CN115824550A - Civil aircraft drop-adaptive emergency breaking pin falling shock impact test bed and test method - Google Patents
Civil aircraft drop-adaptive emergency breaking pin falling shock impact test bed and test method Download PDFInfo
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- CN115824550A CN115824550A CN202211488968.4A CN202211488968A CN115824550A CN 115824550 A CN115824550 A CN 115824550A CN 202211488968 A CN202211488968 A CN 202211488968A CN 115824550 A CN115824550 A CN 115824550A
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Abstract
The invention discloses a falling impact test bed and a falling impact test method for a falling emergency breaking pin of a civil aircraft. The test bed comprises a main body type frame (1), wherein a lifting device (2) is installed at the top of the main body type frame, and a falling shock impact platform (6) is arranged at the bottom of the main body type frame; a drop shock lifting platform (3) is arranged below the lifting device, a breaking pin (8) is arranged at the lower part of the drop shock lifting platform through a shock clamp (7), and the breaking pin is positioned right above the drop shock impact platform; a counterweight is configured on the drop impact hanging platform; and a dynamic force sensor (18) is arranged on the drop impact platform, and a speed sensor (12) is arranged on the drop impact hanging platform. The invention can be used for verifying the breaking failure load, the failure mode and the breaking time of the emergency breaking pin and provides test reference for structural design, strength check and breaking failure mode research of the emergency breaking pin.
Description
Technical Field
The invention relates to a civil aircraft drop-adaptive test device, in particular to a civil aircraft drop-adaptive emergency break pin drop shock test bed and a test method.
Background
When the airplane is subjected to emergency working conditions such as forced landing, the airplane body structure, the seat system, the escape device and the like have the characteristics of protecting the personal safety of passengers and furthest ensuring that the passengers are not damaged by fatigues, namely the requirement on the design of the falling adaptability of the civil airplane is met. Emergent breaking away design belongs to one of the aircraft and suits to weigh down nature design content, usually includes the emergent breaking away design of undercarriage and engine and hangs and breaks away from the design, and the purpose prevents to take place emergent falling because of the aircraft and leads to piercing the oil tank with the system part that the oil tank is connected, causes the emergence of fuel leakage and conflagration, reduces the secondary damage to the passenger.
The emergency break design mainly comprises two types of integral break of structural components such as connecting rods and the like and break of pin shafts (break pins and safety pins) of connecting joints, wherein the break pins (also called safety pins) are designed and adopted by various large airplane companies due to simple structure and stress analysis and convenient design and manufacture. At present, the emergency disconnection design of civil aircraft is mastered abroad and is applied to the aircraft such as boeing, air passenger and the like, but the emergency disconnection technology, the test method and the test data are difficult to obtain under the constraint of technical secrecy; the emergency disconnection research aspect in China is in a starting exploration stage, and mainly focuses on the aspects of emergency disconnection dynamics simulation, structural design and simulation of emergency disconnection pins and quasi-static test research. However, under the influence of the complex crash condition of the airplane, the quasi-static strength of the emergency break pin (safety pin) cannot accurately reflect the dynamic load response of the emergency break pin (safety pin) in the crash process, so that the dynamic impact performance of the break pin (safety pin) needs to be verified by adopting a dynamic impact test, and test reference is provided for the structural design, the strength check and the fracture failure strength verification of the adaptive crash emergency break pin (safety pin).
Disclosure of Invention
The invention aims to solve the technical problem that the existing drop impact test bed cannot accurately test the impact failure load (break load) of an emergency break pin (safety pin), and provides a drop impact test bed and a test method for the emergency break pin of civil aircraft, which are used for verifying the break failure load and form of the emergency break pin (safety pin) and providing test reference for the structural design, strength check and the study of the break failure form of the emergency break pin (safety pin).
