CN112340060A - An aircraft instantaneous sinking speed measuring device and its measuring method - Google Patents
An aircraft instantaneous sinking speed measuring device and its measuring method Download PDFInfo
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- CN112340060A CN112340060A CN202011291694.0A CN202011291694A CN112340060A CN 112340060 A CN112340060 A CN 112340060A CN 202011291694 A CN202011291694 A CN 202011291694A CN 112340060 A CN112340060 A CN 112340060A
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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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Abstract
本发明提供一种飞机瞬时下沉速度测量装置及其测量方法，该装置包括方形盒、方形柱体、配重块、左摩擦制动块、右摩擦制动块；方形盒安装在飞机主起落架上；在方形盒内设有方形孔；在方形盒前侧面横向设有刻度标线；方形柱体竖向套设在方形孔内；在方形柱体前侧面设有刻度线；在方形盒上设有视窗；配重块安装在方形柱体下端；左摩擦制动块与右摩擦制动块分别贴合在方形柱体左右两侧面上；飞机着舰或着陆时，方形柱体和配重块构成的整体能沿方形盒向下单向运动直至相对方形盒静止。本发明可以直接测量飞机着陆瞬时的下沉速度，与目前使用的飞参记录系统相比，更直接、简单明了,也可广泛应用于汽车碰撞测试、民用设备跌落试验等场合的速度数据采集。
The invention provides a device for measuring the instantaneous sinking speed of an aircraft and a measuring method thereof. The device comprises a square box, a square cylinder, a counterweight, a left friction brake block and a right friction brake block; the square box is installed on the main lift of the aircraft. On the drop frame; a square hole is arranged in the square box; a scale mark is arranged horizontally on the front side of the square box; the square cylinder is vertically sleeved in the square hole; a scale line is arranged on the front side of the square cylinder; There is a viewing window on it; the counterweight is installed on the lower end of the square cylinder; the left friction brake block and the right friction brake block are attached to the left and right sides of the square cylinder respectively; when the aircraft lands or lands, the square cylinder and the The whole formed by the weight block can move down in one direction along the square box until it is stationary relative to the square box. The invention can directly measure the sinking speed of the aircraft at the instant of landing. Compared with the currently used flight parameter recording system, the invention is more direct, simple and clear, and can also be widely used for speed data collection in automobile crash tests, civil equipment drop tests and other occasions.
Description
Technical Field
The invention belongs to the technical field of airplane measurement and monitoring, and particularly relates to an airplane instantaneous sinking speed measuring device and a measuring method thereof.
Background
The sinking speed of the airplane is one of main parameters of the design of the undercarriage and the airframe structure of the airplane and is also an important index of the impact severity of carrier-based airplane landing, the undercarriage strength inspection task during the design shaping test flight of the airplane can be completed only by measuring the sinking speed of the airplane, and the collection of the sinking speed has important significance for the service life evaluation of the undercarriage and the airframe structure of the airplane. However, the current flight parameter system on the airplane does not directly acquire sinking speed data from the undercarriage, and the flight parameter data is huge in calculation workload and difficult to reflect the landing and the real sinking speed of the undercarriage during landing, so that the data acquisition difficulty is increased, and meanwhile, the accuracy is difficult to guarantee.
Disclosure of Invention
In view of the above problems, the present invention provides an aircraft instantaneous sinking speed measuring device and a measuring method thereof, which can directly measure the sinking speed of an aircraft and provide data support for strength inspection and life evaluation of a landing gear.
The purpose of the invention is realized by the following technical scheme:
an instantaneous sinking speed measuring device of an airplane comprises a square box, a square cylinder, a balancing weight, a left friction brake block and a right friction brake block; the square box is arranged on a main undercarriage of the airplane; a square hole which penetrates through the square box from top to bottom is vertically arranged in the square box; scale marks are transversely arranged on the front side surface of the square box; the square cylinder is vertically sleeved in the square hole, and the upper end and the lower end of the square cylinder extend out of the square hole; the front side surface of the square column body is provided with scale marks; a window which is communicated with the square hole and is positioned on the right side of the scale mark line and used for observing the scale on the scale mark line is arranged on the square box and is positioned right in front of the scale mark line; the balancing weight is positioned below the square box and is detachably arranged at the lower end of the square column body; the left friction brake block and the right friction brake block are arranged in the square box and are respectively attached to the left side surface and the right side surface of the square column body; in the flying process of the airplane, the square column is clamped by the left friction brake block and the right friction brake block to be in a static state, and the zero line of the scale mark and the scale mark line are on the same straight line; when the aircraft lands on a ship or lands, the whole body formed by the square column body and the balancing weight can move downwards in a single direction along the square box until the square box is static relative to the square box.
