CN116923725A - Wing lift force test method for simulating ship-based aircraft full aircraft drop test - Google Patents
Wing lift force test method for simulating ship-based aircraft full aircraft drop test Download PDFInfo
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- 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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- 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
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Abstract
The invention provides a wing lift force test method for simulating a ship-based aircraft full-aircraft drop test, and belongs to the technical field of aircraft full-aircraft drop tests. According to the method, in the whole aircraft drop test process of the carrier aircraft, a plurality of loading points are arranged at different wing rib positions according to the space size and the lift distribution relation of the wing, the loading points are connected with a lift distribution device, and lift is provided for the wing through the lift distribution device. The invention solves the problem that the laboratory environment simulation method has low consistency with the real service environment because the centralized load simulation method adopted by the existing ship-based aircraft full aircraft drop test when the wing lift force is provided can not check the actual condition that part of the wing sections and the wing clamping plates have overlarge quality, and has the advantages of reducing the simulated lifting load pitching moment generated by the gesture change in the aircraft drop process during single-point loading and enabling the gesture change in the aircraft drop process to be more real.
Description
Technical Field
The invention relates to the technical field of aircraft full-aircraft drop tests, in particular to a wing lift test method for simulating a carrier-based aircraft full-aircraft drop test.
Background
As is well known, in order to verify the cushioning performance of the landing gear under the action of the carrier-borne load, the dynamic response of the aircraft body, the reliability of important components, the overload borne by drivers, passengers and airborne equipment, and the like, the carrier-borne aircraft needs to pass a full-size aircraft full-aircraft drop test, and the aircraft landing load and the dynamic response of the body and important equipment caused by the landing ground load are checked in a laboratory environment.
Because of the possibility of failure of the barrier, the aircraft needs to maintain a high heading speed, in which case there is a high lift on the wing and a high heading speed is maintained, so that the wing lift is always acting on the airframe.
The ship-based aircraft whole aircraft drop test is a test for simulating the free falling body of a full-size aircraft to strike the ground in a laboratory environment, and is used for testing physical quantities such as ground load, strain change of a designated part of the whole aircraft, gravity center sinking displacement, sinking speed, acceleration of the designated part and the like in the process of striking the ground. The whole aircraft drop test is a test for researching dynamic response of an engine body and a landing gear in the whole aircraft drop process of the carrier aircraft. The carrier-based aircraft landing sinking speed is about 7m/s, and the impact energy is more than 4 times of that of the land-based aircraft. Obvious dynamic response is generated in the engine body structure in the process of landing impact, and the impact environment also has adverse effects on the reliability and service life of airborne weapons, engines and high-sensitivity airborne equipment.
The method is characterized in that the carrier-based aircraft landing load is simulated in a laboratory environment, the mass of an aircraft cannot be reduced, an energy equivalent drop test method is adopted, and a drop test method with simulated lift can only be adopted, so that wing lift force must be applied through a specific device, the landing load and structural response of a test piece are evaluated under the action of the wing lift force, and the like, and the wing lift force simulation in the whole-aircraft drop test is a key technology for success or failure of the whole-aircraft drop test.
At present, a centralized load simulation method is used for lift simulation of a ship-based aircraft full-aircraft drop test at home and abroad (because a hanging point capable of being directly connected with an imitation lifting actuator is not arranged on an aircraft wing, a clamp is generally arranged on the aircraft wing and is attached to the aircraft wing, and a single lug is directly connected with the actuator on the clamp, the method is called a centralized load simulation method because the lift of the aircraft wing directly acts on a connecting part), and the method has great difference from the actual stress condition of the aircraft wing, and has the following defects: the acting force is applied to the root of the wing during the concentrated load simulation, and the examination from the root of the wing to the wing tip is absent; after the carrier-based aircraft touches a platform in the test, the pitching attitude of the aircraft can be changed due to the action of a front landing gear and a main landing gear or the surging of fuel oil in an oil tank, so that the gravity center position of the aircraft is changed, but the loading point of the simulated lift force is unchanged at the moment, so that the simulated lift force can generate additional pitching moment to influence the attitude of the aircraft; the method for simulating the lift force by the concentrated load concentrates the lift force of the whole wing at one point, and the local load at the loading point is also caused to be over-checked.
