Aerodynamic shape structure of a product sled of a hypersonic monorail rocket sled

Abstract

The present invention discloses an aerodynamic shape structure of a product sled of a hypersonic monorail rocket sled, which comprises a drag reduction rod, a fairing, a cabin section and a transition section from front to back; the drag reduction rod can slow down the incoming flow speed and reduce the aerodynamic resistance of the system; the fairing can reduce the aerodynamic resistance and increase the downforce; the cabin section can realize the continuity and smoothness of the system profile, while reducing the aerodynamic resistance and increasing the downforce; the transition section is used to transmit the thrust of the thrust sled to the product sled carrying the test product, while realizing the continuity and smoothness of the system profile, further reducing the aerodynamic resistance. The present invention greatly reduces the structural weight and aerodynamic resistance of the rocket sled system, and can realize the hypersonic ground test in the most economical way.

Description

Technical Field

[0001] The invention belongs to the technical field of shooting range testing, and in particular relates to an aerodynamic shape structure of a product skid. Background Art

[0002] Hypersonic technology is the new commanding height of future aerospace technology. It is strategic, forward-looking, iconic and driving. At present, hypersonic weapons have become the focus of weapon equipment development of major military powers. To achieve the leap from supersonic speed to hypersonic speed (≥5Ma), strong support from test and testing technology is needed. The hypersonic rocket sled test relies on a special ground slide rail. Through the acceleration of a multi-stage power system, the tested product is accelerated along the high-precision slide rail to more than 5Ma, and related functions, performance evaluations and assessments such as aerodynamic characteristics, thermal ablation, structural response, and collision damage are carried out.

[0003] In the field of hypersonic rocket sled test technology, my country's rocket sleds currently usually adopt a layout mode of test object + mounting clamp + sled truss + sliding shoe, which is mainly used in subsonic, transonic and supersonic tests. However, for hypersonic tests, due to the large aerodynamic resistance and overall mass of the sled, the rocket sled system cannot be pushed to the specified speed based on the existing engine thrust conditions. Therefore, it is urgent to develop a monorail rocket sled aerodynamic shape that can be suitable for hypersonic rocket sled tests. Summary of the invention

[0004] In order to overcome the deficiencies of the prior art, the present invention provides an aerodynamic shape structure of a product sled of a hypersonic monorail rocket sled, which includes, from front to back, a drag reduction rod, a fairing, a cabin section, and a transition section; the drag reduction rod can slow down the incoming flow speed and reduce the aerodynamic drag of the system; the fairing can reduce the aerodynamic drag and increase the downforce; the cabin section can achieve a continuous and smooth system profile, while reducing the aerodynamic drag and increasing the downforce; the transition section is to transmit the thrust of the thrust sled to the product sled carrying the test product, while achieving a continuous and smooth system profile, further reducing the aerodynamic drag. The present invention greatly reduces the structural weight and aerodynamic drag of the rocket sled system, and can most economically achieve hypersonic ground testing.

[0005] The technical solution adopted by the present invention to solve the technical problem is as follows:

[0006] A product sled aerodynamic shape structure of a hypersonic monorail rocket sled, comprising a drag reduction rod, a fairing, a cabin section and a transition section; the cabin section is an outer cabin section of a test object, and the transition section is a transition section between the tail of the outer cabin section of the test object and the thrust sled;

[0007] The aerodynamic shape structure is composed of a drag reduction rod, a fairing, a cabin section and a transition section from front to back;

[0008] The fairing adopts a streamlined design, consisting of an upper semi-conical shape and a lower V-shape; the angle between the semi-conical generatrix and the axis is 15° to 30°; the angle between the V-shaped shape and the axis is 2° to 20°; it is used to reduce aerodynamic drag and increase downforce;

[0009] The drag reduction rod is a variable diameter cylindrical rod, which is arranged at the intersection of the semi-conical and V-shaped sections of the fairing, placed above the V-shaped section, and smoothly transitions with the semi-conical section, thereby reducing the aerodynamic drag and aerodynamic heating of the fairing;

