CN115127401A - Method for reusing ballistic target free flight model - Google Patents
Method for reusing ballistic target free flight model Download PDFInfo
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- CN115127401A CN115127401A CN202210819791.5A CN202210819791A CN115127401A CN 115127401 A CN115127401 A CN 115127401A CN 202210819791 A CN202210819791 A CN 202210819791A CN 115127401 A CN115127401 A CN 115127401A
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41J—TARGETS; TARGET RANGES; BULLET CATCHERS
- F41J9/00—Moving targets, i.e. moving when fired at
- F41J9/08—Airborne targets, e.g. drones, kites, balloons
Abstract
The invention relates to the technical field of ballistic target tests, in particular to a method for reusing a ballistic target free flight model. According to the method, through the structural optimization design of the model, the model is prevented from being damaged due to the concentrated stress generated at the assembly joint of the model. Meanwhile, the center of gravity of the model is set, so that the model and the pressure center are in a certain specific position relation, the flight of the model is more stable while the test requirements are met, the model can enter a recovery field according to the preset condition, and the model is prevented from deviating out of the recovery field in the recovery process. And a recovery field with adaptive recovery capacity is arranged at the tail end of the target chamber, so that the model is decelerated and finally recovered without damage. And detecting the models before and after the test, and if the physical quantity parameters of the recovered models are unchanged compared with the physical quantity parameters before the test or the variable quantity meets the test requirement, the recovered test models can be reused. The recovery and the reuse of the ballistic target test model are realized, the recovery success rate is high, the test cost is reduced, and the test efficiency is improved.
Description
Technical Field
The invention relates to the technical field of ballistic target tests, in particular to a method for reusing a ballistic target free flight model.
Background
The method has the advantages of free flight of the model during ballistic target test, no support interference, real and controllable target chamber environment and the like, and is one of ideal ways for obtaining the pneumatic parameters of the free flight model. Because the model has higher flying speed and high complete recovery difficulty during ballistic target test, the model is generally not considered to be recovered but directly intercepted and broken during test, namely, one test model can only be used once. The processing cost of the model is high, the manufacturing period is long, the test efficiency is seriously restricted, the test cost is increased, and the dust and the fragments generated by intercepting the broken model pollute the environment, so that the resource waste is caused.
Disclosure of Invention
Technical problem to be solved
The invention aims to provide a method for reusing a ballistic target free flight model, which solves the problem that the existing ballistic target free flight model cannot be completely recovered and reused.
(II) technical scheme
In order to achieve the above object, in a first aspect, the present invention provides a method for reusing a ballistic target free flight model, which in a first implementation manner includes:
designing a model, namely designing a main body structure of the model into an integral structure, wherein the center of gravity of the model is in front of a pressure center in the flight direction;
before the test, measuring and recording physical quantity parameters of the model, and setting a recovery field at the tail end of the target chamber based on the geometric dimension, the mass and the launching speed of the model, wherein the recovery field is positioned on the flight track of the model and used for recovering the model during the test;
and after the test, measuring the physical quantity parameters of the recovered model, and if the physical quantity parameters of the recovered model are compared with the physical quantity parameters of the model before the test and have no change or the variable quantity meets the test requirement, the recovered test model can be reused.
In combination with the first implementation manner, in the second implementation manner, the recovery field comprises flame-retardant deceleration parts which are arranged in a multistage manner along the flight direction of the model, the material density of the flame-retardant material layers of the flame-retardant deceleration parts at each stage is sequentially increased in the flight direction of the model, and the adjacent flame-retardant deceleration parts are in surface contact connection;
in the flying direction of the model, each stage of the flame-retardant deceleration part comprises at least one flame-retardant deceleration layer, the material density of the flame-retardant deceleration layers in each stage of the flame-retardant deceleration part is the same, and the adjacent flame-retardant deceleration layers are in contact connection.
In combination with the first implementation manner, in a third implementation manner, each stage of the inflaming retarding deceleration part comprises one inflaming retarding deceleration layer.