In order to solve the technical problems, the invention adopts the following technical scheme:
a civil aircraft drop-adaptive emergency breaking pin drop impact test stand comprises a main body type frame, wherein a lifting device is installed at the top of the main body type frame, and a drop impact platform is arranged at the bottom of the main body type frame;
a drop impact lifting platform is arranged below the lifting device through a lock mechanism, a breaking pin is arranged below the drop impact lifting platform through an impact fixture, and the breaking pin is positioned right above the drop impact platform; a counterweight block is arranged on the drop impact hanging platform;
and a dynamic force sensor is arranged on the falling shock impact platform, and a speed sensor is arranged on the falling shock impact hanging platform.
When the device is used, the tested breaking pin (safety pin) and the impact clamp thereof are installed on the drop impact hanging platform, and the equivalent weight and the falling speed borne by the breaking pin (safety pin) before falling are simulated by adjusting the mass of the balancing weight and the lifting height of the drop impact hanging platform and then statically releasing; meanwhile, a dynamic force sensor capable of collecting impact load data is installed on a drop impact platform to obtain accurate impact load change of a break pin (safety pin) under a high-speed impact condition and obtain a failure mode after the break pin (safety pin) fails and is damaged, and a speed sensor is installed on a drop impact lifting platform to accurately obtain the dropping and impacting speed of the break pin.
Preferably, guide rails are respectively arranged on two sides of the main body frame, pulleys are respectively installed at two ends of the falling shock impact lifting platform, and the falling shock impact lifting platform is slidably installed on the guide rails through the pulleys.
In order to prevent the falling shock impact device from falling to the falling shock impact platform and the main body frame to cause damage, the lower part of the main body frame is provided with a limiting block, and the limiting block is positioned at the shock stroke end point of the falling shock impact device.
Preferably, a damping device with a good damping and energy-absorbing effect is installed on the drop impact hanging platform, and the damping device starts to work after the breaking pin (safety pin) is completely damaged, so that the whole test bed is protected from impact damage.
Preferably, the damping device is an oil-gas damper or a hydraulic or pneumatic cylinder.
Preferably, the impact clamp is a single shear structure clamp or a double shear structure clamp. The double-shear structure clamp comprises an upper clamp and a lower clamp, the upper clamp is fixed on the drop impact hanging platform, and the upper clamp is hinged to the lower clamp through the breaking pin.
Preferably, a stay wire displacement sensor is installed between the impact fixture and the falling and vibrating impact platform, an acceleration sensor is installed on the impact fixture, a strain gauge is installed on the breaking pin, a high-speed camera device is installed above the falling and vibrating impact platform, and the strain gauge, the dynamic force sensor, the displacement sensor, the speed sensor and the acceleration sensor are respectively connected with a computer through a high-speed data acquisition card.
Based on the same invention concept, the invention also provides a test method of the civil aircraft drop-adaptive emergency break pin drop impact test bed, which comprises the following steps:
firstly, calculating according to the mass distribution of the airplane to obtain the weight born by the breaking pin, and installing a proper counterweight on the drop impact device according to the weight;
secondly, designing an impact fixture according to the actual installation size and the assembly relation of the break pin, wherein the impact fixture needs to ensure that the verified break pin conforms to the actual installation working condition, and installing the impact fixture with the break pin to a drop impact lifting platform;
then, setting the sinking speed v of the airplane according to the actual emergency falling working condition, and according to the relation between the speed and the displacement in the free falling body formula: h = v 2 The lifting height h of the drop impact lifting platform is obtained according to 2 g;
and finally, after the drop impact hanging platform is lifted to a lifting height h, the lock mechanism is unlocked to release the drop impact hanging platform to perform a drop impact test, meanwhile, the breaking load, the falling collision speed and the breaking time of the breaking pin are obtained, on the basis, whether the structural design of the breaking pin meets the requirements of the breaking pin limiting load, the limit load and the breaking load of the airplane design is judged, and the accuracy of the failure load calculation and the simulation model of the breaking pin is verified.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
Fig. 1 is a structural diagram of a breaking pin (safety pin) drop impact test bed of the invention.
Fig. 2 is a perspective view of the double shear structure jig.
Fig. 3 is a schematic structural diagram of a signal acquisition system.
Detailed Description
The invention is further described below with reference to specific preferred embodiments, without thereby limiting the scope of protection of the invention.
