A pneumatic structure of a test specimen support frame for a 3.5Ma double-track rocket sled

Abstract

The present invention discloses a pneumatic structure of a test object support frame for a 3.5Ma double-track rocket sled, including a front rectifier, an inner sealing plate, an outer sealing plate, an internal reinforcing rib and a rear support; the inner sealing plate and the outer sealing plate are arranged in parallel, and the inner sealing plate and the outer sealing plate are connected by reinforcing ribs; the front rectifier is welded between the inner sealing plate and the outer sealing plate at the front of the pneumatic structure of the support frame, and forms a 30° wedge structure with the inner sealing plate; the rear support is a pentagonal prism structure formed by splicing five steel plates, the inner sealing plate and the outer sealing plate are welded at the front, and the inner tail of the rear support is designed with a chamfer to increase the internal airflow channel area and reduce resistance. The present invention can provide suitable aerodynamic pressure under the condition of small aerodynamic resistance, improve the on-track operating environment of the sled, and can provide sufficient lateral support strength to ensure the reliability of lateral fixation of the test object.

Description

Technical Field

[0001] The invention belongs to the technical field of shooting range testing, and in particular relates to a pneumatic structure of a test object support frame. Background Art

[0002] The rocket sled is a ground test system that uses rocket engines as power and slides at high speed along a specially built slide rail. It mainly simulates the speed and acceleration conditions in the development process of weapon systems and is used for the functional assessment of missiles, aircraft, aerospace vehicles, etc. As my country's weapon systems develop towards high speed and intelligence, the requirements for the terminal speed of weapon systems are getting higher and higher. As a special weapon system test method, the rocket sled test is basically not limited by the volume and weight of the test piece. From full-size aircraft or missile parts (except large transport aircraft, bombers and large missiles) to small components such as electrical appliances, they can all be tested through the rocket sled.

[0003] Among all kinds of rocket sled tests, warhead terminal effect type rocket sled test is one of the important types. This type of test requires that the test object is fixed on the sled during the operation of the sled. When it reaches the end point, the test object and the sled are unfixed, and the test object penetrates the target alone. The fixation of the test object on the sled is mainly divided into three directions: vertical, lateral and heading. When there is reliable fixation in all three directions, the test object is reliably and completely fixed on the sled. Among them, the vertical and heading fixation of the test object is directly transmitted to the sled by the column structure, and the lateral fixation is borne by the support frame of the test object. A stable support frame plays a decisive role in the reliable fixation of the test object.

[0004] As weapons and equipment develop towards high speed, the terminal speed of rocket sled tests is getting higher and higher. In some warhead rocket sled tests, the warhead mass is large (more than 1000kg) and the terminal speed is high (more than 3.5Ma). Under such conditions, the overload and aerodynamic force on the test object will increase sharply. The traditional double-track rocket sled test object support structure can no longer meet the requirements. Therefore, a new support structure is needed to ensure that during the operation of the sled, it can meet both the fixed requirements of the test object and the overall aerodynamic environment requirements.

[0005] During the high-speed operation of the rocket sled on the track, the aerodynamic drag is mainly generated by the windward surface products of the sled and the test object. As the main structure for fixing the test object, the support structure will inevitably have a certain windward area, generating aerodynamic drag and lift. Its aerodynamic drag and lift will have a certain impact on the operating environment of the sled. Among them, the aerodynamic drag affects the running speed of the entire sled, and the aerodynamic lift will have a certain impact on the vibration overload. Reducing aerodynamic drag, increasing the thrust-to-drag ratio, and improving the on-orbit running speed of the rocket sled and the utilization rate of the rocket engine, the rocket sled always maintains pressure on the track during operation, which is more conducive to smooth operation. Therefore, based on the currently used rocket engine and double-track rocket sled, it is necessary to design a low-drag, negative-lift, and sufficient-strength-and-rigidity support frame aerodynamic structure for the double-track rocket sled test object support requirements and its aerodynamic environment to meet the test requirements of large-mass test objects and 3.5Ma rocket sleds. Summary of the invention

