CN215413432U - Reducing eccentric device suitable for small-moment inertia product posture adjustment - Google Patents
Reducing eccentric device suitable for small-moment inertia product posture adjustment Download PDFInfo
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- CN215413432U CN215413432U CN202121500232.5U CN202121500232U CN215413432U CN 215413432 U CN215413432 U CN 215413432U CN 202121500232 U CN202121500232 U CN 202121500232U CN 215413432 U CN215413432 U CN 215413432U
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Abstract
The invention provides a reducing eccentric device suitable for adjusting the posture of a small-rotational-inertia product, which comprises a switching ring, a cabin body and a buffer pad, wherein the cabin body is of a columnar structure, the rear end of the cabin body is fixedly connected with a rocket sled body, and the axis direction is parallel to the running direction of the rocket sled; one end of the adapter ring is fixedly connected with the front end of the cabin body, the other end of the adapter ring is provided with an opening, and the tail of the tested object is coaxially and fixedly connected in the opening of the adapter ring; a cushion pad is filled between the rear end face of the tested object and the bottom of the inner cavity of the adapter ring; the outer diameter of the cabin body is smaller than that of the adapter ring, and the distance between the upper edge of the cabin body and the upper edge of the adapter ring is smaller than that between the lower edge of the cabin body and the lower edge of the adapter ring. The invention can realize the effective control of the flying attitude of the separated product bullet sledge.
Description
Technical Field
The invention belongs to the technical field of military target range test, mainly relates to a rocket sled test technology, and particularly relates to a pneumatic layout device which is used for adjusting flight postures of small-sized rotary inertia products in an ultrasonic rocket sled test and realizing comprehensive examination of technical indexes of the products.
Background
The rocket sled test is a ground simulation test system which takes a rocket engine as power and slides along a special track between a wind tunnel test and a flight test, mainly provides relevant speed and acceleration conditions in the weapon system development process, and is used for function examination of complete machines or parts of airplanes, missiles, aerospace aircrafts and the like.
At present, aiming at a product with a small slenderness ratio in a rocket sled test, in order to control the flight attitude of the product after the constraint between the product and a sled body is relieved, factors such as the test purpose, the external dimension of the product, the structure of a rocket sled test platform, the undisturbed separation of the rocket sled and the like are generally considered in the test design process, a cylindrical lengthened cabin device with the length, the diameter, the wall thickness, the material and the matching mode meeting the test specification is designed at the tail part of the product, and the design of the lengthened cabin device provides a reliable mechanical environment for the stable flight of the product on the premise of not influencing the function and performance examination of the product through the verification of a large number of rocket sled tests. The difference of the test technical indexes and the pneumatic appearance of the product, especially for the small rotational inertia (less than or equal to 100 kg.m)2) For the product, under the action of the same incoming flow Mach number, the overturning moment formed by the 'belly' high-pressure area of the 'cylindrical' lengthened cabin enables the product to generate larger angular acceleration around the mass center, the flight attitude is easier to change, and the situation that the attack angle of the product is difficult to control sometimes occurs, so that the traditional lengthened cabin structure does not meet the requirements.
The applicant of the invention searches domestic and foreign patent documents and published journal articles in a certain range, and reports or documents closely related to and the same as the invention are not found.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides a reducing eccentric device suitable for adjusting the attitude of a small-moment product, which can effectively control the flight attitude of the product after the product is separated from a sledge.
The technical scheme adopted by the invention for solving the technical problems is as follows: a reducing eccentric device suitable for adjusting the posture of a small-rotational-inertia product comprises a switching ring, a cabin and a buffer pad.
The cabin body is of a columnar structure, the rear end of the cabin body is fixedly connected with the rocket sled body, and the axis direction is parallel to the running direction of the rocket sled; one end of the adapter ring is fixedly connected with the front end of the cabin body, the other end of the adapter ring is provided with an opening, and the tail of the tested object is coaxially and fixedly connected in the opening of the adapter ring; a cushion pad is filled between the rear end face of the tested object and the bottom of the inner cavity of the adapter ring; the outer diameter of the cabin body is smaller than that of the adapter ring, and the distance between the upper edge of the cabin body and the upper edge of the adapter ring is smaller than that between the lower edge of the cabin body and the lower edge of the adapter ring.