For convenience of description, the relative positional relationship of the components, such as: the descriptions of the upper, lower, left, right, etc. are described with reference to the layout directions of the drawings in the specification, and do not limit the structure of the present patent.
The embodiment of the civil aircraft dropping emergency breaking pin falling shock impact test stand comprises a mechanical part and a signal acquisition system.
The mechanical part is shown in figure 1 and comprises a main body type frame 1, a lifting device 2, a falling shock impact lifting platform 3, a damping device 4, a limiting device 5, a falling shock impact platform 6, an impact clamp 7, a breaking pin 8, a pulley 9, a counterweight 10 and a lock mechanism 11.
The main body frame 1 is made of reinforced concrete structure or structural steel (Q235, Q345, 45 steel and the like) materials, the specific size of the design is checked through strength, and guide rails (not shown) are respectively arranged on two sides of the main body frame 1 so as to ensure that the drop impact lifting platform 3 moves along the guide rails. In order to prevent the drop shock impact lifting platform 3 from falling to the drop shock impact platform 6, the lower part of the main body type frame 1 is provided with a limiting device 5, and the limiting device 5 is positioned at the shock stroke end point of the drop shock impact lifting platform 3 so as to ensure the safety of testing personnel and a test bed.
The lifting device 2 is fixedly arranged on the upper part of the main body type frame 1, and the lifting device 2 is of an existing structure and can be a motor-driven lifting device or a hydraulic-driven lifting device or a purely mechanical manual lifting device.
The drop impact platform 3 is mounted below the lifting device 2 and, when lifted, is connected to the lifting device 2 by a lock mechanism 11.
Pulleys 9 are respectively arranged at two ends of the lifting device 2 and the falling shock hoisting platform 3, and two ends of the lifting device 2 and the falling shock hoisting platform 3 are slidably arranged on the guide rail through the pulleys 9 and move upwards or downwards on the guide rail of the main body type frame 1 through the pulleys 9.
And a breaking pin 8 is arranged below the drop impact lifting platform 3 through an impact clamp 7, and the breaking pin 8 is positioned right above the drop impact platform 6. The impact clamp 7 is designed according to the actual assembly relationship of the emergency break pin 8, and generally has a single-shear structure or a double-shear structure, and the embodiment is described by taking a double-shear structure clamp as an example. As shown in fig. 2, in this embodiment, the impact clamp 7 includes two parts, namely an upper clamp 71 and a lower clamp 72, the upper clamp 71 is hinged to the lower clamp 72 through the break pin 8, and during actual assembly, after the upper clamp 71, the lower clamp 72 and the break pin 8 are assembled on the drop impact platform 6, the upper clamp 71 is fixed on the drop impact platform 3 through bolt connection. In addition, the impact clamp 7 is made of high-strength steel or tool steel materials, the hardness is not lower than 60HRC, and the contact part of the impact clamp 7 and the break pin 8 is sharp and has no defect.
The drop impact hanging platform 3 is provided with a damping device 4, and the damping device 4 can be an oil-gas buffer with damping and energy absorbing functions or a hydraulic cylinder or a pneumatic cylinder. The damping device 4 starts to work after the breaking pin 8 is completely damaged, and the falling shock impact lifting platform 3 is protected from being impacted on the falling shock impact platform 6 after the breaking pin (safety pin) 8 is broken and fails, so that the accuracy and reliability of the acquisition of various test data are guaranteed.
The drop impact lifting platform 3 is also provided with a counterweight 10 to simulate the equivalent mass borne by the breaking pin 8 before breaking off the drop.
The drop impact platform 6 is arranged on the bottom plate of the main body frame 1 and is used for bearing the impact of the whole drop impact lifting platform 3.
As shown in fig. 3, the signal acquisition system includes a strain gauge 17, a dynamic force sensor 18, a pull wire displacement sensor 19, a speed sensor 12, an acceleration sensor 13, a high-speed camera 16, a high-speed data acquisition card 14 and a computer 15.