[0006] In order to overcome the shortcomings of the prior art, the present invention provides a test article support frame aerodynamic structure for a 3.5Ma double-track rocket sled, including a front fairing, an inner sealing plate, an outer sealing plate, an internal reinforcing rib and a rear support; the inner sealing plate and

[0007] The outer sealing plates are arranged in parallel, and the inner sealing plates and the outer sealing plates are connected by reinforcing ribs; the front rectifier is welded between the inner sealing plates and the outer sealing plates at the front of the support frame pneumatic structure, forming a 30° wedge structure with the inner sealing plate; the rear support is a pentagonal column structure composed of five steel plates, with the inner sealing plates and the outer sealing plates welded at the front, and an inverted rear end of the rear support is designed.

[0008] The angle is used to increase the internal airflow channel area and reduce resistance. The present invention can provide appropriate aerodynamic pressure under the condition of small aerodynamic resistance, improve the on-track running environment of the skid, and provide sufficient lateral support strength to ensure that the skid is

[0009] Reliability of lateral fixation of the specimen.

[0010] The technical solution adopted by the present invention to solve the technical problem is as follows:

[0011] An aerodynamic structure of a test article support frame for a 3.5Ma double-track rocket sled, comprising a front fairing, an inner sealing plate, an outer sealing plate, an inner reinforcing rib and a rear support;

[0012] 5 The inner sealing plate and the outer sealing plate are arranged in parallel, and the inner sealing plate and the outer sealing plate are connected by reinforcing ribs to improve the overall

[0013] Stiffness;

[0014] The front rectifier is welded between the inner sealing plate and the outer sealing plate at the front of the support frame aerodynamic structure, and forms a 30° wedge structure with the inner sealing plate to reduce the aerodynamic resistance of the structure;

[0015] The front of the inner sealing plate is welded with a front rectifier, and the rear side is connected to the rear support. The inner sealing plate expands outward at an angle of 8° to the running direction of the skid body to compensate for the reduction in channel area caused by the rectifier structure of the skid body, so that the airflow is not congested;

[0016] The front of the outer sealing plate is welded with a front rectifier, and the rear side is connected to the rear support. The outer sealing plate expands outward at an angle of 8° with the running direction of the skid body, and is used to generate downward and inward pneumatic pressure to make the running environment of the skid body more stable;

[0017] The rear support is a pentagonal column structure made of five steel plates, with an inner sealing plate and an outer sealing plate welded at the front.

[0018] The inner tail of the support is designed with a chamfer to increase the internal airflow channel area and reduce resistance;

[0019] 5 When installing the pneumatic structure of the support frame, first weld the rear support, inner sealing plate, and internal reinforcement together, and then

[0020] Weld the outer cover plate and the front rectifier, and finally place the whole unit in the designed position of the skid. The upper part is welded to the column of the test product, and the lower part is welded to the chassis of the skid.

[0021] Preferably, the front fairing, outer sealing plate, inner sealing plate and internal reinforcing ribs are all made of BS 960 steel plates with a thickness of 4 mm.

[0022] Preferably, the rear support is made of BS 960 steel plate with a thickness of 6 mm.

[0023] Preferably, the chamfer designed for the inner tail of the rear support is a 50×20 chamfer.

[0024] The beneficial effects of the present invention are as follows:

[0025] 1. The pneumatic structure of the test object support frame designed in the present invention can provide appropriate pneumatic pressure under the condition of small pneumatic resistance, thereby improving the on-track operating environment of the sled.

[0026] 2. The pneumatic structure of the test object support frame designed in the present invention can provide sufficient lateral support strength to ensure the reliability of lateral fixation of the test object. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 It is a schematic diagram of the pneumatic structure of the support frame of the present invention.

[0028] Figure 2It is a schematic diagram of the support frame aerodynamic structure of the present invention after removing the front fairing and outer sealing plate.

