CN109703793B - Design method of buffering energy-absorbing recovery device and buffering energy-absorbing recovery device - Google Patents
Design method of buffering energy-absorbing recovery device and buffering energy-absorbing recovery device Download PDFInfo
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- CN109703793B CN109703793B CN201910004334.9A CN201910004334A CN109703793B CN 109703793 B CN109703793 B CN 109703793B CN 201910004334 A CN201910004334 A CN 201910004334A CN 109703793 B CN109703793 B CN 109703793B
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Abstract
The invention provides a design method of a buffering energy-absorbing recovery device and the buffering energy-absorbing recovery device, wherein the method comprises the following steps: step one, according to the application environment and the installation position of the buffering energy-absorbing recovery device, taking the energy-absorbing performance and the reliable connection performance of the buffering energy-absorbing recovery device as design key points; selecting a buffering energy-absorbing mechanism aiming at a design key point of the energy-absorbing performance of the buffering energy-absorbing recovery device; selecting a fixed connecting piece of the buffering and energy-absorbing mechanism aiming at a design key point of reliable connection performance of the buffering and energy-absorbing recovery device; and step three, respectively carrying out numerical simulation analysis and ground verification tests on the buffering energy-absorbing recovery device selected in the step two so as to verify the feasibility of the design method of the buffering energy-absorbing recovery device. By applying the technical scheme provided by the invention, the technical problem that the explosive bolt separation residual part with high hazard cannot be safely and reliably recovered in the prior art is solved.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a method for designing a buffering energy-absorbing recovery device and the buffering energy-absorbing recovery device.
Background
Thin-walled structures can utilize plastic deformation of materials to dissipate impact kinetic energy, and axial deformation of the structure stores much higher energy than transverse. The thin-wall structure has the advantages of high strength-to-weight ratio, low cost, high energy absorption efficiency, stable and controllable deformation mode and the like, and is widely applied to systems utilizing collision kinetic energy for dissipation, such as spaceflight, vehicles, ships and the like.
The explosive bolt is widely applied to aircrafts such as rockets, satellites and missiles due to simple structure and reliable separation. The explosive bolt belongs to a strong connection and strong unlocking type unlocking mechanism, and when the connecting force is larger, the required unlocking force is also larger. After the explosive bolts are separated and unlocked, the residual bolt bodies and the screw rods fly out at a high speed, and large impulse is generated to the cabin body. In the prior art, no proper buffering energy absorption device is available for safely and reliably recovering the explosive bolt separation residual part with high hazard, so that the safety performance of the aircraft is greatly reduced.
Disclosure of Invention
The invention provides a design method of a buffering energy-absorbing recovery device and the buffering energy-absorbing recovery device, which can solve the technical problem that the separation residual part of an explosive bolt with high harmfulness cannot be safely and reliably recovered in the prior art.
According to one aspect of the invention, a design method of a buffering energy-absorbing recovery device for interstage separation of an aircraft is provided, and the design method of the buffering energy-absorbing recovery device comprises the following steps: step one, according to the application environment and the installation position of the buffering energy-absorbing recovery device, taking the energy-absorbing performance and the reliable connection performance of the buffering energy-absorbing recovery device as design key points; selecting a buffering energy-absorbing mechanism aiming at a design key point of the energy-absorbing performance of the buffering energy-absorbing recovery device; selecting a fixed connecting piece of the buffering and energy-absorbing mechanism aiming at a design key point of reliable connection performance of the buffering and energy-absorbing recovery device; and step three, respectively carrying out numerical simulation analysis and ground verification tests on the buffering energy-absorbing recovery device selected in the step two so as to verify the feasibility of the design method of the buffering energy-absorbing recovery device.
Further, aiming at the design key point of the energy absorption performance of the buffering energy-absorbing recovery device, a high-temperature alloy honeycomb buffer piece is selected as a buffering energy-absorbing mechanism; aiming at the design key point of reliable connection performance of the buffering energy-absorbing recovery device, a screw and a pin are selected as fixed connecting pieces of the buffering energy-absorbing mechanism.