Further, to vary the pressure of the left friction brake pad against the square cylinder, the range of speed measurements is varied. The measuring device also comprises an adjusting knob and a spring; the right end of the adjusting knob is in threaded connection with the left side wall of the square box and transversely extends into the square box, and an annular plate is arranged at the part, located in the square box, of the right end of the adjusting knob; the spring is transversely installed in the square box, the right end of the spring is fixed on the right side face of the left friction brake block, and the left end of the spring is in contact with the annular plate at the right end of the adjusting knob. The adjusting knob is rotated to adjust the compression amount of the spring, and the pressure applied to the left side of the left friction brake block by the spring is further adjusted, so that the pressure of the left friction brake block on the square column is changed, and the purpose of changing the measurement range of the speed is achieved.
Furthermore, in order to facilitate screwing of the adjusting knob, anti-skid grains are arranged on the outer side of the left end of the adjusting knob.
Further, the balancing weight is cylindrical or square.
Furthermore, in order to ensure that the counterweight block has enough weight so that the counterweight block and the square column body can overcome the friction force between the left friction brake block and the left friction brake block to realize downward movement when the airplane lands on a warship or lands, and simultaneously ensure that the volume cannot be overlarge and other factors, the counterweight block adopts a lead block, and the lead block has various specifications with different qualities so as to change the measurement range of the speed by replacing the lead block.
Furthermore, the left friction brake block and the right friction brake block are made of friction materials, and the friction materials have good friction coefficient and wear resistance.
Furthermore, a limiting plate used for limiting the upper end of the square column body to slide into the square hole or slide out of the lower end of the square hole is arranged at the upper end of the square column body. The left friction brake block and the right friction brake block have service lives, and when the service lives reach the limit, the left friction brake block and the right friction brake block are aged or embrittled, the friction coefficient is sharply reduced, the limitation on the square cylinder is lost, the square cylinder and the balancing weight can easily slide out of the square hole and fall off, particularly fall off at high altitude, and personal or property damage is easily caused.
A measuring method of an aircraft instantaneous sinking speed measuring device comprises the following steps:
s1, in the normal flying process of the airplane, the square column is clamped by the left friction brake block and the right friction brake block to be in a static state, and at the moment, a zero line of the scale mark and the scale mark line are on the same straight line.
S2, when the aircraft lands on a ship or lands, under the action of inertia, the whole formed by the square column body and the balancing weight can move downwards in a single direction along the square box, and in the moving process, the aircraft stops after moving for a period of time under the action of the friction force of the left friction brake block and the right friction brake block.
S3, reading the scale which is in the same straight line with the scale mark line on the square box in the scale mark through the window, obtaining the relative displacement of the square cylinder with the balancing weight relative to the square box, further measuring the sinking speed of the airplane through the numerical value and a corresponding speed measuring formula, and manually resetting the whole body formed by the square cylinder and the balancing weight after reading.
The invention can directly measure the sinking speed of the airplane at the moment of landing, is more direct, simple and clear compared with the currently used flight parameter recording system, and can also be widely applied to speed data acquisition in occasions such as automobile collision test, civil equipment drop test and the like.
Drawings
The present invention will be described in further detail with reference to the accompanying drawings.
FIG. 1 is a schematic structural diagram of an instantaneous sinking speed measuring device of an aircraft according to the present invention;
FIG. 2 is a cross-sectional view of FIG. 1;
shown in the figure: 1-square box, 2-square column, 3-left friction brake block, 4-counterweight block, 5-adjusting knob, 6-spring, 7-right friction brake block, 8-square hole, 9-scale marking, 10-window, 11-scale line, 12-limiting plate.
Detailed Description
The following description of the embodiments of the present invention is provided for illustrative purposes, and other advantages and effects of the present invention will become apparent to those skilled in the art from the present disclosure.
