A device and method for measuring aircraft instantaneous sinking speed

Abstract

The present invention provides an aircraft instantaneous sinking speed measuring device and a measuring method thereof, the device comprises a square box, a square column, a counterweight, a left friction brake block, and a right friction brake block; the square box is installed on the main landing gear of the aircraft; a square hole is provided in the square box; a scale mark is provided horizontally on the front side of the square box; the square column is vertically sleeved in the square hole; a scale mark is provided on the front side of the square column; a window is provided on the square box; the counterweight is installed at the lower end of the square column; the left friction brake block and the right friction brake block are respectively attached to the left and right side surfaces of the square column; when the aircraft is landing, the whole formed by the square column and the counterweight can move downward in one direction along the square box until it is stationary relative to the square box. The present invention can directly measure the instantaneous sinking speed of the aircraft when it lands, which is more direct, simple and clear compared with the currently used flight parameter recording system, and can also be widely used in speed data collection in occasions such as automobile collision test and civil equipment drop test.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft measurement and monitoring, and in particular relates to an aircraft instantaneous sinking speed measuring device and a measuring method thereof. Background Art

[0002] The sinking speed of an aircraft is one of the main parameters for the design of the aircraft landing gear and fuselage structure, and is also an important indicator of the severity of the impact of carrier-based aircraft landing. Only by measuring the sinking speed of the aircraft can the strength inspection task of the landing gear during the aircraft design finalization test flight be completed. The collection of sinking speed is also of great significance to the life assessment of the aircraft landing gear and fuselage structure. However, the current flight parameter system on the aircraft does not directly collect sinking speed data from the landing gear. The workload of converting the flight parameter data is huge and it is difficult to reflect the actual sinking speed of the landing gear during landing, which increases the difficulty of data acquisition and the accuracy is difficult to guarantee. Summary of the invention

[0003] In view of the above problems, the purpose of the present invention is to provide an aircraft instantaneous sinking speed measuring device and a measuring method thereof, which can directly measure the aircraft sinking speed and provide data support for landing gear strength inspection and life assessment.

[0004] The objective of the present invention is achieved through the following technical solutions:

[0005] A device for measuring the instantaneous sinking speed of an aircraft comprises a square box, a square column, a counterweight, a left friction brake block, and a right friction brake block; the square box is installed on the main landing gear of the aircraft; a square hole penetrating the upper and lower parts of the square box is vertically arranged in the square box; a scale mark is horizontally arranged on the front side of the square box; the square column is vertically sleeved in the square hole and its upper and lower ends extend out of the square hole; a scale mark is arranged on the front side of the square column; a position on the square box directly in front of the scale mark is provided which is penetrating the square hole and located on the right side of the scale mark for measuring the instantaneous sinking speed of an aircraft Observe the window with scale marks on the scale lines; the counterweight block is located below the square box and is detachably mounted on the lower end of the square column; the left friction brake block and the right friction brake block are mounted in the square box and are respectively attached to the left and right side surfaces of the square column; during the flight of the aircraft, the square column is clamped by the left friction brake block and the right friction brake block and is in a stationary state, and the zero line of the scale line is in the same straight line as the scale mark line; when the aircraft is landing, the whole formed by the square column and the counterweight block can move downward in one direction along the square box until it is stationary relative to the square box.

[0006] Furthermore, in order to change the pressure of the left friction brake block on the square cylinder, the speed measurement range can be changed. The measuring device also includes an adjusting knob and a spring; the right end of the adjusting knob is threadedly connected to the left side wall of the square box and extends horizontally into the square box, and an annular plate is provided at the position of the right end of the adjusting knob in the square box; the spring is installed horizontally in the square box, the right end of the spring is fixed on the right side surface of the left friction brake block, and the left end is in contact with the annular plate at the right end of the adjusting knob. Rotate the adjusting knob to adjust the spring compression, and further adjust the pressure applied by the spring on the left side of the left friction brake block, thereby changing the pressure of the left friction brake block on the square cylinder and achieving the purpose of changing the speed measurement range.

[0007] Furthermore, in order to facilitate turning the adjusting knob, an anti-slip pattern is provided on the outer side of the left end of the adjusting knob.

[0008] Furthermore, the counterweight block is cylindrical or square.

[0009] Furthermore, in order to ensure that the counterweight block has sufficient weight so that the counterweight block and the square column can overcome the friction between the left friction brake block and the left friction brake block to achieve downward movement when the aircraft is landing, while also ensuring that the volume is not too large and other factors, the counterweight block is made of lead block, and the lead block has a variety of different mass specifications, so that the speed measurement range can be changed by replacing the lead block.

