotating flywheel (2), control the electromagnetic release lock (43) of the lifting / releasing mechanism (4) to be unlocked, and control the lifting / releasing mechanism (4) to ascend so that the electromagnetic release lock (43) is at a safe height; Step 4: Control the ejection load loading / releasing mechanism (9) to lock the ejection rod (73), and control the check tensioning mechanism (10) to lock the check rod (74); Step 5: Start the rotating flywheel (2) to rotate in the opposite direction, and control the ejection load loading / releasing mechanism (9) and the restraining tensioning mechanism (10) to coordinate the loading to meet the force balance relationship in the horizontal direction; Step 6: When the load on the check rod (74) reaches the design load, the check tensioning mechanism (10) is controlled to release the check rod (74), and the ejection load loading / releasing mechanism (9) continues to load the ejection rod (73) according to the load spectrum. When the speed of the rotating flywheel (2) reaches the requirement and the load application is completed, the ejection load loading / releasing mechanism (9) is controlled to release the ejection rod (73). At this time, the load on the ejection rod (73) is unloaded, and the ejection rod (73) rotates upward quickly to recover, and the energy stored in the landing gear buffer is released, and the landing gear (7) protrudes upward; Step 7: Synchronously test the ejection impact dynamic response of the landing gear (7) through the hinge force sensor (8), thereby completing an ejection impact test condition.

Images