[0010] The cabin section is composed of a variable-section cylinder and a V-shaped oblique drape; the variable-section cylinder wraps the test object and has a rectifying effect. The upper semicircle of the variable-section cylinder adopts a variable-section design, and the angle between the upper semicircle generatrix and the horizontal plane is 2° to 5°, which increases the downward pressure of the cabin section, and the lower semicircle generatrix is ​​parallel to the horizontal plane; the angle between the V-shaped oblique drape and the axis is 2° to 10°, which has the effect of guiding and preventing deflection;

[0011] The transition piece is a variable diameter cylindrical shape, the front outer diameter is consistent with the tail circle of the cabin section, the center of the circle coincides, and the rear outer diameter is consistent with the front end circle diameter of the engine installed on the thrust skid, the center of the circle coincides, so that the airflow flows evenly;

[0012] The drag reduction rod, fairing, cabin section and transition section are all arranged concentrically, that is, the axes are on the same horizontal straight line, so that the mass of the product skid and the aerodynamic external load are symmetrical along the lateral neutral plane.

[0013] Preferably, the drag reduction rod is a variable diameter cylindrical type with a diameter between 30 and 100 mm and a length of 400 mm.

[0014] The beneficial effects of the present invention are as follows:

[0015] (1) The present invention proposes for the first time a monorail rocket sled product sled aerodynamic shape with a smooth and continuous aerodynamic shape and excellent aerodynamic characteristics. It can realize the rocket sled test of hypersonic missile-type test products under the existing engine thrust conditions and break through the functional assessment of 5Ma missile-type weapon systems.

[0016] (2) The aerodynamic shape of the monorail rocket sled product sled of the present invention realizes an integrated design with the test product, breaks through the traditional truss structure sled configuration, and proposes a streamlined aerodynamic shape of the product sled for the first time, which greatly reduces the structural weight and aerodynamic resistance of the rocket sled system, and can realize hypersonic ground testing in the most economical way.

[0017] (3) The present invention designs a transition section between the rear end face of the test article and the front end face of the engine of the thrust sled, and rectifies the airflow between the two stages of the sleds, so that the streamlines here smoothly and evenly transition to the thrust sled, avoiding the generation of aerodynamic separation vortices and greatly reducing the aerodynamic resistance of the system.

[0018] (4) Compared with the traditional monorail rocket sled, the present invention significantly improves the running stability of the sled. Through the coaxial design of different components, the mass of the entire sled can be guaranteed to be symmetrical along the lateral neutral plane, reducing the unbalanced sled force and shoe wear caused by mass eccentricity; at the same time, the symmetry of the aerodynamic external load along the lateral neutral plane is also achieved, reducing the possibility of aerodynamic eccentricity of the sled, and ensuring the safety and reliability of the test. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a schematic diagram of a rocket sled test platform that combines the aerodynamic shape structure of the product sled of the present invention with a thrust sled.

[0020] Figure 2 It is a schematic diagram of the pneumatic structure of the product skid of the present invention.

[0021] Figure 3 It is a schematic diagram of the appearance of the fairing of the present invention.

[0022] Figure 4 It is a schematic diagram of the appearance of the drag reduction rod of the present invention.

[0023] Figure 5 It is a schematic diagram of the cabin section appearance of the present invention.

[0024] Figure 6 It is a schematic diagram of the appearance of the transition section of the present invention.

[0025] Among them: 1 - product skid; 2 - thrust skid, 3 - drag reduction rod, 4 - fairing, 5 - cabin section, 6 - transition section. DETAILED DESCRIPTION

[0026] The present invention is further described below in conjunction with the accompanying drawings and embodiments.

[0027] The present invention aims to solve the problem that the existing rocket sled aerodynamic shape in the existing rocket sled test technology cannot carry out hypersonic rocket sled tests, and proposes an aerodynamic shape of a monorail rocket sled product sled suitable for hypersonic speed. The aerodynamic shape of the rocket sled product sled of the present invention has the advantages of excellent aerodynamic characteristics, high thrust-to-weight ratio, high stability, etc.