Further, when the high-temperature alloy honeycomb buffering member is selected by using a theoretical analysis method, according to the Daronbel principle, inertia force is added into the buffering and energy-absorbing recovery device, so that an unbalanced power system is changed into a balanced inertia system, the deformation energy of the high-temperature alloy honeycomb buffering member is calculated by using a static load calculation method, and the section load of the high-temperature alloy honeycomb buffering member is determined according to the deformation energy of the high-temperature alloy honeycomb buffering member.
Further, the section load f of the high-temperature alloy honeycomb buffer piece is required to meet the requirement
Wherein，m1Quality of explosive bolt remnants, V0The speed of separating the residual parts of the explosive bolt is shown in the specification, A is the cross-sectional area of the high-temperature alloy honeycomb buffer part, alpha is a conversion coefficient, and L isdIs the inelastic compression of the superalloy honeycomb buffer, LeThe elastic compression of the high-temperature alloy honeycomb buffer piece.
Further, after the fixed connecting piece of the buffering and energy absorbing mechanism is analyzed by using a theoretical analysis method, a first screw and a second screw are selected to bear the bending moment when the structure of the high-temperature alloy honeycomb buffering piece deforms, a pin is selected to bear the shearing moment when the structure of the high-temperature alloy honeycomb buffering piece deforms, and the maximum tensile force F of the first screw and the second screwPAll should satisfy
Wherein L is2Is the distance between the central axis of the explosive bolt and the mounting table of the recovery box, L1Is the distance between the first screw and the second screw, F0Is the average crushing force of the superalloy honeycomb cushion.
Further, in the third step, when the numerical simulation analysis is carried out on the selected buffering energy-absorbing recovery device, modeling and meshing are carried out on the buffering energy-absorbing recovery device, and the contact relation between the high-temperature alloy honeycomb buffer and the explosive bolt is established by setting the material property and the boundary condition of the buffering energy-absorbing recovery device; iteratively solving the buffering energy-absorbing recovery device according to the contact relation between the high-temperature alloy honeycomb buffer piece and the explosion bolt to obtain the crushing condition of the high-temperature alloy honeycomb buffer piece and the load curve of the bolt; and verifying the rationality of the selected buffering, energy-absorbing and recycling device according to the obtained crushing condition of the high-temperature alloy honeycomb buffer and the load curve of the screw.
Further, in the third step, when the ground verification test is carried out on the selected buffering energy-absorbing recovery device, the explosion bolt is installed on the test bed through the nut, one end of the explosion bolt is not restrained, the buffering energy-absorbing recovery device is installed at one end of the nut, and the explosion bolt is detonated to verify the buffering performance of the buffering energy-absorbing recovery device.
According to still another aspect of the present invention, there is provided a buffering energy-absorbing recovery apparatus, which includes a recovery box 10, a fixed connector 20 and a high-temperature alloy honeycomb buffer 30, the buffering energy-absorbing recovery apparatus is designed using the above-mentioned buffering energy-absorbing recovery apparatus design method, the high-temperature alloy honeycomb buffer 30 is disposed between the recovery box 10 and an explosive bolt, and the recovery box 10 is connected to a cabin body through the fixed connector 20.
Further, the superalloy honeycomb cushion 30 includes a honeycomb core, a first panel and a second panel, the honeycomb core is disposed between the first panel and the second panel, and the first panel and the second panel are designed to follow the shape of the honeycomb core; the fixed connection 20 includes a first screw 21, a second screw 22, and a pin 23.
Further, the honeycomb core has a plurality of hexagonal receiving holes for receiving explosive bolt remnants during aircraft interstage separation.