In order to obtain an accurate break pin break load, the lower leg of the drop impact platform 6 is fitted with a dynamic force sensor 18. The break pin 8 is subjected to a break load equal to the sum of the loads measured by the dynamic force sensors 18. Since the time during which the impact breakage of the break pin 8 occurs is extremely short, the dynamic force sensor 18 is preferably a strain gauge type impact force sensor. Meanwhile, the strain gauge 17 is attached to the bearing surface of the break pin 8 to obtain the strain change of the break pin 8, and the stress change of the break pin 8 is calculated according to the generalized hooke's law. In addition, in order to accurately obtain the falling impact speed, a speed sensor 12 is installed on the pulley 9 of the falling impact platform 3, wherein the maximum falling impact speed is a moment when the falling impact tower 3 contacts the falling impact platform 6. A stay wire displacement sensor 19 is installed between the impact clamp 7 and the drop impact platform 6 to accurately obtain the lifting height of the break pin 8. The acceleration sensor 13 is arranged on the impact clamp 7 to obtain the acceleration change of the impact clamp 7, and the load born by the impact clamp 7 is calculated according to Newton's second law to judge whether the impact clamp 7 is overloaded or not. The high-speed camera device 16 is arranged above the falling and impacting platform 6, shoots the whole breaking process of the breaking pin 8 in real time, and calculates the breaking time through shooting frequency. The strain gauge 17, the dynamic force sensor 18, the stay wire displacement sensor 19, the speed sensor 12 and the acceleration sensor 13 are respectively connected with the computer 15 through the high-speed data acquisition card 14.
The test principle of the invention is as follows: installing a tested breaking pin (safety pin) 8 and an impact clamp 7 thereof on a drop impact lifting platform 3, and simulating the equivalent weight and the falling speed borne by the breaking pin (safety pin) 8 before falling by increasing the mass and the lifting height of a counterweight 10 on the drop impact lifting platform 3; meanwhile, the dynamic force sensor 18 is mounted on the drop impact platform 6 to obtain accurate break load change of the break pin (safety pin) 8 under high-speed impact conditions, and obtain a failure mode after the break pin (safety pin) 8 fails and is damaged.
The test method comprises the following steps: firstly, calculating and obtaining the equivalent mass born by a break-away pin (safety pin) 8 according to the load distribution of the airplane, setting a counterweight 10 according to the equivalent mass, and installing the counterweight 10 on a drop impact lifting platform 3; secondly, designing an impact clamp 7 according to the actual installation size and the assembly relation of a breaking pin (safety pin) 8, ensuring that the verified breaking pin (safety pin) 8 meets the actual installation working condition, and installing the impact clamp 7 with the breaking pin (safety pin) 8 on the drop impact lifting platform 3; then, setting the sinking speed v of the airplane according to the actual emergency falling working condition, and calculating the lifting height h = v of the falling impact lifting platform 3 according to the relation between the speed and the displacement in the free falling body formula and the sinking speed v of the airplane 2 And 2g, lifting the falling shock impact lifting platform 3 to a lifting height h through the lifting device 2, and unlocking the lock mechanism 11 to release the falling shock impact lifting platform 3 to perform a falling shock impact test. Finally, according to the test data of breaking load, falling and impacting speed and breaking time of breaking pin (safety pin) 8 obtained by the falling shock test, judging the breaking pin (C)Safety pin) structural design whether the structural design meets the requirements of the breaking pin limiting load, the ultimate load and the breaking load of the aircraft design (the requirements of the breaking pin limiting load, the ultimate load and the breaking load are well known by the technical personnel in the field), and verifying the accuracy of the breaking failure load calculation and the simulation model of the breaking pin (the breaking failure load calculation and the preparation of the simulation model are well known by the technical personnel in the field).
It should be noted that:
1. the ultimate load borne by the breaking pin can be obtained in a main landing gear drop test according to the requirements of an airplane main landing gear strength design guideline; or, the load is calculated according to the ground load of the main landing gear; or according to the simulation of the main landing gear emergency fracture dynamics.