[0028] The present invention is described in detail below:

[0029] The present invention is a hypersonic monorail rocket sled product sled aerodynamic shape, mainly including drag reduction rods, fairings, test product outer cabin section (hereinafter referred to as cabin section), and transition section between the tail of the test product outer cabin section and the thrust sled (hereinafter referred to as transition section). The drag reduction rod can slow down the incoming flow speed and reduce the aerodynamic resistance of the system; the fairing can reduce the aerodynamic resistance and increase the downforce; the cabin section can achieve a continuous and smooth system profile, while reducing the aerodynamic resistance and increasing the downforce; the transition section is to transmit the thrust of the thrust sled to the product sled carrying the test product, and at the same time can achieve a continuous and smooth system profile, further reducing the aerodynamic resistance.

[0030] The present invention is realized in that the fairing adopts a streamlined design, which is composed of an upper semi-conical shape and a lower V-shape. The angle between the conical generatrix and the axis is 15° to 30° (the angle is determined by the shape of the test object and the required downforce), and the semi-conical shape has the function of guiding flow and providing downforce. The angle between the V-shaped shape and the axis is 2° to 20° (the angle is determined by the shape of the test object), which has the function of guiding flow and preventing deflection, can reduce aerodynamic resistance, and ensure operational stability.

[0031] The present invention is realized in that: the drag reduction rod is a variable diameter cylinder with a diameter of 30 to 100 mm and a length of about 400 mm. It is arranged at the intersection of the semi-conical and V-shaped sections of the fairing, placed above the V-shaped section, and smoothly transitions with the semi-conical section. In a near-ground environment with dense gas and high Reynolds number, it has the effect of reducing the aerodynamic resistance and aerodynamic heating of the fairing.

[0032] The present invention is realized in that the cabin section is composed of a variable-section cylinder and a V-shaped oblique drape. The variable-section cylinder wraps the test object and has a rectifying effect. The upper semicircle of the variable-section cylinder adopts a variable-section design. The angle between the upper semicircle generatrix and the horizontal plane is 2° to 5°, which increases the downforce of the cabin section. The lower semicircle generatrix is ​​parallel to the horizontal plane. The angle between the V-shaped oblique drape and the axis is 2° to 10°, which has the effect of guiding and preventing deflection. At the same time, it can improve the aerodynamic environment around the thrust sled, reduce the aerodynamic resistance of the thrust sled and prevent the generation of aerodynamic separation vortices.

[0033] The implementation of the present invention lies in that: the transition piece has a variable diameter cylindrical shape, the front outer diameter is consistent with the tail circle of the cabin section, the center of the circle coincides, and the rear outer diameter is consistent with the front end circle diameter of the engine installed on the thrust sled, the center of the circle coincides. This shape allows the airflow to flow evenly, no aerodynamic separation vortex is generated, and the aerodynamic resistance is small.

[0034] The present invention is realized in that different components such as the drag reduction rod, the fairing, the cabin section, the test product and the transition section are all arranged concentrically (the axes are on the same horizontal straight line), which can ensure that the mass of the entire skid and the aerodynamic external load are symmetrical along the lateral neutral plane, and the system operation stability is high. Specific embodiment:

[0036] The warhead structure is cone + cylinder, with a total length of 1100mm, an outer diameter of the cone bottom of 350mm, and equal diameters of the cylindrical section and the cone bottom. The test cruise speed of the missile rocket sled is required to be 5Ma. According to the structural form of the test product, the aerodynamic shape of the product sled is designed, and the aerodynamic shape of the hypersonic monorail rocket sled product sled of the present invention is applied to the aerodynamic shape design of the product sled of this project.

[0037] The product skid designed for this test project includes fairing, drag reduction rod, cabin section, test product and transition section. There are no other skid components, nor are there structures such as clamps and bolts used to install the test product on the traditional product skid. The aerodynamic shape is simple, avoiding the increase of aerodynamic drag and aerodynamic ablation caused by the protruding structure of the leading edge such as the clamp, and fully integrating the better aerodynamic shape of the hypersonic test product, achieving the advantages of low aerodynamic drag and light weight of the aerodynamic shape of the hypersonic monorail rocket sled product skid.