The method takes a small-space large-impulse buffering energy-absorbing recovery device as a research object, firstly analyzes key design points of the device according to background input conditions, provides an analysis method for solving two key design points of buffering energy-absorbing performance and reliable connection performance, and determines the technical state of the buffering energy-absorbing recovery device according to the analysis method; then, carrying out numerical simulation analysis on the selected buffering and energy-absorbing recovery device to check and evaluate impact, and considering the evaluation result that the buffering and energy-absorbing recovery device designed by the guidance of the patent can effectively recover explosive bolt residual parts; finally, the buffering energy-absorbing recovery device is verified by ground explosion bolt separation and recovery tests, and test results show that the design method of the device is correct and effective. Compared with the prior art, the design method of the buffering energy-absorbing recovery device provided by the invention is safer and more feasible, can safely and reliably recover the explosive bolt separation residual part with high hazard, and is suitable for buffering, absorbing energy and recovering the large-impulse residual part after the explosive bolt is separated at high speed in the aircraft with narrow space.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
FIG. 1 is a schematic structural diagram of a buffering energy-absorbing recovery device according to an embodiment of the invention;
FIG. 2 illustrates a graphical force versus displacement graph for a superalloy honeycomb buffer provided in accordance with an embodiment of the present invention;
FIG. 3 illustrates a graphical plot of force versus displacement for a non-linear spring provided in accordance with a specific embodiment of the present invention;
FIG. 4 is a schematic top view of an installed energy absorption and recovery device according to an embodiment of the present invention;
FIG. 5 is a side view of a crash recovery apparatus installation in accordance with an embodiment of the present invention.
Wherein the figures include the following reference numerals:
10. a recovery box; 20. fixing the connecting piece; 21. a first screw; 22. a second screw; 23. a pin; 30. a high temperature alloy honeycomb buffer; 100. exploding the bolt; 200. and a nut.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments according to the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.
The relative arrangement of the components and steps, the numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.
As shown in fig. 1, according to an embodiment of the present invention, there is provided a method for designing a buffering energy-absorbing recovery device for interstage separation of an aircraft, the method comprising: step one, according to the application environment and the installation position of the buffering energy-absorbing recovery device, taking the energy-absorbing performance and the reliable connection performance of the buffering energy-absorbing recovery device as design key points; selecting a buffering energy-absorbing mechanism aiming at a design key point of the energy-absorbing performance of the buffering energy-absorbing recovery device; selecting a fixed connecting piece of the buffering and energy-absorbing mechanism aiming at a design key point of reliable connection performance of the buffering and energy-absorbing recovery device; and step three, respectively carrying out numerical simulation analysis and ground verification tests on the buffering energy-absorbing recovery device selected in the step two so as to verify the feasibility of the design method of the buffering energy-absorbing recovery device.
By applying the configuration mode, a design method of a buffering energy-absorbing recovery device for interstage separation of an aircraft is provided, the method takes a small-space large-impulse buffering energy-absorbing recovery device as a research object, firstly, key design points of the device are analyzed according to background input conditions, an analysis method for solving two key design points of buffering energy-absorbing performance and reliable connection performance is provided, and the technical state of the buffering energy-absorbing recovery device is determined according to the analysis method; then, carrying out numerical simulation analysis on the selected buffering and energy-absorbing recovery device to check and evaluate impact, and considering the evaluation result that the buffering and energy-absorbing recovery device designed by the guidance of the patent can effectively recover explosive bolt residual parts; finally, the buffering energy-absorbing recovery device is verified by ground explosion bolt separation and recovery tests, and test results show that the design method of the device is correct and effective. Compared with the prior art, the design method of the buffering energy-absorbing recovery device provided by the invention is safer and more feasible, can safely and reliably recover the explosive bolt separation residual part with high hazard, and is suitable for buffering, absorbing energy and recovering the large-impulse residual part after the explosive bolt is separated at high speed in the aircraft with narrow space.
In the first step, firstly, according to design requirements and design input conditions, design key points of the small-space large-impulse buffering energy-absorbing recovery device are determined. Particularly, in the invention, the buffering energy-absorbing recovery device needs to effectively and reliably recover the explosive bolt separation residual parts with the dynamic quantity of up to 18Ns and the impact energy of up to 300J. Meanwhile, the residual parts of the explosive bolts are close to the equipment in the cabin, and the design space of the effective design is only 30 mm. Based on the design, the energy absorption performance and the reliable connection performance of the buffering energy-absorbing recovery device are taken as design key points according to the application environment and the installation position of the buffering energy-absorbing recovery device.
After the design key point of the buffering energy-absorbing recovery device is determined, the design of the energy-absorbing buffering and reliable connection scheme of the buffering energy-absorbing recovery device is developed aiming at the design key point. Aiming at the design key point of the energy absorption performance of the buffering energy absorption recovery device, a high-temperature alloy honeycomb buffer piece 30 is selected as a buffering energy absorption mechanism; aiming at the design key point of reliable connection performance of the buffering energy-absorbing recovery device, a screw and a pin are selected as fixed connecting pieces of the buffering energy-absorbing mechanism.