[0010] Furthermore, the left friction brake pad and the right friction brake pad are made of friction material, and the friction material has good friction coefficient and wear resistance.

[0011] Furthermore, a limit plate is provided at the upper end of the square column to limit the upper end of the square column from sliding into the square hole or sliding out of the lower end of the square hole. The left friction brake block and the right friction brake block have a service life. When the service life reaches the limit, they will age or become brittle, and the friction coefficient will drop sharply. Without the restriction on the square column, the square column and the counterweight block will easily slide out of the square hole and fall, especially from a high altitude, which can easily cause personal injury or property damage.

[0012] A measuring method of an aircraft instantaneous sinking speed measuring device comprises the following steps:

[0013] S1. During normal flight of the aircraft, the square cylinder is clamped by the left friction brake pad and the right friction brake pad and is in a stationary state. At this time, the zero line of the scale line and the scale mark line are on the same straight line.

[0014] S2. When the aircraft touches down or lands, under the action of inertia, the whole composed of the square column and the counterweight block can move unidirectionally downward along the square box. During the movement, it will stop after moving for a period of time due to the friction force of the left friction brake block and the right friction brake block.

[0015] S3. The scale mark on the scale line that is in the same straight line as the scale mark on the square box is read through the window, and the relative displacement of the square column with the counterweight block relative to the square box is obtained. Then, the sinking speed of the aircraft is measured by this value and the corresponding speed measurement formula. After reading, the whole composed of the square column and the counterweight block is manually reset.

[0016] The present invention can directly measure the sinking speed of an aircraft at the moment of landing. Compared with the currently used flight parameter recording system, it is more direct, simple and clear. It can also be widely used in speed data collection in occasions such as automobile collision tests and civil equipment drop tests. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The present invention is further described in detail below with reference to the accompanying drawings.

[0018] Figure 1 It is a structural schematic diagram of a device for measuring instantaneous sinking speed of an aircraft according to the present invention;

[0019] Figure 2 for Figure 1 A cross-sectional view of

[0020] As shown in the figure: 1-square box, 2-square cylinder, 3-left friction brake block, 4-counterweight block, 5-adjusting knob, 6-spring, 7-right friction brake block, 8-square hole, 9-scale marking line, 10-window, 11-scale line, 12-limit plate. DETAILED DESCRIPTION

[0021] The following is a description of the implementation of the present invention by means of specific embodiments. Those skilled in the art can easily understand other advantages and effects of the present invention from the contents disclosed in this specification.

[0022] It should be noted that the structures, proportions, sizes, etc. drawn in the drawings of this specification are only used to match the contents disclosed in the specification for people familiar with this technology to understand and read, and are not used to limit the limiting conditions for the implementation of the present invention, so they have no substantial technical significance. Any modification of the structure, change of the proportional relationship or adjustment of the size should still fall within the scope of the technical content disclosed by the present invention without affecting the effects and purposes that can be achieved by the present invention. At the same time, the terms such as "upper", "lower", "left", "right", "middle" and so on quoted in this specification are only for the convenience of description, and are not used to limit the scope of the implementation of the present invention. The change or adjustment of their relative relationship should also be regarded as the scope of the implementation of the present invention without substantially changing the technical content.

[0023] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "connected" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0024] Embodiment 1:

[0025] like Figure 1 , Figure 2 As shown, an aircraft instantaneous sinking speed measuring device of the present invention comprises a square box 1, a square column 2, a counterweight 4, a left friction brake block 3, and a right friction brake block 7; the square box 1 is installed on the main landing gear of the aircraft; a square hole 8 penetrating the upper and lower parts of the square box 1 is vertically arranged in the square box 1; scale markings 9 are horizontally arranged on the front side of the square box 1; the square column 2 is vertically sleeved in the square hole 8 and its upper and lower ends extend out of the square hole 8; scale markings 11 are arranged on the front side of the square column 2; a portion of the square box 1 that is located directly in front of the scale markings 11 and that is penetrating the square hole 8 and located on the scale markings 9 is provided. The right side is provided with a viewing window 10 for observing the scale on the scale line 11; the counterweight 4 is located below the square box 1 and is detachably mounted on the lower end of the square column 2; the left friction brake block 3 and the right friction brake block 7 are mounted in the square box 1 and are respectively attached to the left and right side surfaces of the square column 2; during the flight of the aircraft, the square column 2 is clamped by the left friction brake block 3 and the right friction brake block 7 and is in a stationary state, and the zero line of the scale line 11 and the scale mark line 9 are in the same straight line; when the aircraft is landing, the whole formed by the square column 2 and the counterweight 4 can move downward in one direction along the square box 1 until it is stationary relative to the square box 1. The counterweight block 4 is a cylindrical or square lead block. The purpose of using the lead block is to ensure that the counterweight block 4 has enough weight so that the counterweight block 4 and the square column 2 can overcome the friction between the left friction brake block 3 and the left friction brake block 7 to move downward when the aircraft is landing. At the same time, it is also necessary to ensure that the volume is not too large and other factors. The lead block has a variety of different quality specifications, so that the speed measurement range can be changed by replacing the lead block. The left friction brake block 3 and the right friction brake block 7 are made of friction material, and the friction material has a good friction coefficient and wear resistance.