[0029] Figure 3 It is a schematic diagram of the installation of the aerodynamic structure of a support frame of a 3.5Ma double-track rocket sled test product according to an embodiment of the present invention.

[0030] Among them: 1-front fairing; 2-external sealing plate; 3-rear support; 3-inner sealing plate; 5-internal reinforcement ribs. DETAILED DESCRIPTION

[0031] The present invention is further described below in conjunction with the accompanying drawings and embodiments.

[0032] The purpose of the present invention is to construct an aerodynamic structure of a test article support frame suitable for the test conditions of a 3.5Ma high-speed double-track rocket sled. The structure can provide stable lateral support for the test article without generating excessive aerodynamic resistance, and provide a certain aerodynamic downforce, thereby optimizing the operating environment of the sled body and enabling the sled body to run smoothly to the end point at a specified speed.

[0033] The present invention is described in detail below:

[0034] like Figure 1 and Figure 2 As shown, the present invention is an aerodynamic structure of a test article support frame, which is used in a warhead terminal effect type rocket sled test to provide reliable lateral support for the test article in the lateral direction. Its external structure has been specially aerodynamically designed, and has small air resistance and appropriate aerodynamic downforce during the high-speed operation of the sled.

[0035] The present invention is realized in that: the pneumatic structure of the test object support frame is supported on both sides of the front clamping column of the test object, connecting the upper end of the column and the chassis of the sled body, and transmitting the lateral force of the test object from the upper end of the column to the chassis, so that the test object does not move in the horizontal direction. The pneumatic structure of the support frame is composed of front rectification, inner and outer sealing plates, internal reinforcement ribs, and rear support. The front rectification can reduce air resistance; the inner and outer sealing plates are parallel to each other and expand outward at an angle of 8° with the heading of the sled body. When the airflow enters the channel composed of the sled body, the column of the test object, and the pneumatic structure of the support frame, it will not cause airflow congestion and increase air resistance due to the narrowing of the channel area. The outer sealing plate will generate a certain inward and downward pneumatic pressure to optimize the operating environment of the sled body; the internal reinforcement ribs are used to connect the inner and outer sealing plates to improve the overall rigidity; the rear support is the main load-bearing structure of the pneumatic structure of the support frame, and there is an outward-expanding inclined plate on the inside, which is also used to expand the airflow channel area, reduce the rear negative pressure area, and thus reduce air resistance.

[0036] The present invention is also realized in that the front fairing is a BS 960 steel plate with a thickness of 4 mm, which is welded to the front of the support structure and forms a 30° wedge structure with the inner sealing plate, in order to reduce the aerodynamic resistance of the entire structure.

[0037] The present invention is also achieved in that: the inner sealing plate is a BS 960 steel plate with a thickness of 4 mm, a front rectification is welded on the front, and the rear side is connected to the rear support. The inner sealing plate expands outward at an angle of 8° with the running direction of the skid body to compensate for the reduction in channel area caused by the skid body rectification structure, so that the airflow is not congested.

[0038] The present invention is also achieved in that: the outer sealing plate is a BS 960 steel plate with a thickness of 4 mm, a front rectifier is welded on the front, and the rear side is connected to the rear support. The outer sealing plate expands outward at an angle of 8° with the running direction of the skid body to generate downward and inward pneumatic pressure, so that the running environment of the skid body is more stable.

[0039] The present invention is also realized in that: the internal reinforcing ribs are BS 960 steel plates with a thickness of 4 mm, which are welded between the inner and outer sealing plates to improve the overall rigidity.

[0040] The present invention is also realized in that: the rear support is the main structure for bearing the lateral overload of the test object, and is composed of five BS 960 steel plates with a thickness of 6mm, which are spliced ​​into a pentagonal prism structure, and the inner and outer sealing plates are welded at the front. The inner tail of the rear support is designed with a 50×20 chamfer to increase the internal airflow channel area and reduce resistance.