By applying the configuration mode, the high-temperature alloy honeycomb buffer piece is selected as the energy-absorbing buffer component, so that the impact force of the explosive bolt residual piece can be effectively reduced, the high-speed separation residual piece is recovered, and the buffer energy-absorbing recovery effect is achieved. The recovery box can be safely and reliably connected under the impact of the explosive bolt residual part by selecting the screw and the pin as the fixed connecting piece of the buffering energy-absorbing mechanism.
Further, in the present invention, when the selection of the superalloy honeycomb cushion 30 is performed using the theoretical analysis method, an inertial force is added to the buffering and energy-absorbing recovery device according to the darnbel principle, so that the structure is changed from an unbalanced power system to a balanced inertial system, the deformation energy of the superalloy honeycomb cushion is calculated using the static load calculation method, and the section load of the superalloy honeycomb cushion 30 is determined according to the deformation energy of the superalloy honeycomb cushion 30.
Specifically, in the invention, the buffering and collecting process of the buffering and energy-absorbing recovery device can be simplified as follows: mass m1After separation, the explosive bolt remains are separated by V0Fly forward at a speed of L0And acts on the superalloy honeycomb cushion 30 having a sectional area a. Average crushing force F of the superalloy honeycomb cushion 300The kinetic energy of the explosive bolt remnants is absorbed under the action of the explosive bolt.
According to the Dalabel principle, inertia force is added into the buffering energy-absorbing recovery device, so that an unbalanced power system of the structure is changed into a balanced inertia system, and deformation energy is calculated by using a static load calculation method. This simplified method can be used for the estimation of the parameters of the energy absorption and recovery device. The high-temperature alloy honeycomb buffer 30 of the buffering energy-absorbing recovery device is crushed and deformed under the impact force of the explosive bolt residual part, and the curve of the force and the displacement is shown in fig. 2. If the energy loss during the impact is neglected, the superalloy honeycomb damper 30 deforms similar to a nonlinear spring whose force versus displacement curve is shown in FIG. 3. Therefore, the stamping deformation of the superalloy honeycomb buffer can be simplified to the force versus displacement curve in fig. 3.
When the compression amount x is less than or equal to LdWhen the temperature of the water is higher than the set temperature,
T0≤Wj(formula one), Wj＝αW0(formula two)
Wherein, T0The kinetic energy of the explosive residual screw and nut, WjThe compression amount of the high-temperature alloy honeycomb buffer piece under dynamic impact is LdPotential energy of time, W0The compression amount of the high-temperature alloy honeycomb buffer piece 30 under static impact is LeThe potential energy of time, alpha, is the conversion coefficient. As an embodiment of the present invention, compared with quasi-static compression, the dynamic impact increases the platform strength, specific load, mass ratio energy absorption, and volume ratio energy absorption of each specification superalloy honeycomb cushion 30 by about 33% on average, so α may be 1.33.
From Wj＝αW0In a clear view of the above, it is known that,
according to the formula one, three and five
Let F0F × a, one can obtain:
From the above, the section load f of the superalloy honeycomb buffer should satisfy
Wherein m is1Quality of explosive bolt remnants, V0A is the cross-sectional area of the superalloy honeycomb cushion 30, alpha is the conversion coefficient, and L is the speed at which the remaining components of the explosive bolt separatedIs the inelastic compression, L, of the superalloy honeycomb cushion 30eIs the amount of elastic compression of the superalloy honeycomb buffer 30.