With reference to the second or third implementation manner, in a fourth implementation manner, the flame-retardant deceleration layers are concentrically arranged, and the sectional areas of the flame-retardant deceleration layers are sequentially increased in the flight direction of the model.
With reference to any one of the second to fourth implementation manners, in a fifth implementation manner, each of the retarding and decelerating layers is formed by splicing a plurality of materials, and adjacent blocks are in surface contact connection.
With reference to the fifth implementation manner, in the sixth implementation manner, the sizes of the blocks of materials used for splicing each flame-retardant deceleration layer are the same.
With reference to the sixth implementation manner, in the seventh implementation manner, each material for splicing each flame-retardant deceleration layer is a cube.
With reference to any one of the second to seventh implementation manners, in an eighth implementation manner, the flame-retardant deceleration layer is a flame-retardant sponge.
With reference to any one of the second to eighth implementation manners, in a ninth implementation manner, each flame-retardant deceleration layer is embedded in a fixed frame, the inner side surface of the fixed frame is in contact connection with the outer peripheral surface of the flame-retardant deceleration layer, and the outer peripheral surface of the fixed frame is in contact with the inner wall surface of the target chamber;
the material density of the fixing frame is greater than that of the flame-retardant speed-reducing layer embedded in the fixing frame.
With reference to any one of the second to eighth implementation manners, in a tenth implementation manner, a deviation-preventing portion is arranged on the periphery of each flame-retardant deceleration layer, and the material density of the deviation-preventing portion is greater than that of the flame-retardant deceleration layer at the same level, so that the model is prevented from deviating from the recovery field in the recovery process.
With reference to the tenth implementation manner, in an eleventh implementation manner, each of the run-out preventing portions is embedded in a fixing frame, an inner side surface of the fixing frame is in contact connection with an outer circumferential surface of the run-out preventing portion, and the outer circumferential surface of the fixing frame is in contact with an inner wall surface of the target chamber;
the material density of the fixing frame is greater than that of the deviation blocking part embedded in the fixing frame.
With reference to any one of the foregoing implementation manners, in this embodiment, the distance between the center of gravity and the center of pressure of the model is not less than 5% of the length of the model; and/or
The launched model is wrapped by the bullet support, and sets up at the supporting shoe of the bottom of bullet support and bullet support structure as an organic whole.
(III) advantageous effects
The technical scheme of the invention has the following advantages: according to the method for reusing the ballistic target free flight model, the model is prevented from being damaged due to concentrated stress generated at the assembly joint of the model through the structural optimization design of the model. Meanwhile, the center of gravity of the model is set, so that the model and the pressure center are in a certain specific position relation, the flight of the model is more stable while the test requirements are met, the model can enter a recovery field according to the preset condition, and the model is prevented from deviating out of the recovery field in the recovery process. Based on the geometric dimension, the quality and the launching speed of the model, a recovery field with adaptive recovery capacity is selected to be arranged at the tail end of the target chamber, so that the model is decelerated and finally recovered without damage. And respectively detecting the models before and after the test, and if the physical quantity parameters of the recovered models are compared with the physical quantity parameters of the models before the test, and the physical quantity parameters are unchanged or the variable quantity meets the test requirements, the recovered test models can be reused. The method can realize the recovery and the repeated use of the ballistic target test model, has high recovery success rate, can effectively reduce the test cost, improve the test efficiency, avoid the resource waste and reduce the pollution of dust and fragments generated by the interception and the fragmentation of the model to the environment.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention are clearly and completely described, and it is obvious that the described embodiments are a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