[0038] According to the aerodynamic shape of the test product, the product skid length is 1600mm, the fairing length is 450mm, the diameter is 270mm, the angle between the upper semicircle generatrix and the horizontal plane is 22.5°, and the angle between the V-shaped shape and the axis is 14.6°; the drag reduction rod length is 395mm, the leading edge diameter is 30mm, and the trailing edge diameter is 72mm; the cabin section length is 770mm, the diameter is 350mm, the angle between the upper semicircle generatrix and the horizontal plane is 5.2°, and the angle between the V-shaped drape and the axis is 6.8°; the transition piece length is 132mm, the leading edge diameter is 350mm, and the trailing edge diameter is 326mm.

[0039] Table 1 Aerodynamics of rocket sled products in this example (unit: N)

[0040]

[0041] From the simulation results, it can be seen that the present invention meets the requirements of small aerodynamic resistance of the product skid (the aerodynamic resistance of the traditional truss-type product skid is nearly 100 tons at a speed of 5Ma) and the aerodynamic lift is in a state of slight downward pressure. The design scheme is reasonable and reliable, and provides a universal product skid aerodynamic shape design method for future hypersonic rocket sled tests.

Claims

1. A product sled aerodynamic shape structure of a hypersonic monorail rocket sled, characterized in that: It includes a drag reduction rod, a fairing, a cabin section and a transition section; the cabin section is the outer cabin section of the test object, and the transition section is the transition section between the tail of the outer cabin section of the test object and the thrust skid; The aerodynamic shape structure is composed of a drag reduction rod, a fairing, a cabin section and a transition section from front to back; The fairing adopts a streamlined design, consisting of an upper semi-conical shape and a lower V-shape, which is used to reduce aerodynamic resistance and increase downforce; The drag reduction rod is a variable diameter cylindrical rod, which is arranged at the intersection of the semi-conical and V-shaped sections of the fairing, placed above the V-shaped section, and smoothly transitions with the semi-conical section, thereby reducing the aerodynamic drag and aerodynamic heating of the fairing; The cabin section is composed of a variable-section cylinder and a V-shaped oblique drape; the variable-section cylinder wraps the test object and has a rectifying effect. The upper semicircle of the variable-section cylinder adopts a variable-section design, and the angle between the upper semicircle generatrix and the horizontal plane is 2° to 5°, which increases the downward pressure of the cabin section, and the lower semicircle generatrix is ​​parallel to the horizontal plane; the angle between the V-shaped oblique drape and the axis is 2° to 10°, which has the effect of guiding and preventing deflection; The transition piece is a variable diameter cylindrical shape, the front outer diameter is consistent with the tail circle of the cabin section, the center of the circle coincides, and the rear outer diameter is consistent with the front end circle diameter of the engine installed on the thrust skid, the center of the circle coincides, so that the airflow flows evenly; The drag reduction rod, fairing, cabin section and transition section are all arranged concentrically, that is, the axes are on the same horizontal straight line, so that the mass of the product skid and the aerodynamic external load are symmetrical along the lateral neutral plane.

2. The aerodynamic shape structure of the product sled of a hypersonic monorail rocket sled according to claim 1 is characterized in that: The drag reduction rod is a variable diameter cylindrical type.

3. The aerodynamic shape structure of the product sled of a hypersonic monorail rocket sled according to claim 2 is characterized in that: The diameter of the drag reduction rod is between 30 and 100 mm.

4. The aerodynamic shape structure of the product sled of a hypersonic monorail rocket sled according to claim 2 is characterized in that: The length of the drag reduction rod is 400mm.

5. The aerodynamic shape structure of the product sled of a hypersonic monorail rocket sled according to claim 1 is characterized in that: The included angle between the generatrix of the semi-cone and the axis is 15° to 30°.

6. The aerodynamic shape structure of the product sled of a hypersonic monorail rocket sled according to claim 1, characterized in that: The angle between the V-shaped shape and the axis is 2° to 20°.

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