Disclosure of Invention
The invention solves the technical problems that: the centralized load simulation method adopted by the existing ship-based aircraft full-aircraft drop test when the wing lift force is provided cannot check the actual condition that the quality of part of the wing sections and the wing clamping plates is overlarge, so that the consistency of the laboratory environment simulation method and the real service environment is low.
In order to solve the problems, the technical scheme of the invention is as follows:
a wing lift test method for simulating a ship-based aircraft full aircraft drop test comprises the following steps:
s1, installing an imitation lifting cylinder: fixing the lifting-imitating barrel on the top of the bearing frame in the laboratory through the fixing seat, and filling high-pressure gas into the lifting-imitating barrel;
s2, equivalent loading points: according to the requirement of a ship-based aircraft full aircraft drop test on lift simulation, the lift of a wing is equivalent to a wing rib, a loading area is arranged at a position corresponding to the wing rib, and loading points are selected from the loading area;
s3, installing a lifting force distribution device: the lifting force distribution device is fixed on the loading point and connected with the lifting force simulation barrel through a chain;
s4, the lift force distribution device provides lift force: in the ship-based aircraft full-aircraft drop test, the lift-simulating cylinder drives the lift force distribution device to provide lift force for the wing of the ship-based aircraft.
Further, the top of the imitation lifting cylinder is fixed on the top of the bearing frame in the laboratory through a fixing seat.
Description: the simulated lifting force can be ensured to be adjusted according to test requirements by fixing the simulated lifting cylinder at the top of the bearing frame.
Further, an air chamber is arranged in the imitation lifting cylinder, a piston is fixed on the inner wall of the top of the air chamber, a piston rod penetrating out of the imitation lifting cylinder is connected to the piston, and a safety valve is further arranged at the bottom of the imitation lifting cylinder.
Description: the pressure change of the high-pressure gas in the imitation lifting cylinder fixed at the top of the bearing frame is within five percent in the compression process, and the high-pressure gas can be approximately understood as load stabilization, namely, stable lifting force is provided for the wing.
Further, the pressure calculation formula of the high-pressure gas is:
F = P*S
in the above formula, F is the load provided by the simulated lift cylinder, namely the simulated wing lift force; p is the pressure of the high-pressure gas; s is the area of the piston.
Preferably, the lift distribution device comprises one primary lever, two secondary levers and four tertiary levers; the top of the primary rod is hung at the bottom of the imitation lifting cylinder through a chain; the two secondary rods are hung on two sides of the bottom of the primary rod through chains respectively; the four three-level rods are in a group, and are hung on two sides of the bottom of the two-level rods through chains respectively; the two sides of the bottom of the three-level rod are respectively connected with loading points on the wing through chains.
Description: the lift force distribution device provides lift force for the wing based on a plurality of loading points respectively selected on wings on two sides of the carrier-based aircraft based on wing rib positions, and can meet the requirements of simulating lift force for aircraft landing.
Preferably, the hanging point distance between the bottom of the primary rod and the connection of the two secondary rods is inversely proportional to the load ratio borne by the secondary rods; the hanging point distance between the bottom of the secondary rod and the connection of the two tertiary rods is inversely proportional to the load ratio borne by the tertiary rods; the distance between the hanging points is the distance between the connecting point of the chain and the piston rod in the horizontal direction.
Description: the lift force distribution device can adjust and select the positions of loading points according to the shapes of the wings and the distribution positions of the wing ribs of different carrier-based aircraft, so that the wing lift force test method is applicable to the carrier-based aircraft all-aircraft drop test of most carrier-based aircraft.
Preferably, the loading points are arranged in each loading area in a pairwise corresponding manner; each loading area is respectively positioned right above each wing rib on the wing and comprises the wing rib corresponding to the upper surface of the wing; the position relation between the loading point and the loading area is as follows: the two loading points are centrally located in the loading area and the distance between the two loading points is two-thirds of the length of the loading area.
Description: the loading area can be selected according to the requirement of the ship-based aircraft all-aircraft drop test on the lifting load, so that the size and shape of the loading area can be determined according to actual conditions and can be the same or different.
Further preferably, the loading area is stuck with an encrypted canvas; the encryption canvas is adhered to the wing through glue.
Description: the lift force distribution device applies the simulated lift load through the encrypted canvas, the additional mass can be controlled within 50 kg, and the influence of the additional mass on the dynamic response of the drop test aircraft is greatly reduced.