Ballistic target testing is one of the ideal ways to obtain the aerodynamic parameters of a free-flight model. In general, multiple tests are typically required for the same model to verify or achieve different test goals. In order to obtain the influence of the model flight speed and the environmental parameters on the pneumatic parameters in the test, the most ideal situation is that the physical quantity characteristic parameters such as the centroid position, the mass, the rotational inertia and the like of the model are completely the same, but the difference of the processing precision of different models hardly ensures that the physical quantity characteristic parameters are the same. However, in the ballistic target test, the model has high flying speed, high complete recovery difficulty and high cost, so that the test model can only be used once in the prior art. The test cost is increased, the resources are wasted, and the dust and the fragments generated by intercepting the crushing model pollute the environment. But also may have some influence on the test results. In addition, because characteristic mark points need to be made on the surface of the model before the ballistic target aerodynamic force test and the characteristic mark points are scanned and associated, the preparation time before the machining and the test is long, and the test efficiency is seriously restricted. However, in order to solve the above problems, at least two important technical problems need to be solved, and firstly, how to ensure that the free flight model can smoothly enter a recovery field; and secondly, under the condition of considering both the cost and the test efficiency, how to realize the lossless recovery of the model in the recovery field. Through long-term research and test, the applicant mainly starts from the aspects of model design and model recovery, and detects the recovered model, so that the reuse of the recovered model is finally realized, and the model processing cost is reduced. The same model is repeatedly used, so that the precision of test data is guaranteed, and the influence of the machining precision of the model on a test result is reduced. The preparation time of the test model is shortened, and the test efficiency is improved. In addition, the pollution of dust and debris generated by the model intercepting and crushing to the environment is reduced.
The inventive concept and embodiments are further illustrated by the following specific examples.
The method for reusing the ballistic target free flight model provided by the embodiment of the invention needs the model to meet certain requirements, and specifically comprises the following steps:
with the major structure design of model structure as an organic whole, can adopt mode processing that integrated into one piece processed or 3D printed, compare concatenation and the threaded connection mode commonly used among the prior art, can effectively avoid the model when accelerating in the transmitter and retrieve the in-process, in the junction stress concentration of model, lead to the major structure fracture or the breakage of model. In some preferred embodiments, on the basis of ensuring that the model has a shape similar to the geometry of the aircraft, the remaining structural parts are rounded, typically by a fillet of 0.05mm to 2.5mm depending on the model size.
The model is designed as follows: the center of gravity of the model is in front of the pressure center in the flying direction, so that the model can stably and successfully fly into the recovery field, and the probability of deviating from the recovery field after entering the recovery field is lower, thereby improving the recovery success rate. In order to ensure better flight stability of the model, in some preferred embodiments, the center of gravity of the model is not less than 5% of the length of the model, for example, 5%, 6%, 8%, 10%, 14%, 20%, etc. of the length of the model. In some alternative embodiments, the model is designed to be blunt without affecting the test, i.e. the model is designed to have a blunt profile without affecting the test. The blunt profile model has large resistance coefficient, and the model has shorter deceleration movement distance in a recovery field, thereby further improving the recovery success rate of the model.
In some preferred embodiments, the launched model is wrapped with a sabot which is easily separated when separated from the model and does not affect the initial trajectory of the model. The split supporting blocks are not arranged at the bottom of the bullet holder, the supporting blocks and the bullet holder are processed into a whole, the phenomenon that the bullet holder is damaged by a model due to collision in the flying process of the model due to the fact that the supporting blocks can be caught up by the supporting blocks behind to cause collision is avoided, or the model decelerates in a recovery field, the supporting blocks catch up the model due to collision along with the fact that the movement trajectory of the model decelerates unobviously in the recovery field to cause damage to the model is avoided, and therefore the lossless recovery rate of the model is further improved.
The model is generally made of high-strength metal or engineering plastic, such as titanium alloy, stainless steel, aluminum alloy, high-strength nylon, and the like.
Through the structural optimization design of the model, the damage of the model caused by the concentrated stress generated at the assembly joint of the model is avoided. Meanwhile, the specific position relation between the model and the pressure center is realized by setting the gravity center of the model, so that the model can fly more stably while meeting the test requirement, the model can enter a recovery field according to the preset condition, and the model is prevented from deviating from the recovery field in the recovery process. On the basis, the recovery field is arranged at the tail end of the target chamber and on the flight track of the model after the model is ensured to fly freely for a long distance in the target chamber, so that the important guarantee for recovering the test model is finally realized, and the recovery field and the prior model structure optimization design coact but cannot be realized.