It should be understood that the structures, proportions, and dimensions shown in the drawings and described herein are for illustrative purposes only and are not intended to limit the scope of the present invention, which is defined by the claims, but rather by the claims. In addition, the terms such as "upper", "lower", "left", "right" and "middle" used in the present specification are for convenience of description only, and are not intended to limit the scope of the present invention, and changes or modifications of the relative relationship thereof may be regarded as the scope of the present invention without substantial changes in the technical contents.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "connected" and "connected" are to be interpreted broadly, e.g., as being fixed or detachable or integrally connected; can be mechanically or electrically connected; may be directly connected or indirectly connected through an intermediate. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The first embodiment is as follows:
as shown in fig. 1 and 2, the device for measuring the instantaneous sinking speed of an airplane comprises a square box 1, a square column 2, a balancing weight 4, a left friction brake block 3 and a right friction brake block 7; the square box 1 is arranged on a main undercarriage of an airplane; a square hole 8 which runs through the square box 1 from top to bottom is vertically arranged in the square box 1; the front side surface of the square box 1 is transversely provided with scale marks 9; the square cylinder 2 is vertically sleeved in the square hole 8, and the upper end and the lower end of the square cylinder extend out of the square hole 8; the front side surface of the square column body 2 is provided with scale marks 11; a window 10 which is communicated with the square hole 8 and is positioned at the right side of the scale mark line 9 and used for observing the scale on the scale mark 11 is arranged at the position right in front of the scale mark 11 on the square box 1; the balancing weight 4 is positioned below the square box 1 and is detachably arranged at the lower end of the square column body 2; the left friction brake block 3 and the right friction brake block 7 are arranged in the square box 1 and are respectively attached to the left side surface and the right side surface of the square cylinder 2; in the flying process of the airplane, the square cylinder 2 is clamped by the left friction brake block 3 and the right friction brake block 7 and is in a static state, and the zero line of the scale mark 11 and the scale mark line 9 are on the same straight line; when the aircraft lands on a ship or lands, the whole body formed by the square column body 2 and the balancing weight 4 can move downwards in a single direction along the square box 1 until the square box 1 is static. The balancing weight 4 is cylindrical or square lead block, the purpose of adopting the lead block is to ensure that the balancing weight 4 has enough weight, so that when the balancing weight 4 and the square cylinder 2 are on a warship or land of an airplane, the balancing weight can overcome the friction force between the left friction brake block 3 and the left friction brake block 7 to realize downward movement, and meanwhile, various factors such as overlarge size and the like are ensured, and the lead block has various specifications with different qualities, so that the measurement range of the speed is changed by replacing the lead block. The left friction brake block 3 and the right friction brake block 7 are made of friction materials, and the friction materials have good friction coefficient and wear resistance.
Example two:
the difference between this embodiment and the first embodiment is:
as shown in fig. 1 and 2, the pressure of the left friction brake pad on the square column 2 is changed to change the speed measurement range. The measuring device also comprises an adjusting knob 5 and a spring 6; the right end of the adjusting knob 5 is in threaded connection with the left side wall of the square box 2 and transversely extends into the square box 1, and an annular plate is arranged at the position, located in the square box 2, of the right end of the adjusting knob 5; spring 6 transverse installation is in square box 1, and 6 right-hand members of spring are fixed on the 3 right flank of left friction brake block, and the left end contacts with the annular plate of 5 right-hand members of adjust knob. The adjusting knob 5 is rotated to adjust the compression amount of the spring 6, and further adjust the pressure applied by the spring 6 to the left side of the left friction brake block 3, so that the pressure of the left friction brake block 3 on the square column body 2 is changed, and the purpose of changing the measurement range of the speed is achieved. In order to facilitate the screwing of the adjusting knob 5, the outer side of the left end of the adjusting knob 5 is provided with anti-skid grains.
Example three:
the difference between this embodiment and the first or second embodiment is:
as shown in fig. 1 and 2, a limiting plate 12 for limiting the upper end of the square column 2 to slide into the square hole 8 or slide out of the lower end of the square hole 8 is arranged at the upper end of the square column 2. The left friction brake block 3 and the right friction brake block 7 have service lives, and when the service lives reach the limit, the left friction brake block and the right friction brake block age or become brittle, the friction coefficient is reduced sharply, the limit on the square column body 2 is lost, the square column body 2 and the balancing weight 4 easily slide out of the square hole 8 and fall, particularly fall at high altitude, and personal or property damage is easily caused.