[0026] Embodiment 2:

[0027] The difference between this embodiment and the first embodiment is that:

[0028] like Figure 1 , Figure 2As shown, the pressure of the left friction brake block on the square cylinder 2 is changed to change the measurement range of the speed. The measuring device also includes an adjusting knob 5 and a spring 6; the right end of the adjusting knob 5 is threadedly connected to the left side wall of the square box 2 and extends horizontally into the square box 1, and an annular plate is provided on the part of the right end of the adjusting knob 5 located in the square box 2; the spring 6 is horizontally installed in the square box 1, the right end of the spring 6 is fixed on the right side surface of the left friction brake block 3, and the left end is in contact with the annular plate at the right end of the adjusting knob 5. Rotate the adjusting knob 5 to adjust the compression of the spring 6, and further adjust the pressure applied by the spring 6 on the left side of the left friction brake block 3, thereby changing the pressure of the left friction brake block 3 on the square cylinder 2, and achieving the purpose of changing the measurement range of the speed. In order to facilitate the turning of the adjusting knob 5, an anti-slip pattern is provided on the outer side of the left end of the adjusting knob 5.

[0029] Embodiment three:

[0030] The difference between this embodiment and the first or second embodiment is that:

[0031] like Figure 1 , Figure 2 As shown, a limit plate 12 is provided at the upper end of the square column 2 to limit the upper end of the square column 2 from sliding into the square hole 8 or sliding out of the lower end of the square hole 8. The left friction brake block 3 and the right friction brake block 7 have a service life. When the service life reaches the limit, they will age or become brittle, and the friction coefficient will drop sharply. Without the restriction on the square column 2, the square column 2 and the counterweight block 4 will easily slide out of the square hole 8 and fall, especially falling from a high altitude, which is easy to cause personal injury or property damage.

[0032] Working principle:

[0033] During the normal flight of the aircraft, the square cylinder 2 is clamped by the left friction brake block 3 and the right friction brake block 7 and is in a stationary state. At this time, the zero line of the scale line 11 and the scale mark line 9 are on the same straight line.

[0034] When the aircraft touches down or lands, under the action of inertia, the whole composed of the square column 2 and the counterweight 4 can move unidirectionally downward along the square box 1. During the movement, it will stop after a period of movement due to the friction force of the left friction brake block 3 and the right friction brake block 7. The scale 11 (on the square column 2) that is in the same straight line with the scale mark 9 on the square box 1 is read through the window 10, that is, the relative displacement of the square column 2 with the lead block relative to the square box 1 is obtained, and then the sinking speed of the aircraft is measured by this value and the corresponding speed measurement formula.

[0035] After reading the value, rotate the adjusting knob 5 to move the adjusting knob 5 to the left, the compression of the spring 6 decreases, the spring 6 stretches, and the pressure applied by the right end of the spring 6 on the left friction brake block 3 decreases, so that the pressure of the left friction brake block 3 on the square cylinder 2 also decreases, and the friction force on the square cylinder 2 also decreases, and the square cylinder 2 with the lead block can be easily pushed to reset manually, so that the zero line of the scale line 11 and the scale mark line 9 on the square box 1 are in the same straight line; after resetting, rotate the adjusting knob 5 again to move the adjusting knob 5 to the right, and the right movement of the adjusting knob 5 pushes the spring 6 to compress to the right Deformation (energy storage), the pressure (elastic force) applied by the right end of spring 6 on the left friction brake block 3 increases, so that the pressure of the left friction brake block 3 on the square column 2 also increases, and the friction force on the square column 2 also increases. Under the joint action of the left friction brake block 3 and the right friction brake block 7, the square column 2 can be clamped to keep it in a static state. During the resetting process, while ensuring the measurement range of the speed, it is also necessary to ensure that the square column 2 with the lead block remains static (gravity equals friction), that is, the zero line of the scale line 11 is in the same straight line with the scale mark 9 on the square box 1.