In the embodiment, the recovery is carried out in a soft recovery mode according to the yield strength limit born by the model material and the deceleration movement characteristic of the model in the recovered material. Generally, based on the geometric dimension, the mass and the launching speed of the model, a recovery field with adaptive recovery capacity is selected to be arranged at the tail end of the target chamber, so that the model is decelerated and finally recovered without damage.
In one embodiment, the recovery field comprises flame-retardant deceleration parts which are arranged in a plurality of stages along the flight direction of the model, the material density of the flame-retardant material layers of each stage of flame-retardant deceleration part is sequentially increased in the flight direction of the model so as to reduce the distance of the recovery field, and each stage of flame-retardant deceleration part comprises one flame-retardant deceleration layer. In order to reduce the interference of the interface of the flame-retardant deceleration layer on the model movement, the adjacent flame-retardant deceleration layers are in contact connection, so that no gap exists between the two adjacent flame-retardant deceleration layers and the two adjacent flame-retardant deceleration layers are not deformed. The flame-retardant retarding layer is generally soft with common densityA flame retardant material. Preferably, the flame-retardant deceleration layer is made of flame-retardant sponge with the density of 15kg/m on the market at present 3 ～100kg/m 3 The flame-retardant sponge has mature processing technology and can meet the requirements.
In some preferred embodiments, the flame retarding and decelerating layers are arranged concentrically, and the cross-sectional area of each flame retarding and decelerating layer increases sequentially in the flight direction of the model, for example, the cross-section of each flame retarding and decelerating layer is square, the center of the cross-section of each flame retarding and decelerating layer is on a straight line, the side length of the cross-section of the flame retarding and decelerating layer positioned at the front side is 1.5m, and the side length of the cross-section of the adjacent and following flame retarding and decelerating layer is 2m in the flight direction of the model. The cross-sectional area of the flame-retardant deceleration layer which is further back in the flight direction is larger, so that the model can be further prevented from deviating out of the recovery field after entering the recovery field.
In some preferred embodiments, each flame retardant deceleration layer is formed by splicing multiple pieces of materials, so that the processing is convenient, the arrangement of a recovery field is convenient, and the damaged part is replaced individually. In order to further reduce the interference of the flame retardant deceleration layer interface on the movement of the model, the adjacent blocks are connected in a surface contact mode.
In some preferred embodiments, the flame-retardant deceleration layer is fixed by a fixing frame, namely, each flame-retardant deceleration layer is embedded in the fixing frame, the inner side surface of the fixing frame is in contact connection with the surface of the flame-retardant deceleration layer, and the fixing frame is connected with the target chamber. The material density of the fixing frame is generally greater than that of the flame-retardant speed-reducing layer embedded in the fixing frame, and the fixing frame has a fixing effect and also has a protection effect on a target chamber. Preferably, the fixing frame adopts a wooden frame.
In order to further improve interchangeability and reduce the arrangement difficulty, the sizes of the materials for splicing each flame-retardant deceleration layer are preferably the same.
In some preferred embodiments, the size of each block of material used for splicing the flame retardant and deceleration layer is 0.5m by 0.5m cube, and further preferably, the size error of each block of material is less than 2 mm.
Before the recycling field is arranged, size and quality detection is carried out on each processed/purchased material, and the quality, the size and the density of each material are marked on the surface of the recycling field, so that the recycling field is convenient to arrange.