Limit load F of the break-off pin, obtained by calculation u The calculation is as follows:
F u ＝S×F l (1)
in the formula: f u Is the limit load of the break pin; f l A restraining load (known) to break the pin; and S is a safety factor, and the safety factor is 1.5 specified in the pilot flight standard.
2. The judgment of whether the structural design of the break pin (safety pin) meets the break load requirement refers to whether the break load of the break pin (safety pin) 8 obtained by the drop impact test is between the minimum break load and the maximum break load. Specifically, the minimum breakaway load is determined according to the structural integrity of the main landing gear and the minimum breakaway load destructive failure requirement; determining the maximum breaking load according to the material tolerance, the geometric tolerance, the rigidity tolerance of the main landing gear and the rigidity tolerance of the wings; minimum break load F of break pin Dmin Obtained by calculation of formula (2):
F Dmin ＝ n 1 ×F u (2)；
maximum breaking load F of the breaking pin Dmax Obtained by calculation of formula (3):
F Dmax ＝ n 2 ×F Dmin (3)
in the above formulas (2) and (3): n is 1 、n 2 For breaking load coefficient (known), n 1 Take 1.1,n 2 Take 1.03.
3. According to the designed breaking load of the breaking pin and the installation size requirements of the breaking load, wings and the landing gear, the inner and outer diameter sizes and the inner structure of the emergency breaking pin are designed, and finally, an impact breaking test is carried out through the drop impact test bed of the civil aircraft drop emergency breaking pin, so that whether the breaking load of the breaking pin meets the design requirements is verified, the accuracy of a simulation model is verified, meanwhile, the breaking load coefficients of the formulas (2) and (3) can be further checked, and test reference is provided for the emergency breaking design of the main landing gear.
The above description is only a specific embodiment of the present invention, but the scope of the present invention is not limited thereto, and those skilled in the art can make many possible variations and modifications to the technical solution of the present invention or modify equivalent embodiments using the technical content disclosed above without departing from the technical solution of the present invention. Therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical spirit of the present invention should fall within the protection scope of the technical scheme of the present invention, unless the technical spirit of the present invention departs from the content of the technical scheme of the present invention.
Claims (9)
1. The utility model provides a civil aircraft is fit emergent disconnected round pin of falling and shakes impact test platform, includes main part type frame (1), its characterized in that:
the top of the main body type frame is provided with a lifting device (2), and the bottom of the main body type frame is provided with a falling and impacting platform (6);
a drop impact hanging platform (3) is arranged below the lifting device through a lock mechanism (11), a breaking pin (8) is arranged at the lower part of the drop impact hanging platform through an impact clamp (7), and the breaking pin is positioned right above the drop impact platform; a counterweight is configured on the drop impact hanging platform;
and a dynamic force sensor (18) is arranged on the drop impact platform, and a speed sensor (12) is arranged on the drop impact hanging platform.
2. The civil aircraft drop-adaptive emergency break pin drop impact test stand according to claim 1, wherein guide rails are respectively arranged on two sides of the main body frame, pulleys are respectively mounted on two ends of the drop impact hanging platform, and the drop impact hanging platform is slidably mounted on the guide rails through the pulleys.
3. The civil aircraft dropping emergency breaking pin falling shock impact test bed according to claim 1, wherein a limiting device is arranged at the lower part of the main body type frame, and the limiting device is positioned at the shock stroke end point of the falling shock impact lifting platform.
4. The civil aircraft drop adaptive emergency break pin drop impact test stand according to claim 1, wherein a damping device is mounted on the drop impact hanging stand.
5. The civil aircraft crash-adaptive emergency break pin drop impact test stand of claim 4, wherein the damping device is an oil-gas buffer or a hydraulic or pneumatic cylinder.
6. The civil aircraft drop adaptive emergency break pin drop impact test stand of claim 1, wherein the impact clamp is a single shear structure clamp or a double shear structure clamp.
7. The civil aircraft drop adaptive emergency break pin drop impact test stand according to claim 6, wherein the double shear structure clamp comprises an upper clamp and a lower clamp, the upper clamp is fixed on the drop impact hanging stand, and the upper clamp is hinged with the lower clamp through the break pin.