The beneficial effects of the invention are as follows:
(1) The lift simulation device for the full-aircraft landing of the carrier-based aircraft is provided, the action process of wing lift in the full-aircraft landing test process is simulated in a laboratory, a verification way is provided for checking the full-aircraft landing performance of the carrier-based aircraft, and the technical risk of real aircraft landing adaptation test flight verification is reduced;
(2) The multipoint lift-simulating loading method can reduce the lift-simulating load pitching moment generated by the posture change in the aircraft earthquake falling process during single-point loading, so that the posture change in the aircraft earthquake falling process is more real;
(3) The multi-point simulated lift loading method uniformly distributes the simulated lift of the whole wing on a plurality of loading points, and is a surface loading mode, compared with a concentrated loading lift simulation method, the problem of overlarge local load of the wing is avoided;
(4) The multipoint distributed lifting loading method applies the simulated lifting load through the encrypted canvas, the additional mass can be controlled within 50 kg, and the influence of the additional mass on the dynamic response of the drop test aircraft is greatly reduced.
Drawings
FIG. 1 is a test state diagram of a wing lift test method for simulating a ship-based aircraft full-aircraft drop test in embodiment 3 of the invention;
FIG. 2 is a structural view of a lift distribution device in embodiment 1 of the present invention;
FIG. 3 is a view showing a construction of a lift-simulating cylinder in example 2 of the present invention;
FIG. 4 is a graph of the loading point profile on a wing in example 3 of the present invention;
FIG. 5 is a flow chart of a method for simulating the lift force of a wing in a ship-based aircraft full aircraft drop test according to the embodiment 3 of the invention;
the device comprises a 1-lift force distribution device, a 11-primary rod, a 12-secondary rod, a 13-tertiary rod, a 2-lift simulating cylinder, a 21-fixing seat, a 22-air chamber, a 23-piston, a 24-piston rod and a 25-safety valve.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail below with reference to the accompanying drawings, and it is apparent that the described embodiments are only some embodiments of the present invention, not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The terminology used in the embodiments of the invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used in this application and the appended claims, the singular forms "a," "an," and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise, the "plurality" generally includes at least two.
The invention is further illustrated by the following examples. In order to solve the problem that the actual condition of the ship-based aircraft falling shock cannot be attached to the centralized load simulation method adopted by the existing ship-based aircraft full-aircraft falling shock test when the wing lifting force is provided, and test data lack of reality, the embodiment of the invention provides a wing lifting force test method for simulating the ship-based aircraft full-aircraft falling shock test, which is shown in fig. 5.
Example 1: the present embodiment describes the structure of the lift force distribution device 1, and as shown in fig. 2, the lift force distribution device 1 includes one primary lever 11, two secondary levers 12, and four tertiary levers 13; the top of the primary rod 11 is hung at the bottom of the imitation lifting cylinder 2 through a chain; the two secondary rods 12 are hung on two sides of the bottom of the primary rod 11 through chains respectively; the four three-level rods 13 are in a group, and are hung on two sides of the bottom of the two-level rod 12 through chains respectively; the two sides of the bottom of the three-stage rod 13 are respectively connected with loading points on the wing through chains.
Alternatively, the hanging point distance between the bottom of the primary rod 11 and the two secondary rods 12 is inversely proportional to the load ratio carried by the secondary rods 12; the hanging point distance of the bottom of the secondary rod 12 and the connection of the two tertiary rods 13 is inversely proportional to the load ratio borne by the tertiary rods 13; the hanging point distance is the distance between the chain connecting point and the piston rod 24 in the horizontal direction.
In this embodiment, the load ratio of the two secondary levers 12 is 1:1, therefore, the hanging point distance between the bottom of the primary rod 11 and the connection of the two secondary rods 12 is the same; the load ratio of the two tertiary bars 13 is 1:1, the hanging point distance between the bottom of the secondary rod 12 and the connection of the two tertiary rods 13 is the same.
Example 2: in this embodiment, the structure of the lift-simulating cylinder 2 is described, as shown in fig. 3, an air chamber 22 is provided in the lift-simulating cylinder 2, a piston 23 is fixed to the inner wall of the top of the air chamber 22, a piston rod 24 penetrating the lift-simulating cylinder 2 is disposed on the piston 23, and a safety valve 25 is further provided at the bottom of the lift-simulating cylinder 2.