In other primary embodiments, each stage of the retarding deceleration portion may include a plurality of retarding deceleration layers, e.g., two, three, etc., as desired. The material density of the flame retarding and decelerating layers in the same flame retarding and decelerating part is the same, for example, one of the flame retarding and decelerating parts in front has two flame retarding and decelerating layers, and the two flame retarding and decelerating layers are sealed at 15kg/m 3 The flame-retardant sponge. The adjacent rear flame-retardant deceleration part is also provided with two flame-retardant deceleration layers, and the two flame-retardant deceleration layers are sealed at 20kg/m 3 The flame-retardant sponge. The number of stages of the retarding and decelerating sections and the number of the retarding and decelerating layers in each stage of the retarding and decelerating sections are set according to actual needs, and can be determined by software simulation and the like. In the case where the model-lossless recovery can be achieved, the smaller the size of the recovery field in the flight direction, the better.
In order to further prevent the mold from deviating out of the recovery field during recovery, in some preferred embodiments, a deviation preventing part is disposed at the periphery of each of the inflaming retarding deceleration layers, and the material density of the deviation preventing part is greater than that of the inflaming retarding deceleration layers at the same level, so as to prevent the mold from deviating out of the recovery field during recovery. To facilitate the arrangement of the recycling site, the material of the deviation preventing part is made of a flame retardant material having a relatively high density, for example, 100kg/m 3 A flame-retardant sponge. In the embodiment of fixing the flame-retardant speed-reducing layer by using the fixing frame, the deviation-preventing part is arranged between the flame-retardant speed-reducing layer and the fixing frame, the material density of the fixing frame is greater than that of the deviation-preventing part embedded in the fixing frame, the deviation-preventing part is in a frame shape, the inner side surface of the deviation-preventing part is in contact connection with the flame-retardant speed-reducing layer surface, the outer peripheral surface of the deviation-preventing part is in surface contact connection with the inner side surface of the fixing frame, and the outer peripheral surface of the fixing frame is connected with the target chamber to form a structure with the density increasing from inside to outside in the radial direction.
Before the test, physical quantity parameters of the model are measured and recorded, and the terminal field is arranged at the tail end of the target chamber and positioned on the flight path of the model based on the geometric dimension, the mass and the launching speed of the model. And after the recovery of the model is finished, measuring the physical quantity parameters of the recovered model, and if the physical quantity parameters of the recovered model are compared with the physical quantity parameters of the model before the test and have no change or the variable quantity meets the test requirement, the recovered test model can be reused. Otherwise, it cannot be reused or can be used only in limited ways (used in tests that do not affect the test results).
The physical quantity parameters of the measured model before and after the test mainly comprise the overall dimension, the profile, the mass center, the rotational inertia and the like of the model, and are determined according to actual needs. For example, for an aerodynamic force test model, the surface of the model is usually blackened, surface characteristic mark points are manufactured in a laser marking mode, when the recovered model physical quantity parameters are not changed, the model surface mark points are clear and can be repeatedly used, and when any condition is not met, the aerodynamic force test model is not suitable for repeatedly carrying out the same aerodynamic force test.
The method for reusing the ballistic target free flight model in this embodiment can be used for low-speed and high-speed (about 1500m/s) ballistic target tests. Particularly, the model lossless recovery success rate and the reuse rate are high aiming at the high structure and material strength, the blunt appearance and the good flight stability.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: each embodiment does not include only one independent technical solution, and in the case of no conflict between the solutions, the technical features mentioned in the respective embodiments may be combined in any manner to form other embodiments as will be understood by those skilled in the art.
Furthermore, modifications may be made to the technical solutions described in the foregoing embodiments, or equivalents may be substituted for some of the technical features thereof, without departing from the scope of the present invention, and the essence of the corresponding technical solutions does not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (10)
1. A method of reusing a ballistic target free-fly model, comprising:
designing a model, wherein the main structure of the model is designed into an integral structure, and the center of gravity of the model is in front of a pressure center in the flight direction;
before the test, measuring and recording physical quantity parameters of the model, and setting a recovery field at the tail end of a target chamber based on the geometric dimension, the mass and the launching speed of the model, wherein the recovery field is positioned on the flight track of the model and is used for recovering the model during the test;
and after the test, measuring the recovered physical quantity parameters of the model, and if the recovered physical quantity parameters of the model are compared with the physical quantity parameters of the model before the test and have no change or the variable quantity meets the test requirement, the recovered test model can be reused.