As one embodiment of the invention, after the explosion bolt is detonated and unlocked, the impulse I is 18 N.s, and the mass m of the explosive bolt residual piece1The impact speed of the explosive bolt residual part is 545g, and is the ratio of the momentum to the mass, namely the impact speed is as follows:
Le≈3.1％L0～5.8％L0≈1.3mm
Ld≈78％L0～90％L0≈19mm
the cross section A of the high-temperature alloy honeycomb buffer piece is 50mm multiplied by 50mm, namely A is 2500mm2
Substituting the above parameters into formula seven to obtain f is not less than 4.9J/cm3。
In the invention, in order to avoid the damage of the explosive bolt residual parts to the cabin body, the impact force generated in the buffer energy absorption and recovery processes of the residual parts cannot be overlarge, and the volume ratio energy absorption of the selected main energy absorption structure is not less than 4.9J/cm3. The volume ratio of the high-temperature alloy honeycomb buffer piece absorbs energy as high as 6J/cm3Initial crushing force of about 22000N, which satisfies the requirements of the main energy absorption structure of the buffering energy absorption recovery device, so the energy absorption structure can be determined to be the main energy absorption structure. The superalloy honeycomb cushion 30 comprises a honeycomb core, a first face plate and a second face plate, the honeycomb core is disposed between the first face plate and the second face plate, and the first face plate and the second face plate are designed to follow the shape of the honeycomb core. As a specific embodiment of the invention, GH99 is selected as the honeycomb core material, the diameter of an inscribed circle is 10mm, the thickness of the honeycomb core is 0.12mm, and the front skin and the rear skin are both GH99 panels with the thickness of 1mm, and the skins and the honeycomb core are connected by brazing. The thickness of the superalloy honeycomb was taken to be 30mm, depending on the buffer space limitations in the chamber.
Further, according to the third formula, the impact energy of the screw of the explosive bolt is 297J, and the specific energy absorption of the high-temperature alloy honeycomb buffer part is 6J/cm3. If L is030mm, the design space is 75cm3And the energy can be absorbed 375J, and the design requirement of small space buffering and energy absorption is met.
After the buffering and energy absorbing design of the high-temperature alloy honeycomb buffer is completed, the connection reliability design of the fixed connecting piece needs to be carried out. The bending moment generated by the average crushing force acting on the high-temperature alloy honeycomb buffer piece is borne by a first screw and a second screw on the recovery box, and the maximum tensile force F borne by the first screw and the second screwPMounting table board L of explosive bolt central shaft distance recovery box2The distance between the first screw and the second screw is L1。
To ensure reliable connection of the buffer collection device, the average crushing force F of the superalloy honeycomb buffer when compressed0Resulting bending moment MLShould be less than the maximum pulling force F of the mounting screw of the honeycomb support bracketPResulting bending moment MPThus:
MP≥ML(formula eight)
FPL1≥F0L2(formula nine)
From the aboveAfter the fixed connecting piece of the buffering and energy absorbing mechanism is analyzed by using a theoretical analysis method, a first screw and a second screw are selected to bear the bending moment when the structure of the high-temperature alloy honeycomb buffering piece 30 is deformed, a pin is selected to bear the shearing moment when the structure of the high-temperature alloy honeycomb buffering piece 30 is deformed, and the maximum tensile force F of the first screw 21 and the second screw 22PAll should satisfy
Wherein L is2Is the distance between the central axis of the explosive bolt and the mounting table of the recovery box, L1Is the distance between the first screw and the second screw, F0Is the average crushing force of the superalloy honeycomb cushion.
As an embodiment of the present invention, L1＝25mm，L227mm, average crushing load F of superalloy honeycomb cushion0The average screw pull obtained for 15000N was:
FP≥16200N
if according to the peak crushing load F of the high-temperature alloy honeycomb buffer piece during instantaneous compression0At 22000N and a safety factor of 1.25 for peak loads, the maximum tension that the screw design can withstand is:
FP≥29700N
according to the invention, the buffering energy-absorbing recovery device is connected with the aircraft cabin through the connecting screw and the shear pin. The tensile strength of the 9310 steel is more than 1200MPa, the impact energy is more than 180J, the impact toughness is more than 2.3J/mm2, and the bearing capacity of the M6 screw made of the 9310 steel can reach 33.9 kN. Therefore, the 9310 steel meets the requirements of the buffer energy-absorbing recovery device on high strength and impact resistance of the fixed connection structure. The maximum tensile force that the screw can bear is 33912N, and then when M6's screw broke, the initial crushing force of GH99 honeycomb was 31400N, satisfied static load-bearing requirement.