It can be understood that the pressure change of the high-pressure gas (calculated according to the area load of the piston 23) in the lifting-simulated cylinder 2 provided by the embodiment is within five percent in the whole ship-based aircraft drop test process, and can be approximately understood as load stabilization, namely, stable lifting force is provided for the wing.
In the embodiment, the high-pressure gas is compressed air, and the pressure of the high-pressure gas is set by the requirement of the ship-based aircraft on the lift force of the wing in the full aircraft drop test; the pressure calculation formula of the high-pressure gas is as follows:
F = P*S
in the above formula, F is the load provided by the simulated lift cylinder 2, namely the simulated wing lift force; p is the pressure of the high-pressure gas; s is the area of the piston 23.
Example 3: the present embodiment describes a wing lift test method for simulating a ship-based aircraft full aircraft drop test based on the lift distribution device 1 of embodiment 1 and the lift simulating cylinder 2 of embodiment 2, and includes the following steps, as shown in fig. 5:
s1, installing an imitation lifting cylinder 2: fixing the imitation lifting cylinder 2 on the top of a bearing frame in a laboratory through a fixing seat 21, and filling high-pressure gas into the imitation lifting cylinder 2;
s2, equivalent loading points: according to the requirement of a ship-based aircraft full aircraft drop test on lift simulation, the lift of a wing is equivalent to a wing rib, a loading area is arranged at a position corresponding to the wing rib, and loading points are selected from the loading area;
s3, installing a lift force distribution device 1: the lift force distribution device 1 is fixed on the loading point, and the lift force distribution device 1 and the imitation lifting cylinder 2 are connected through a chain;
s4, the lift force distribution device 1 provides lift force: in the ship-based aircraft full-aircraft drop test, the lift simulating cylinder 2 drives the lift distributing device 1 to provide lift for the wing of the ship-based aircraft.
In this embodiment, the loading points are disposed in each loading area in a corresponding manner; each loading area is respectively positioned right above each wing rib on the wing and comprises the wing rib corresponding to the upper surface of the wing; the position relation between the loading point and the loading area is as follows: the two loading points are centrally located in the loading area and the distance between the two loading points is two-thirds of the length of the loading area.
In this embodiment, as shown in fig. 4, four loading areas with the same shape and size are provided, and the single-side lift load is equivalent to eight loading points, each two loading points are arranged in one loading area, and the eight loading points correspond to four wing ribs of the aircraft wing in pairs.
In this embodiment, the loading area is stuck with an encrypted canvas; the encrypted canvas is adhered to the wing through glue, and in the embodiment, the glue is FN-305 brand; therefore, when the lift distribution device 1 provides lift for the aircraft wing, the simulated lift load is applied by the encrypted canvas, the additional mass can be controlled within 50 kg, and the influence of the additional mass on the dynamic response of the drop test aircraft is greatly reduced.
Example 4: example 4 differs from example 1 in that: the load ratio of the two secondary rods 12 is 1:2, and the distance between the two hanging points on the primary rod 11 is 2:1. The pressure of the imitation lifting cylinder 2 is adjusted according to the total load, the load on the secondary rod 12 is adjusted according to the position of the connecting point of the primary rod 11, and the lifting force distribution device 1 is finally connected with the loading point on the wing by pushing the same. Therefore, the hanging point distances of the secondary rod 12 and the tertiary rod 13 are not uniformly distributed, and the hanging point distances are divided according to the actual stress condition of the wing.