[0041] The present invention is also implemented in that: when the pneumatic structure of the test object support frame is installed, the rear support, the inner sealing plate, and the internal reinforcement ribs are first welded together, and then the outer sealing plate and the front rectifier are welded, and finally the whole is placed in the designed position of the sled body, the upper part is welded to the test object column, and the lower part is welded to the chassis of the sled body. Specific embodiment:

[0043] Figure 3 It is a 3.5Ma terminal effect rocket sled test platform with a ton-class warhead, which mainly tests the structural strength and penetration capability of the ignition system. The aerodynamic structure of the test object support frame is installed at the front of the sled, on both sides of the front column of the test object, with the upper part connected to the upper end of the column and the lower part connected to the chassis of the sled, so that the lateral force of the test object is transmitted from the upper end of the column to the chassis, so that the test object does not move in the horizontal direction; and because the inner sealing plate has an 8° angle outward, it can avoid the airflow channel surrounded by the column, support structure, and sled rectification due to the sled rectification to form a "large in front and small in the back" structure, causing airflow congestion and increasing air resistance.

[0044] During the test, the rocket engine is ignited at the launch point, and the sled moves forward under the thrust of the engine until it reaches a predetermined speed at the end point. The dynamic power-on system on the sled cooperates with the ground device to detonate the explosive bolts, thereby releasing the constraints between the sled and the test object, and the test object penetrates the target alone, achieving the test purpose.

Claims

1. A pneumatic structure of a test object support frame for a 3.5Ma double-track rocket sled, characterized in that: It includes front fairing, inner sealing plate, outer sealing plate, internal reinforcement ribs and rear support; The inner sealing plate and the outer sealing plate are arranged in parallel, and the inner sealing plate and the outer sealing plate are connected by reinforcing ribs to improve the overall rigidity; The front rectifier is welded between the inner sealing plate and the outer sealing plate at the front of the support frame aerodynamic structure, and forms a 30° wedge structure with the inner sealing plate to reduce the aerodynamic resistance of the structure; The front of the inner sealing plate is welded with a front rectifier, and the rear side is connected to the rear support. The inner sealing plate expands outward at an angle of 8° with the running direction of the skid body to compensate for the reduction in channel area caused by the rectifier structure of the skid body, so that the airflow is not congested; The front of the outer sealing plate is welded with a front rectifier, and the rear side is connected to the rear support. The outer sealing plate expands outward at an angle of 8° with the running direction of the skid body, and is used to generate downward and inward pneumatic pressure to make the running environment of the skid body more stable; The rear support is a pentagonal column structure formed by five steel plates, with an inner sealing plate and an outer sealing plate welded at the front. The inner tail of the rear support is designed with a chamfer to increase the internal airflow channel area and reduce resistance; When installing the pneumatic structure of the support frame, first weld the rear support, inner sealing plate, and internal reinforcement ribs together, then weld the outer sealing plate and the front rectifier, and finally place the whole in the designed position of the skid, weld the upper part to the column of the test product, and weld the lower part to the chassis of the skid.

2. The pneumatic structure of the test object support frame for a 3.5Ma double-track rocket sled according to claim 1 is characterized in that: The front fairing, outer sealing plate, inner sealing plate and internal reinforcement ribs are all made of BS 960 steel plates.

3. The pneumatic structure of the test object support frame for a 3.5Ma double-track rocket sled according to claim 1 is characterized in that: The thickness of the front fairing, outer sealing plate, inner sealing plate and internal reinforcing ribs are all 4 mm.

4. The pneumatic structure of the test object support frame for a 3.5Ma double-track rocket sled according to claim 1 is characterized in that: The rear support is made of BS 960 steel plate.

5. The pneumatic structure of the test object support frame for a 3.5Ma double-track rocket sled according to claim 1 is characterized in that: The thickness of the rear support is 6 mm.

6. The pneumatic structure of the test object support frame for a 3.5Ma double-track rocket sled according to claim 1 is characterized in that: The chamfer designed at the inner tail of the rear support is a 50×20 chamfer.

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