And a plurality of reinforcing ribs are arranged between the cabin body and the adapter ring.
The outer diameter of the cabin body is 2/3 of the outer diameter of the adapter ring, the length of the cabin body is 3.5 times of the outer diameter of the cabin body, and the distance between the cabin body and the upper edge of the adapter ring is 1/8 of the outer diameter of the adapter ring.
The cabin body is of a cylindrical structure with an opening at one end and a sealing at one end, the cabin body is made of aluminum materials with the model of 2A12, and the wall thickness is 20 mm.
The tail of the cabin body is tightly matched with the rear snap ring and is arranged on the rocket sled body, and the tail of the cabin body is tightly attached to the rear baffle of the rocket sled body in the axial direction.
The adapter ring is made of aluminum, the inner cavity is a step hole, the inner diameter of the rear end is smaller than that of the front end, and the wall thickness of the end face of the rear end is 30 mm.
The opening of the adapter ring is connected with a product in a threaded mode, and the adapter ring is fixedly connected with the cabin body through welding.
The cushion pad is made of rubber materials.
The invention has the beneficial effects that:
1. the reducing eccentric pneumatic layout device can change the flying mechanical environment around the product, reduce the contribution of the lengthened cabin to the overturning moment under the supersonic speed condition, control the aerodynamic force on the tested product, and realize the accurate control of the flying attitude of the product with small rotational inertia through numerical simulation calculation and test verification;
2. the ingenious design of the reducing and eccentric structures in the invention ensures that the airflow at the tail part of the lengthened cabin is smoother, prevents the high-speed airflow from being blocked at the tail part, further reduces the local high-pressure area at the tail part of the tested product, indirectly reduces the negative moment, and simultaneously effectively reduces the pneumatic disturbance at the separation moment of the elastic sledge;
3. the whole structure of the device is made of aluminum materials, and the device is matched with the cushion pad for use, so that the mechanical collision between the device and a product under the inertia action at the moment that a tested product attacks a target is avoided, and the target attack angle and the target penetration effect of the product are not influenced;
4. the device has simple structure, is easy to assemble with a product and operate, and ensures that the product does not deviate vertically or horizontally during the high-speed sliding of the rocket sled on the rail.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a structural cross-sectional view of the present invention;
FIG. 3 is a rear view of the structure of the present invention;
FIG. 4 is a view of the adapter ring structure of the present invention;
FIG. 5 is a view of the cushion of the present invention;
FIG. 6 is a structural view of the enclosure of the present invention;
FIG. 7 is a schematic view of the configuration of a dual track rocket sled of a type installed using the present invention.
In the figure, 1-adapter ring; 2-a buffer pad; 3-a cabin body; 4-reinforcing ribs; 5-opening; 6-closing the opening; 7-a boss; 8-a cushion filling zone; 9-a chassis; 10-a front pillar; 11-rear upright; 12-an engine; 13-product; 14-diameter reducing eccentric pneumatic layout device; 15-front snap ring; 16-rear snap ring; 17-a rear baffle.
Detailed Description
The present invention will be further described with reference to the following drawings and examples, which include, but are not limited to, the following examples.
The invention provides a 'reducing eccentric' pneumatic adjusting device for a lengthened cabin, which is characterized in that firstly, the lengthened cabin is subjected to 'reducing' treatment, the stress area and the lift force at the position are reduced, and therefore the negative moment is reduced by about 45%; and secondly, the lengthened cabin is subjected to 'eccentricity' treatment, namely the cabin body is not coincident with the axis of the product, and meanwhile, the attitude of the lengthened cabin is adjusted to 0 degree, so that the airflow at the tail part of the lengthened cabin is smoother, the airflow blockage is prevented, the negative moment is indirectly reduced, and through attack angle calculation and test verification, the device can realize favorable control of the flight attitude of the product after the product is separated by the elastic sledge, and provides a reference basis for attack angle control of similar rocket sledge test products.
For convenience of description, the system composed of the product, the pneumatic layout device and the clamping ring is called a tested product system.