After theoretical analysis of the high-temperature alloy honeycomb buffer piece and the fixed connecting piece is completed, numerical simulation verification needs to be carried out on the buffering energy-absorbing recovery device. Specifically, in the third step, when the numerical simulation analysis is performed on the selected buffering energy-absorbing recovery device, modeling and meshing are performed on the buffering energy-absorbing recovery device, and the contact relation between the high-temperature alloy honeycomb buffer and the explosive bolt is established by setting the material property and the boundary condition of the buffering energy-absorbing recovery device; iteratively solving the buffering energy-absorbing recovery device according to the contact relation between the high-temperature alloy honeycomb buffer piece and the explosion bolt to obtain the crushing condition of the high-temperature alloy honeycomb buffer piece and the load curve of the bolt; and verifying the rationality of the selected buffering, energy-absorbing and recycling device according to the obtained crushing condition of the high-temperature alloy honeycomb buffer and the load curve of the screw.
As a specific embodiment of the invention, ABAQUS/Explicit software can be used for carrying out numerical simulation on the buffering and energy-absorbing recovery device, establishing a model of the buffering and energy-absorbing recovery device and carrying out grid division, establishing a contact relation between a honeycomb and an explosive bolt screw by setting material properties and boundary conditions of the buffering and energy-absorbing recovery device, and obtaining the crushing condition of the high-temperature alloy honeycomb buffer and the load curve of the screw after iterative solution. According to simulation calculation, after the explosive bolt residual piece impacts the high-temperature alloy honeycomb buffer piece, the high-temperature alloy honeycomb buffer piece is crushed after entering plastic deformation. The maximum displacement of the high-temperature alloy honeycomb buffer piece when being crushed is about 15.2mm and is less than 30mm of design space, and the requirement of buffering and energy absorption is met. At the moment that the residual screw of the explosive bolt impacts the high-temperature alloy honeycomb buffer, the maximum tensile force of the connecting screw of the buffer recovery box and the cabin body is 16113N, which is smaller than the snapping load 33912N, and the residual strength coefficient is 1.5, so that the bearing requirement of the screw is met.
After the simulation verification of the buffering energy-absorbing recovery device is completed, the buffering test verification needs to be performed on the buffering energy-absorbing recovery device. In the third step, when the selected buffering energy-absorbing recovery device is subjected to ground verification test, the explosion bolt is installed on the test bed through the nut, one end of the explosion bolt is not restrained, the buffering energy-absorbing recovery device is installed at one end of the nut, and the explosion bolt is detonated to verify the buffering performance of the buffering energy-absorbing recovery device.
As an embodiment of the present invention, as shown in fig. 4 and 5, an explosive bolt 100 is mounted on a test bed by a nut 200, one end of the explosive bolt 100 is not restrained, a buffering energy-absorbing recovery device is mounted on one end of the nut 200, and the explosive bolt 100 is detonated to verify the buffering performance of the buffering energy-absorbing recovery device. The buffering energy-absorbing recovery device is fixed on the mounting boss through two M6 screws. In order to increase the shearing resistance of the buffering energy-absorbing recovery device, a positioning pin is arranged at the bottom. In order to reduce the deformation of the energy-absorbing recovery device under the impact condition, a support structure is added at the lower end of the rear part of the energy-absorbing recovery device to bear the additional bending moment generated by the impact. The honeycomb core material of the superalloy honeycomb cushion 30 may be a superalloy.
Tests prove that after the explosive bolt 100 is detonated, five connecting screws of the recovery box are kept intact and do not generate plastic deformation, three positioning pin holes of the recovery box do not generate deformation, and the buffering and collection of explosive bolt residual parts are successfully realized. The speed of the explosion bolt residual piece when impacting the high-temperature alloy honeycomb buffer piece 30 is measured to be 33m/s through tests, the safety coefficient is 2, and then the load of the explosion bolt residual piece is 17249N. According to the formula, the tensile force borne by the screw is 18628N, and the maximum tensile force borne by the screw is 33912N, which indicates that the strength and the rigidity of the screw meet the design requirements. The maximum tension of the screw obtained through numerical simulation is 16113N, the numerical calculation error is 13.5%, and the calculation error is small, so that the analysis method provided by the design can effectively support the design of the buffering energy-absorbing recovery device.