2. The method of reusing a ballistic target free-fly model according to claim 1, wherein: the recovery field comprises flame-retardant decelerating parts which are arranged in a multistage manner along the flight direction of the model, the material density of the flame-retardant material layers of the flame-retardant decelerating parts of each stage is sequentially increased in the flight direction of the model, and the adjacent flame-retardant decelerating parts are in surface contact connection;
in the flying direction of the model, each stage of the flame-retardant deceleration part comprises at least one flame-retardant deceleration layer, the material density of the flame-retardant deceleration layers in each stage of the flame-retardant deceleration part is the same, and the adjacent flame-retardant deceleration layers are in contact connection.
3. The method of reusing a ballistic target free-fly model according to claim 2, wherein: each flame-retardant deceleration layer is concentrically arranged, and the sectional area of each flame-retardant deceleration layer is sequentially increased in the flying direction of the model.
4. The method of reusing a ballistic target free-fly model according to claim 2, wherein: each flame-retardant deceleration layer is formed by splicing a plurality of materials, and adjacent blocks are in surface contact connection.
5. The method of reusing a ballistic target free-fly model according to claim 4, wherein: and the sizes of all the materials for splicing each flame-retardant deceleration layer are the same.
6. The method of reusing a ballistic target free-fly model according to claim 2, wherein: each flame-retardant speed-reducing layer is embedded in the fixing frame, the inner side surface of the fixing frame is in contact connection with the outer peripheral surface of the flame-retardant speed-reducing layer, and the outer peripheral surface of the fixing frame is in contact with the inner wall surface of the target chamber;
the material density of the fixing frame is greater than that of the flame-retardant speed-reducing layer embedded in the fixing frame.
7. The method of reusing a ballistic target free-fly model according to claim 2, wherein: the flame-retardant speed-reducing layer is made of flame-retardant sponge.
8. The method of reusing a ballistic target free-fly model according to claim 2, wherein: and arranging a deviation blocking part at the periphery of each flame-retardant deceleration layer, wherein the material density of the deviation blocking part is greater than that of the flame-retardant deceleration layer at the same level, so that the model is prevented from deviating out of the recovery field in the recovery process.
9. The method of reusing a ballistic target free-fly model according to claim 8, wherein: each deviation blocking part is embedded in a fixed frame, the inner side surface of the fixed frame is in contact connection with the outer peripheral surface of the deviation blocking part, and the outer peripheral surface of the fixed frame is in contact with the inner wall surface of the target chamber;
the material density of the fixing frame is greater than that of the deviation blocking part embedded in the fixing frame.
10. The method of reusing a ballistic target free-fly model according to claim 1, wherein:
the distance between the center of gravity and the pressure center of the model is not less than 5% of the length of the model; and/or
The launched model is wrapped by the bullet support, and the supporting block arranged at the bottom of the bullet support and the bullet support are of an integrated structure.
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| CN202210819791.5A CN115127401B (en) | 2022-07-13 | Reuse method of ballistic target free flight model |
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| CN202210819791.5A CN115127401B (en) | 2022-07-13 | Reuse method of ballistic target free flight model |
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| CN110530599A (en) * | 2019-09-27 | 2019-12-03 | 中国航空工业集团公司西安飞机设计研究所 | A kind of reusable drop wind tunnel test weapon model |
| CN113513948A (en) * | 2021-08-04 | 2021-10-19 | 中国空气动力研究与发展中心超高速空气动力研究所 | Device and method for decelerating and recovering ultrahigh-speed flight model |
| CN114323713A (en) * | 2021-11-17 | 2022-04-12 | 航天科工微电子系统研究院有限公司 | Reusable flight test scattering platform system |
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