The invention relates to a reducing eccentric pneumatic layout device which is used as an auxiliary structure for controlling the attack angle of a product and is arranged at the tail part of the product. The adapter ring is a bearing structure of a product and a cabin body, an opening of the adapter ring is connected with the product in a threaded mode, the adapter ring is used for limiting the height of the product in the vertical direction, a closing opening is welded with a port of the cabin body, the cabin body is of a cylindrical structure with an opening at one end and a sealing at one end, the tail part and the rear snap ring are installed on the rocket sled body in a tight fit mode, trapezoidal reinforcing ribs are evenly distributed on the end face of the cabin body, the connecting strength between the adapter ring and the cabin body is increased, and the structural safety of the cabin body in high-speed operation is guaranteed.
The invention is realized in that: the adapter ring is the aluminum product, guarantee coaxial with the product, be the same with product installation angle promptly, it is fixed according to bullet sledge separation boundary carries out attack angle emulation calculation specifically to preset installation angle, the internal diameter is unanimous with the product external diameter, radial wall thickness is 12.5mm, the wall thickness of closing in the mouth is 30mm, opening part design internal thread, thread form and quantity keep unanimous with the product external screw thread, thread department card is dead when preventing the assembly, need evenly paint lubricating oil in thread department before the assembly, the adapter ring inner wall sets up high 4 mm's boss structure, be used for preventing that the product from taking place the course displacement, the screw is screwed and is guaranteed more than 50mm with the adapter ring reservation space behind the boss reality, as blotter filling area.
The invention is realized in that: the cabin body is made of aluminum materials, the model is 2A12, the cabin body is instantly disintegrated at the moment of penetrating a target of a product, the target entering posture and the penetrating efficiency of the product are not affected, the cabin body is subjected to a hole reducing eccentric design (the outer diameter of the cabin body is 2/3 of the outer diameter of the adapter ring), the wall thickness is 20mm, the length is 3.5 times of the outer diameter of the cabin body, the cabin body is parallel to the running direction of the rocket sled, namely, the cabin body is horizontally arranged at 0 degree, the distance between the cabin body and the upper edge of the adapter ring is 1/8 of the outer diameter of the adapter ring, a smooth airflow channel is provided between the cabin body and the stand column, the opening end face is flush with the inner surface of the closing port of the adapter ring, the sealing end of the cabin body is radially installed together with the special clamping ring for the rocket sled test in a fastening mode, the axial direction is tightly attached to a rear baffle of the rocket sled body, and the cabin body is prevented from vertically moving and jumping in the course of the high-speed running of the rocket body.
The invention is realized in that: according to different requirements of product shapes and interfaces, the structural sizes of the cabin and the adapter ring can be adaptively modified in order to facilitate installation and fixation on the rocket sled body.
The invention is realized in that: the connecting ring and the cabin body are fixed in a welding mode, the cabin body is subjected to reducing treatment in order to reduce the lifting force value borne by the cabin body, the cabin body is still subjected to pneumatic lifting force of thousands of newtons or even tens of thousands of newtons, the prying body slides for several seconds before the elastic prying body is separated, and the cabin body has larger moment around the root in the process, so that the cabin body is easy to bend or break, the test failure is influenced, and the welding part needs to be fully welded.
The invention is realized in that: the strengthening rib is the aluminum product, at adapter ring leeward side evenly install 6 trapezoidal strengthening ribs for resist the moment of above-mentioned analysis.
The invention is realized in that: the cushion pad is made of rubber materials and is in a round cake shape, the diameter size is determined according to the cross section shape of the tail of a specific product, and the thickness is based on the residual space filled with the adapter ring, so that the cushion pad is used for isolating the high-frequency vibration of the cabin body under the high-speed operation of the rocket sled test and simultaneously buffering the strong impact force of the cabin body under the action of inertia when impacting a target.
The diameter-reducing eccentric pneumatic layout device is arranged at the tail of a product, can change the layout of a flow field around the product, and achieves the aim of controlling the attack angle of the product with small rotational inertia.