From the test procedures and results, it can be seen that: after the explosion bolt is detonated, the residual kinetic energy of the explosive bolt residual piece is absorbed by the high-temperature alloy honeycomb buffer piece, and the explosive bolt residual piece is recovered into the recovery box without rebound phenomenon, which shows that the energy absorption and buffering performance of the buffering and recovery device is better; the connection screw of the recovery box is intact, which shows that the reliable connection performance of the buffering energy-absorbing recovery device is good, and the design requirements are met.
According to another aspect of the present invention, there is provided a buffering energy-absorbing recovery apparatus, which includes a recovery box 10, a fixed connector 20 and a high-temperature alloy honeycomb buffer 30, wherein the buffering energy-absorbing recovery apparatus is designed using the above-mentioned method for designing a buffering energy-absorbing recovery apparatus, the high-temperature alloy honeycomb buffer 30 is disposed between the recovery box 10 and an explosive bolt, and the recovery box 10 is connected to a cabin body through the fixed connector 20. The energy-absorbing recovery device designed by the design method of the energy-absorbing recovery device is safer and more feasible, can safely and reliably recover the explosive bolt separation residual parts with high hazard, and is suitable for buffering, absorbing energy and recovering the large-impulse residual parts after the explosive bolts are separated at high speed in the aircraft with narrow space.
Further, in the present invention, as shown in fig. 1, the superalloy honeycomb cushion 30 comprises a honeycomb core, a first face plate and a second face plate, the honeycomb core is disposed between the first face plate and the second face plate, and the first face plate and the second face plate are conformal with the honeycomb core; the fixed connection 20 includes a first screw 21, a second screw 22, and a pin 23. As an embodiment of the invention, the body structure of the superalloy honeycomb buffer 30 is a superalloy honeycomb thin-wall structure with an energy-absorbing and buffering effect, and the honeycomb core is provided with a plurality of hexagonal accommodating holes for accommodating explosive bolt residual parts in the process of aircraft interstage separation.
In summary, the invention provides a design method of a small-space large-impulse buffering and energy-absorbing recovery device, which needs to solve two key technical difficulties of buffering and energy-absorbing performance and reliable connection performance of the buffering and energy-absorbing recovery device through methods such as theoretical analysis, numerical simulation, experimental verification and the like according to input conditions, and verifies the feasibility of the design method. Compared with the prior art, the design method disclosed by the invention has the two key design points of insufficient design space and high momentum of recovered residual parts, and the two key design points of the buffering and energy-absorbing performance of the honeycomb and the reliable connection performance of the collecting device are fastened, so that the work is developed by comprehensively applying theories, numerical simulation and ground verification tests, and the design method has important guiding significance on the design of the buffering and energy-absorbing recovery device.
Spatially relative terms, such as "above … …," "above … …," "above … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial relationship to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary term "above … …" can include both an orientation of "above … …" and "below … …". The device may be otherwise variously oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
It should be noted that the terms "first", "second", and the like are used to define the components, and are only used for convenience of distinguishing the corresponding components, and the terms have no special meanings unless otherwise stated, and therefore, the scope of the present invention should not be construed as being limited.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. A design method of a buffering energy-absorbing recovery device for interstage separation of an aircraft is characterized by comprising the following steps:
step one, according to the application environment and the installation position of the buffering energy-absorbing recovery device, taking the energy-absorbing performance of the buffering energy-absorbing recovery device as a first design key point, and taking the reliable connection performance of the buffering energy-absorbing recovery device as a second design key point;
secondly, selecting a high-temperature alloy honeycomb buffer piece as a buffering and energy-absorbing mechanism aiming at a first design key point of the energy-absorbing performance of the buffering and energy-absorbing recovery device; aiming at a second design key point of reliable connection performance of the buffering energy-absorbing recovery device, a screw and a pin are selected as fixed connecting pieces of the buffering energy-absorbing mechanism;
respectively carrying out numerical simulation analysis and ground verification tests on the buffering energy-absorbing recovery device selected in the step two so as to verify the feasibility of the design method of the buffering energy-absorbing recovery device;
when a theoretical analysis method is used for selecting the high-temperature alloy honeycomb buffering piece, according to the Darbel principle, inertia force is added into a buffering and energy-absorbing recovery device, so that an unbalanced power system is changed into a balanced inertia system, the deformation energy of the high-temperature alloy honeycomb buffering piece is calculated by using a static load calculation method, and the section load of the high-temperature alloy honeycomb buffering piece is determined according to the deformation energy of the high-temperature alloy honeycomb buffering piece;
the section load f of the high-temperature alloy honeycomb buffer part is satisfied
Wherein m is1Quality of explosive bolt remnants, V0The speed of separating the residual parts of the explosive bolt is shown in the specification, A is the cross-sectional area of the high-temperature alloy honeycomb buffer part, alpha is a conversion coefficient, and L isdIs the inelastic compression of the superalloy honeycomb buffer, LeThe elastic compression of the high-temperature alloy honeycomb buffer piece.