8. The civil aircraft drop-adaptive emergency break pin drop impact test stand according to claim 1, wherein a stay wire displacement sensor (19) is installed between the impact fixture and the drop impact platform, an acceleration sensor (13) is installed on the impact fixture, a strain gauge (17) is installed on the break pin, a high-speed camera device (16) is installed above the drop impact platform, and the strain gauge, the dynamic force sensor, the displacement sensor, the speed sensor and the acceleration sensor are respectively connected with a computer through high-speed data acquisition cards.
9. A method for testing a falling emergency break pin drop impact test bed of a civil aircraft as defined in any one of claims 1 to 8, which comprises:
firstly, calculating according to the mass distribution of the airplane to obtain the weight born by the breaking pin, and installing a proper counterweight on a drop impact hanging platform according to the weight;
secondly, designing an impact fixture according to the actual installation size and the assembly relation of the break pin, wherein the impact fixture needs to ensure that the verified break pin conforms to the actual installation working condition, and installing the impact fixture with the break pin to a drop impact lifting platform;
then, setting the sinking speed v of the airplane according to the actual emergency falling working condition, and according to the relation between the speed and the displacement in the free falling body formula: h = v 2 The lifting height h of the drop impact lifting platform is obtained according to 2 g;
and finally, after the drop impact tower crane is lifted to a lifting height h, unlocking a lock mechanism to release the drop impact platform to perform a drop impact test, and meanwhile, obtaining the breaking load, the falling collision speed and the breaking time of the breaking pin.
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| CN202211488968.4A CN115824550A (en) | 2022-11-25 | 2022-11-25 | Civil aircraft drop-adaptive emergency breaking pin falling shock impact test bed and test method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211488968.4A CN115824550A (en) | 2022-11-25 | 2022-11-25 | Civil aircraft drop-adaptive emergency breaking pin falling shock impact test bed and test method |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117007267A (en) * | 2023-10-07 | 2023-11-07 | 中国飞机强度研究所 | Three-way ground load measuring device and measuring method for ship-borne aircraft drop test |
| CN117030292A (en) * | 2023-10-08 | 2023-11-10 | 广东粤港澳大湾区黄埔材料研究院 | Shock-falling testing device for aerocar |
| CN117048846A (en) * | 2023-10-11 | 2023-11-14 | 中国飞机强度研究所 | Device and method for preventing aircraft from excessively sinking in full-aircraft drop test |
| CN117109861A (en) * | 2023-10-24 | 2023-11-24 | 中国飞机强度研究所 | System and method for measuring ground load and simulating heading speed of full-machine landing impact |
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2022
- 2022-11-25 CN CN202211488968.4A patent/CN115824550A/en active Pending
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117007267A (en) * | 2023-10-07 | 2023-11-07 | 中国飞机强度研究所 | Three-way ground load measuring device and measuring method for ship-borne aircraft drop test |
| CN117007267B (en) * | 2023-10-07 | 2024-01-09 | 中国飞机强度研究所 | Three-way ground load measuring device and measuring method for ship-borne aircraft drop test |
| CN117030292A (en) * | 2023-10-08 | 2023-11-10 | 广东粤港澳大湾区黄埔材料研究院 | Shock-falling testing device for aerocar |
| CN117048846A (en) * | 2023-10-11 | 2023-11-14 | 中国飞机强度研究所 | Device and method for preventing aircraft from excessively sinking in full-aircraft drop test |
| CN117048846B (en) * | 2023-10-11 | 2024-01-26 | 中国飞机强度研究所 | Device and method for preventing aircraft from excessively sinking in full-aircraft drop test |
| CN117109861A (en) * | 2023-10-24 | 2023-11-24 | 中国飞机强度研究所 | System and method for measuring ground load and simulating heading speed of full-machine landing impact |
| CN117109861B (en) * | 2023-10-24 | 2024-01-09 | 中国飞机强度研究所 | System and method for measuring ground load and simulating heading speed of full-machine landing impact |
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