At a certain product supersonic velocityIn the end-point effect double-track rocket sled test (see figure 7), the product mass is 130kg, and the rotational inertia is 70 kg.m2The test system is assembled with the pneumatic layout device to form a tested product system, products in the tested product system are installed on a front upright post of the sledge body through a front clamping ring at a preset attack angle of 3 degrees, the cabin body is horizontally installed on a rear upright post of the sledge body through a rear clamping ring, a double-rail whole sledge structure is used, and 4 engines are installed on the rear portion of the sledge body. The method comprises the steps that 4 engines are statically ignited at a launching point during testing, a rocket sled reaches the maximum speed of 800m/s, the rocket sled and a tested article are separated through a bullet sled separation system after sliding for a certain distance, the tested article is independently targeted at the speed of 790m/s, the target attack angle is observed and judged to be 4.5 degrees through high-speed video equipment, the pneumatic layout device is instantly disassembled when the tested article impacts a target within the range of 4-6 degrees of the target attack angle required by the technical indexes of the testing, the product penetrates through multiple layers of targets, the structure of the product is complete after the product is discharged, and data collected after the testing shows that the purposes of battle assessment such as product structure strength, charge stability and the like are achieved.
By applying the method, the accurate control of the target attack angle of the small-moment inertia product under the high-speed dynamic condition of the supersonic double-track rocket sled is ensured, and reliable technical support is provided for the ground examination of the product.
Claims (8)
1. A reducing eccentric device suitable for posture adjustment of a small-rotational-inertia product comprises a switching ring, a cabin body and a buffer pad, and is characterized in that the cabin body is of a columnar structure, the rear end of the cabin body is fixedly connected with a rocket sled body, and the axis direction is parallel to the running direction of the rocket sled; one end of the adapter ring is fixedly connected with the front end of the cabin body, the other end of the adapter ring is provided with an opening, and the tail of the tested object is coaxially and fixedly connected in the opening of the adapter ring; a cushion pad is filled between the rear end face of the tested object and the bottom of the inner cavity of the adapter ring; the outer diameter of the cabin body is smaller than that of the adapter ring, and the distance between the upper edge of the cabin body and the upper edge of the adapter ring is smaller than that between the lower edge of the cabin body and the lower edge of the adapter ring.
2. The reducing eccentric device suitable for adjusting the posture of a product with small rotational inertia according to claim 1, wherein a plurality of reinforcing ribs are arranged between the cabin and the adapter ring.
3. The eccentric, diameter-reducing device of claim 1, wherein the outer diameter of the chamber is 2/3 times the outer diameter of the adaptor ring, the chamber has a length 3.5 times the outer diameter of the chamber, and the distance between the chamber and the upper edge of the adaptor ring is 1/8 times the outer diameter of the adaptor ring.
4. A diameter-reducing eccentric device suitable for adjusting the posture of a product with small rotational inertia as claimed in claim 1, wherein the cabin body is of a cylindrical structure with an opening at one end and a sealing at one end, the cabin body is made of aluminum material, the model is 2a12, and the wall thickness is 20 mm.
5. A diameter-reducing eccentric device suitable for attitude adjustment of small rotational inertia products as claimed in claim 1, wherein the tail of the cabin body is tightly fitted with the rear snap ring and mounted on the rocket sled body, and is axially attached to the rear baffle of the rocket sled body.
6. A diameter reducing eccentric device suitable for adjusting the posture of a small rotational inertia product as claimed in claim 1, wherein the adapter ring is made of aluminum, the inner cavity is a stepped hole, the inner diameter of the rear end is smaller than that of the front end, and the wall thickness of the end face of the rear end is 30 mm.
7. The reducing eccentric device suitable for adjusting the posture of a product with small rotational inertia according to claim 1, wherein an opening of the adapter ring is connected with the product in a threaded manner, and the adapter ring is fixedly connected with the cabin body through welding.
8. A reducing eccentric device suitable for adjusting the attitude of a small moment of inertia product as claimed in claim 1, wherein the cushion is made of rubber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121500232.5U CN215413432U (en) | 2021-07-03 | 2021-07-03 | Reducing eccentric device suitable for small-moment inertia product posture adjustment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121500232.5U CN215413432U (en) | 2021-07-03 | 2021-07-03 | Reducing eccentric device suitable for small-moment inertia product posture adjustment |
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| Publication Number | Publication Date |
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| CN215413432U true CN215413432U (en) | 2022-01-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121500232.5U Active CN215413432U (en) | 2021-07-03 | 2021-07-03 | Reducing eccentric device suitable for small-moment inertia product posture adjustment |
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| CN (1) | CN215413432U (en) |
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2021
- 2021-07-03 CN CN202121500232.5U patent/CN215413432U/en active Active
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