The working principle is as follows:
in the normal flight process of the airplane, the square column body 2 is clamped by the left friction brake block 3 and the right friction brake block 7 to be in a static state, and at the moment, the zero line of the scale mark 11 and the scale mark line 9 are on the same straight line.
When an airplane lands on a warship or lands, under the action of inertia, the whole body formed by the square cylinder 2 and the balancing weight 4 can move downwards in a single direction along the square box 1, in the movement process, the square cylinder 2 and the balancing weight can stop after moving for a period of time under the action of the friction force of the left friction brake block 3 and the right friction brake block 7, the scale which is in the same straight line with the scale mark 9 on the square box 1 in the scale mark 11 (on the square cylinder 2) is read through the window 10, the relative displacement of the square cylinder 2 with the lead block relative to the square box 1 is obtained, and the sinking speed of the airplane is measured through the numerical value and a corresponding speed measuring formula.
After the numerical value is read, the adjusting knob 5 is rotated to enable the adjusting knob 5 to move to the left, the compression amount of the spring 6 is reduced, the spring 6 extends, the pressure exerted on the left friction brake block 3 by the right end of the spring 6 is reduced, the pressure of the left friction brake block 3 on the square cylinder 2 is reduced, the friction force applied to the square cylinder 2 is reduced, the square cylinder 2 with the lead block can be easily pushed to reset by manpower, and the zero line of the scale mark 11 and the scale mark 9 on the square box 1 are on the same straight line; after resetting, the adjusting knob 5 is rotated again, so that the adjusting knob 5 moves rightwards, the adjusting knob 5 moves rightwards to push the spring 6 to compress and deform rightwards (store energy), the pressure (elasticity) applied to the left friction brake block 3 by the right end of the spring 6 is increased, the pressure of the left friction brake block 3 on the square cylinder 2 is also increased, the frictional force received by the square cylinder 2 is also increased, the square cylinder 2 can be clamped under the combined action of the left friction brake block 3 and the right friction brake block 7, so that the square cylinder 2 is in a static state, the square cylinder 2 with the lead block is also ensured to keep in a static state (the gravity is equal to the frictional force) under the premise of ensuring the measurement range of the speed in the resetting process, and the zero line of the instant degree line 11 and the scale mark line 9 on the.
It is to be noted that the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
The scope of the present invention is not limited to the technical solutions disclosed in the embodiments, and any modifications, equivalent substitutions, improvements, etc. made to the above embodiments according to the technical spirit of the present invention fall within the scope of the present invention.
Claims (8)
1. An aircraft instantaneous sinking speed measuring device which is characterized in that: comprises a square box (1), a square column body (2), a balancing weight (4), a left friction brake block (3) and a right friction brake block (7); the square box (1) is arranged on a main landing gear of an airplane; a square hole (8) which is communicated with the square box (1) up and down is vertically arranged in the square box (1); the front side surface of the square box (1) is transversely provided with scale marks (9); the square cylinder (2) is vertically sleeved in the square hole (8) and the upper end and the lower end of the square cylinder extend out of the square hole (8); scale marks (11) are arranged on the front side surface of the square column body (2); a window (10) which is communicated with the square hole (8) and is positioned at the right side of the scale mark line (9) and used for observing the scales on the scale mark line (11) is arranged at the position, which is positioned right in front of the scale mark line (11), on the square box (1); the balancing weight (4) is positioned below the square box (1) and is detachably arranged at the lower end of the square column body (2); the left friction brake block (3) and the right friction brake block (7) are arranged in the square box (1) and are respectively attached to the left side surface and the right side surface of the square cylinder (2); in the flying process of the airplane, the square column body (2) is clamped by the left friction brake block (3) and the right friction brake block (7) to be in a static state, and the zero line of the scale mark (11) and the scale mark line (9) are on the same straight line; when the aircraft lands on a ship or lands, the whole body formed by the square column body (2) and the balancing weight (4) can move downwards in a single direction along the square box (1) until the square box (1) is static.
2. The aircraft instantaneous sinking speed measuring device according to claim 1, further comprising an adjusting knob (5), a spring (6); the right end of the adjusting knob (5) is in threaded connection with the left side wall of the square box (1) and transversely extends into the square box (1), and an annular plate is arranged at the position, located in the square box (1), of the right end of the adjusting knob (5); spring (6) transverse installation is in square box (1), and spring (6) right-hand member is fixed on left friction brake block (3) right flank, and the left end contacts with the annular plate of adjust knob (5) right-hand member.