From the integral angle of the ship-based aircraft full-aircraft drop test, the wing lift test method provided by the embodiment of the invention replaces lift simulating equipment for providing lift in the ship-based aircraft full-aircraft drop test and the working process thereof;
the existing ship-based aircraft all-aircraft drop test process is as follows: before the test, firstly, confirming whether the state of the test piece, including the weight of the test piece, the filling parameters of the landing gear and the like, meets the requirements of a test task book; and secondly, checking whether the force measuring platform, the lifting simulating equipment, the belt rotating system and the like normally operate. During the test, the lengths of the four lifting ropes are adjusted through adjusting the adjusting screw sleeves at the joint of the lifting ropes and the wing clamping plates, the pitching and rolling postures of the aircraft are adjusted through different lengths of the lifting ropes, and finally whether the posture of a test piece meets the test requirement is checked. After the pitching and rolling postures of the airplane are adjusted in place, the test piece is lifted through the lifting system. After the test piece is lifted to a preset height by the lifting system, the landing gear wheels are turned by the airplane heading speed simulation system through the reverse heading synchronous belt. When the wheel reaches a preset rotating speed and the state is stable, a test piece throwing instruction is issued, the sinking speed of the airplane is required to reach a specified value at the moment when the wheel contact table of the test piece is touched, and meanwhile, the lifting weight ratio acting on the airplane is enabled to reach 1. Test data were recorded throughout the test run down until the aircraft stopped. And for the free flight hooking test working condition, the free flight hooking landing working condition of the carrier-based aircraft is simulated by releasing the interval between the front lifting point of the aircraft body and the rear lifting point of the aircraft body, and the additional moment and the additional sinking speed of the free flight hooking landing on the front landing gear are generated. The putting postures of different test states are realized by adjusting the lengths of four hanging strips at the front hanging point. When the aircraft is tested, firstly, the aircraft is lifted to the required height, the belt rotating device is started, after the belt rotating speed reaches the required value of the task book, the front hanging point and the rear hanging point are released at intervals, the aircraft falls freely, and a group of carrier-based aircraft free flight hooking landing test working conditions are completed.
It will be appreciated that the aircraft landing simulation lift requirements are as follows: the wing lift force is kept basically constant in the process that the aircraft is below the gravity center displacement zero after the aircraft landing; the wing lift force is applied in each loading area and is consistent with the resultant force of the required load; the motion gesture of the aircraft is not influenced after wing lifting force is applied in the aircraft landing process. The above requirements are ensured by the lift distribution device 1 according to the embodiment of the invention, which is connected with eight loading points.
The above content is based on the requirements of national army standard's on-board aircraft strength and rigidity specification-ground test (GJB 2758-96), national army standard's on-board structural strength specification-ground test (GJB 67 A.9-2008) and national army standard's on-board structural strength specification-ground load (GJB 67 A.4-2008), and belongs to the prior art.
Example 5: after combining embodiments 1 to 4 of the present invention, the embodiment describes a method for testing the drop of a whole ship-borne aircraft, which comprises the following steps:
s1, detecting the state of the carrier-borne aircraft:
before a ship-based aircraft full aircraft drop test, checking the state of the ship-based aircraft, including the weight of the ship-based aircraft and landing gear filling parameters;
s2, detecting the state of the installation test equipment:
the method comprises the steps that lift force distribution devices 1 are arranged on wings on two sides of a carrier aircraft, the carrier aircraft is lifted, and the height of the carrier aircraft in a full aircraft drop test of the carrier aircraft is confirmed; checking whether a force measuring platform, lifting simulating equipment and a belt transfer system for a ship-based aircraft full aircraft drop test run normally or not;
s3, adjusting pitching and rolling postures of the carrier-based aircraft, and lifting the carrier-based aircraft to the test height;
s4, throwing the carrier-based aircraft after the landing gear wheels are rotated:
the landing gear wheel is rotated by an inverse course synchronous belt of the aircraft course speed simulation system, a carrier aircraft throwing instruction is issued after the landing gear wheel reaches a preset rotating speed and the state is stable, the landing gear wheel is contacted with a platform instantly, the sinking speed of the carrier aircraft reaches a specified value, and meanwhile lifting simulation equipment provides lifting force for the carrier aircraft;
s5, test data tested in the whole process from the falling of the test machine to the stop of the aircraft.
It can be appreciated that in step S2, the installation of the lift distribution device 1 on the wings of the two sides of the carrier aircraft includes the following: the imitation lifting cylinder 2 is fixed on the top of the bearing frame in the laboratory through a fixing seat 21; according to the requirement of the ship-based aircraft full-aircraft drop test on lift simulation, the lift is equivalent to a wing rib of a wing, a loading area is determined according to the position of the wing rib, and loading points are determined in the loading area; fixing the lift force distribution device 1 at the loading point; the lift force distribution device 1 is connected with the imitation lifting cylinder 2 through a chain.
It can be appreciated that the force measuring platform, the belt transfer system and the airplane heading speed simulation system provided in the steps are all existing laboratory equipment.