[0036] It should be noted that the terms "comprises", "includes" or any other variations are intended to cover non-exclusive inclusion, so that a process, method, article or apparatus that includes a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or apparatus.

[0037] The protection scope of the present invention is not limited to the technical solutions disclosed in the specific implementation methods. Any modifications, equivalent replacements, improvements, etc. made to the above embodiments based on the technical essence of the present invention shall fall within the protection scope of the present invention.

Claims

1. An aircraft instantaneous sinking speed measuring device, characterized in that: It comprises a square box (1), a square column (2), a counterweight (4), a left friction brake block (3), a right friction brake block (7), an adjustment knob (5) and a spring (6); The square box (1) is installed on the main landing gear of an aircraft; a square hole (8) is vertically provided inside the square box (1) and passes through the upper and lower parts of the square box (1); and a scale mark (9) is horizontally provided on the front side of the square box (1); The square column (2) is vertically sleeved in the square hole (8) and its upper and lower ends extend out of the square hole (8); a scale line (11) is provided on the front side of the square column (2); a window (10) is provided on the square box (1) at a position directly in front of the scale line (11), which is connected to the square hole (8) and is located on the right side of the scale mark line (9) for observing the scale on the scale line (11); The counterweight (4) is located below the square box (1) and is detachably mounted on the lower end of the square column (2); the counterweight (4) is a lead block of various different masses; The left friction brake block (3) and the right friction brake block (7) are installed in the square box (1) and are respectively attached to the left and right side surfaces of the square column (2); during the flight of the aircraft, the square column (2) is clamped by the left friction brake block (3) and the right friction brake block (7) and is in a stationary state, and the zero line of the scale line (11) and the scale mark line (9) are on the same straight line; when the aircraft is landing, the whole formed by the square column (2) and the counterweight block (4) can move downward in one direction along the square box (1) until it is stationary relative to the square box (1); The right end of the adjusting knob (5) is threadedly connected to the left side wall of the square box (1) and extends transversely into the square box (1); an annular plate is provided at the portion of the right end of the adjusting knob (5) located inside the square box (1); The spring (6) is installed transversely in the square box (1), the right end of the spring (6) is fixed to the right side surface of the left friction brake block (3), and the left end is in contact with the annular plate at the right end of the adjusting knob (5).

2. The device for measuring the instantaneous sinking speed of an aircraft according to claim 1, characterized in that: An anti-slip pattern is provided on the outer side of the left end of the adjusting knob (5).

3. The device for measuring the instantaneous sinking speed of an aircraft according to claim 1, characterized in that: The counterweight block (4) is cylindrical or square.

4. The device for measuring the instantaneous sinking speed of an aircraft according to claim 1, characterized in that: The left friction brake block (3) and the right friction brake block (7) are made of friction material.

5. The device for measuring the instantaneous sinking speed of an aircraft according to any one of claims 1 to 4, characterized in that: A limiting plate (12) is provided at the upper end of the square column (2) for limiting the upper end of the square column (2) from sliding into the square hole (8) or sliding out of the lower end of the square hole (8).

6. The measuring method of the aircraft instantaneous sinking speed measuring device according to any one of claims 1 to 4, characterized in that: The following steps are involved: S1. During normal flight of the aircraft, the square cylinder (2) is clamped by the left friction brake pad (3) and the right friction brake pad (7) and is in a stationary state. At this time, the zero line of the scale line (11) and the scale mark (9) are on the same straight line; S2. When the aircraft touches down or lands, under the action of inertia, the whole body consisting of the square column (2) and the counterweight (4) can move unidirectionally downward along the square box (1). During the movement, it is affected by the friction force of the left friction brake block (3) and the right friction brake block (7), and stops after moving for a period of time; S3. The scale mark in the scale line (11) which is in the same straight line as the scale mark (9) on the square box (1) is read through the window (10), and the relative displacement of the square column (2) with the counterweight (4) relative to the square box (1) is obtained. Then, the sinking speed of the aircraft is measured by the value and the corresponding speed measurement formula. After the reading is completed, the whole composed of the square column (2) and the counterweight (4) is manually reset.

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