3. An aircraft instantaneous sinking speed measuring device according to claim 2, characterized in that: the outer side of the left end of the adjusting knob (5) is provided with anti-skid grains.
4. An aircraft instantaneous sinking speed measuring device according to claim 1, wherein: the balancing weight (4) is cylindrical or square.
5. An aircraft instantaneous sinking speed measuring device according to claim 4, wherein: the balancing weight (4) is a lead block with various different masses.
6. An aircraft instantaneous sinking speed measuring device according to claim 1, wherein: the left friction brake block (3) and the right friction brake block (7) are made of friction materials.
7. An aircraft instantaneous sinking speed measuring device according to any one of claims 1 to 6, wherein: a limiting plate (12) used for limiting the upper end of the square column body (2) to slide into the square hole (8) or slide out of the lower end of the square hole (8) is arranged at the upper end of the square column body (2).
8. A method of measuring the instantaneous sinking speed of an aircraft according to any one of claims 1 to 6, comprising the steps of:
s1, in the normal flying process of an airplane, a square column body (2) is clamped by a left friction brake block (3) and a right friction brake block (7) to be in a static state, and at the moment, a zero line of a scale mark (11) and a scale mark line (9) are on the same straight line;
s2, when the aircraft lands on a ship or lands, under the action of inertia, the whole formed by the square column body (2) and the balancing weight (2) can move downwards in a single direction along the square box (1), and in the moving process, the aircraft stops after moving for a period of time under the action of the friction force of the left friction brake block (3) and the right friction brake block (7);
s3, reading the scale which is in the same straight line with the scale mark (9) on the square box (1) in the scale mark (11) through the window (10), namely obtaining the relative displacement of the square cylinder (2) with the balancing weight (4) relative to the square box (1), further measuring the sinking speed of the airplane through the numerical value and a corresponding speed measuring formula, and manually resetting the whole formed by the square cylinder (2) and the balancing weight (4) after reading.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011291694.0A CN112340060B (en) | 2020-11-18 | 2020-11-18 | A device and method for measuring aircraft instantaneous sinking speed |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011291694.0A CN112340060B (en) | 2020-11-18 | 2020-11-18 | A device and method for measuring aircraft instantaneous sinking speed |
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| CN112340060A true CN112340060A (en) | 2021-02-09 |
| CN112340060B CN112340060B (en) | 2025-01-28 |
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Citations (5)
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|---|---|---|---|---|
| US7274310B1 (en) * | 2005-03-29 | 2007-09-25 | Nance C Kirk | Aircraft landing gear kinetic energy monitor |
| CN104111351A (en) * | 2014-08-06 | 2014-10-22 | 江南大学 | Mechanical type accelerometer |
| US20180372535A1 (en) * | 2017-06-26 | 2018-12-27 | Airbus Helicopters | Aircraft undercarriage having an onboard load-measuring device, and an aircraft |
| CN110949677A (en) * | 2019-12-06 | 2020-04-03 | 江西洪都航空工业集团有限责任公司 | Indicating device for airplane heavy landing |
| CN213974523U (en) * | 2020-11-18 | 2021-08-17 | 贵州贵飞飞机设计研究院有限公司 | Airplane instantaneous sinking speed measuring device |
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2020
- 2020-11-18 CN CN202011291694.0A patent/CN112340060B/en active Active
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7274310B1 (en) * | 2005-03-29 | 2007-09-25 | Nance C Kirk | Aircraft landing gear kinetic energy monitor |
| CN104111351A (en) * | 2014-08-06 | 2014-10-22 | 江南大学 | Mechanical type accelerometer |
| US20180372535A1 (en) * | 2017-06-26 | 2018-12-27 | Airbus Helicopters | Aircraft undercarriage having an onboard load-measuring device, and an aircraft |
| CN110949677A (en) * | 2019-12-06 | 2020-04-03 | 江西洪都航空工业集团有限责任公司 | Indicating device for airplane heavy landing |
| CN213974523U (en) * | 2020-11-18 | 2021-08-17 | 贵州贵飞飞机设计研究院有限公司 | Airplane instantaneous sinking speed measuring device |
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| Title |
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| 蒋启登;: "陆基飞机大下沉速度对称着陆试验方法", 北京航空航天大学学报, vol. 39, no. 11, 30 November 2013 (2013-11-30), pages 1421 - 1425 * |
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