2. The method of claim 1, wherein after analyzing the fastening connection of the buffering and energy-absorbing mechanism using a theoretical analysis method, selecting a first screw and a second screw for receiving the bending moment when the superalloy honeycomb buffer structure is deformed, selecting the pin for receiving the shear moment when the superalloy honeycomb buffer structure is deformed, and selecting the maximum tensile force F of the first screw and the second screwPAll should satisfy
Wherein L is2For exploding boltsDistance between central shaft and mounting table of recovery box, L1Is the distance between the first screw and the second screw, F0Is the average crushing force of the superalloy honeycomb cushion.
3. The design method of the energy-absorbing recovery device for the interstage separation of the aircraft according to claim 1, characterized in that in the third step, when the numerical simulation analysis is carried out on the selected energy-absorbing recovery device, the energy-absorbing recovery device is modeled and gridded, and the contact relation between the high-temperature alloy honeycomb buffer and the explosive bolt is established by setting the material properties and the boundary conditions of the energy-absorbing recovery device; iteratively solving the buffering energy-absorbing recovery device according to the contact relation between the high-temperature alloy honeycomb buffer piece and the explosion bolt to obtain the crushing condition of the high-temperature alloy honeycomb buffer piece and the load curve of the bolt; and verifying the rationality of the selected buffering, energy-absorbing and recycling device according to the obtained crushing condition of the high-temperature alloy honeycomb buffer and the load curve of the screw.
4. The design method of the energy-absorbing recovery device for the interstage separation of the aircraft according to claim 3, characterized in that in the third step, when the ground verification test is carried out on the selected energy-absorbing recovery device, an explosion bolt is installed on a test bench through a nut, one end of the explosion bolt is not restrained, an energy-absorbing recovery device is installed at one end of the nut, and the explosion bolt is detonated to verify the buffering performance of the energy-absorbing recovery device.
5. A buffering energy-absorbing recovery device, characterized in that, buffering energy-absorbing recovery device includes retrieving box (10), fixed connector (20) and superalloy honeycomb bolster (30), buffering energy-absorbing recovery device uses the buffering energy-absorbing recovery device design method of any one of claims 1 to 4 to design, superalloy honeycomb bolster (30) sets up retrieve between box (10) and the explosion bolt, retrieve box (10) and cabin body coupling through fixed connector (20).
6. The device according to claim 5, wherein the superalloy honeycomb bumper (30) comprises a honeycomb core, a first face sheet, and a second face sheet, the honeycomb core disposed between the first face sheet and the second face sheet, the first face sheet and the second face sheet following the honeycomb core; the fixed connecting piece (20) comprises a first screw (21), a second screw (22) and a pin (23).
7. The device according to claim 6, wherein the honeycomb core has a plurality of hexagonal receiving holes for receiving explosive bolt remnants during separation between aircraft stages.
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| CN113237394A (en) * | 2021-04-28 | 2021-08-10 | 北京星途探索科技有限公司 | Single-side detachable explosion-proof bolt bar rebounding device |
| CN113280695A (en) * | 2021-06-10 | 2021-08-20 | 北京星途探索科技有限公司 | But single face reassembling type disengaging structure device |
| CN118294097A (en) * | 2024-06-05 | 2024-07-05 | 中国空气动力研究与发展中心超高速空气动力研究所 | Model recovery device for hypersonic wind tunnel model free flight test and design method |
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| CN108033038A (en) * | 2017-12-14 | 2018-05-15 | 北京航空航天大学 | Blasting bolt buffer unit |
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