Claims (9)
1. The wing lift test method for simulating the ship-based aircraft full aircraft drop test is characterized by comprising the following steps of:
s1, installing an imitation lifting cylinder (2): the simulated lifting cylinder (2) is fixed at the top of the bearing frame in the laboratory through the fixing seat (21), and high-pressure gas is filled into the simulated lifting cylinder (2);
s2, equivalent loading points: according to the requirement of a ship-based aircraft full aircraft drop test on lift simulation, the lift of a wing is equivalent to a wing rib, a loading area is arranged at a position corresponding to the wing rib, and loading points are selected from the loading area;
s3, installing a lifting force distribution device (1): the lifting force distribution device (1) is fixed on the loading point, and the lifting force distribution device (1) is connected with the lifting simulating cylinder (2) through a chain;
s4, the lift force distribution device (1) provides lift force: in a ship-based aircraft full aircraft drop test, an imitation lifting cylinder (2) drives a lifting force distribution device (1) to provide lifting force for a ship-based aircraft wing.
2. The wing lift test method for simulating the ship-based aircraft full-aircraft drop test according to claim 1, wherein the top of the lift-simulating cylinder (2) is fixed on the top of a bearing frame in a laboratory through a fixing seat (21).
3. The wing lift test method for simulating the ship-based aircraft full-aircraft drop test according to claim 2, wherein an air chamber (22) is arranged in the lift-simulating cylinder (2), a piston (23) is fixed on the inner wall of the top of the air chamber (22), a piston rod (24) penetrating out of the lift-simulating cylinder (2) is connected to the piston (23), and a safety valve (25) is further arranged at the bottom of the lift-simulating cylinder (2).
4. The method for simulating the wing lift force in the ship-based aircraft full-aircraft drop test according to claim 3, wherein the high-pressure gas is compressed air, and the pressure of the high-pressure gas is set by the requirement of the ship-based aircraft full-aircraft drop test on the wing lift force.
5. The wing lift test method for simulating the ship-based aircraft full aircraft drop test according to claim 4, wherein the pressure calculation formula of the high-pressure gas is as follows:
F = P*S
in the above formula, F is the load provided by the simulated lift cylinder (2), namely the simulated wing lift force; p is the pressure of the high-pressure gas; s is the area of the piston (23).
6. A wing lift test method for simulating a ship-based aircraft full aircraft drop test according to claim 3, wherein the lift distribution device (1) comprises a primary lever (11), two secondary levers (12) and four tertiary levers (13); the top of the primary rod (11) is hung at the bottom of the lifting-imitating barrel (2) through a chain; the two secondary rods (12) are hung on two sides of the bottom of the primary rod (11) through chains respectively; the four tertiary rods (13) are in a group, and are hung on two sides of the bottom of the secondary rod (12) through chains respectively; the two sides of the bottom of the three-level rod (13) are respectively connected with loading points on the wing through chains.
7. The wing lift test method for simulating a ship-based aircraft full aircraft drop test according to claim 6, wherein the hanging point distance between the bottom of the primary rod (11) and the two secondary rods (12) is inversely proportional to the load ratio borne by the secondary rods (12); the hanging point distance between the bottom of the secondary rod (12) and the connection of the two tertiary rods (13) is inversely proportional to the load ratio borne by the tertiary rods (13); the hanging point distance is the distance between the chain connecting point and the piston rod (24) in the horizontal direction.
8. The wing lift test method for simulating a ship-based aircraft full aircraft drop test according to claim 1, wherein the loading points are arranged in each loading area in a pairwise corresponding manner; each loading area is respectively positioned right above each wing rib on the wing and comprises the wing rib corresponding to the upper surface of the wing; the position relation between the loading point and the loading area is as follows: the two loading points are centrally located in the loading area and the distance between the two loading points is two-thirds of the length of the loading area.
9. The wing lift test method for simulating the ship-based aircraft full aircraft drop test according to claim 8, wherein the loading area is stuck with an encrypted canvas; the encryption canvas is adhered to the wing through glue.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202311200804.1A CN116923725B (en) | 2023-09-18 | 2023-09-18 | Wing lift force test method for simulating ship-based aircraft full aircraft drop test |
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| CN202311200804.1A CN116923725B (en) | 2023-09-18 | 2023-09-18 | Wing lift force test method for simulating ship-based aircraft full aircraft drop test |
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| CN116923725A true CN116923725A (en) | 2023-10-24 |
| CN116923725B CN116923725B (en) | 2023-12-12 |
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