Supersonic speed brake parachute rocket sled test platform

Abstract

The utility model provides a supersonic speed brake parachute rocket sled test platform which mainly solves the problems that in a supersonic speed brake parachute recovery test in an existing scheme, all test indexes are difficult to obtain, the test cost is high, and control is complex. According to the scheme, the supersonic speed brake parachute rocket sled test platform comprises a sled body chassis, a supporting part, a rectification part, a clamping ring supporting structure and a dynamic power-up system. The front end of the sledge body is of a truss structure. A tested warhead is connected with the stand columns through three clamping rings, and a triangular rectifying plate and a dynamic power-up system are designed on the skid body chassis. A truss structure is adopted, the erection height is high, the risk that a parachute canopy is possibly damaged due to interference between a supersonic heavy parachute and a rocket sled track is avoided, through the fusion design of multiple rectification structures, the overall aerodynamic resistance of the rocket sled is reduced, meanwhile, the downward pressure of the rocket sled body is increased, and the vibration quantity value of a tested bullet is greatly reduced.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of military target range test and measurement, and mainly relates to a supersonic deceleration parachute rocket sled test platform. BACKGROUND

[0002] Warhead recovery is an important task in the development of missiles. When the warhead of an intercontinental missile reenters the dense atmosphere at a speed of more than 20 times the speed of sound, the extremely severe aerodynamic heat causes high temperature, high pressure and high hot airflow around the warhead, the stagnation point temperature can reach 8000℃, the stagnation point pressure exceeds 10MPa, and the stagnation point heat flow exceeds 1.67x10 6 J / m 3 .s, and the maximum speed pressure exceeds 5MPa (50atm). Under such conditions, how to ensure that the warhead can withstand the harsh environment without being burned out and can hit the target is one of the key problems in the development of warheads. For a long time, warhead designers and aerodynamic heat experts have always regarded warhead recovery as the best identification of the performance of the end cap, heat shield, antenna window and ablation measuring instrument. In the prior art, the scheme of warhead recovery is to increase the deceleration parachute. The opening speed of the deceleration parachute during supersonic warhead recovery can reach 2Ma-3Ma, and the current performance verification method of the deceleration parachute system is high-altitude drop test and live ammunition flight test; the high-altitude drop test is difficult to meet the speed index requirements of the heavy object test, and the reliability of the supersonic opening parachute system cannot be effectively verified, the live ammunition flight test has high cost, wide flight space, high landing point control requirements and great difficulty in obtaining test data, and therefore a new test platform needs to be developed to carry out performance verification of the supersonic heavy object system. SUMMARY

[0003] In order to overcome the shortcomings of the prior art and solve the problems that in the prior art, various test indexes are difficult to obtain, the test cost is high, and the control is complex in the supersonic deceleration parachute recovery test, the present application provides a supersonic deceleration parachute rocket sled test platform.

[0004] A supersonic deceleration parachute rocket sled test platform, comprising a sled body chassis, a support part, a fairing part, a clasp support structure and a dynamic power supply system; the sled body chassis is a double-track rocket sled; an engine is arranged at the rear end of the sled body chassis in the navigation direction; the support part is arranged at the front end of the sled body chassis in the navigation direction; the support part comprises a first support surface and a second support surface; the first support surface and the second support surface are truss structures; the first support surface and the second support surface are respectively arranged on the two sides of the front direction of the sled body chassis; the included angles of the first support surface and the second support surface with the plane where the sled body chassis is located are the same; the upper chords of the first support surface and the second support surface are provided with the clasp support structure; and the dynamic power supply system is arranged on the sled body chassis.

[0005] Further, the first support surface and the second support surface are both parallel chord trusses; the first support surface and the second support surface each include a first vertical web, a second vertical web and a third vertical web; one side of the second vertical web is the first vertical web, and the other side of the second vertical web is the third vertical web; the bottom surface of the first vertical web of the first support surface and the bottom surface of the first vertical web of the second support surface are provided with a first reinforcing horizontal plate.

[0006] Further, the first vertical web of the first support surface and the first vertical web of the second support surface are provided with a second reinforcing horizontal plate; the first reinforcing horizontal plate is parallel to the second reinforcing horizontal plate; a reinforcing vertical plate is arranged between the first reinforcing horizontal plate and the second reinforcing horizontal plate; the second reinforcing horizontal plate and the reinforcing vertical plate form a T-shaped reinforcing structure.

[0007] Further, the windward surfaces of the first reinforcing horizontal plate, the second reinforcing horizontal plate and the reinforcing vertical plate are respectively provided with inclined surfaces, for reducing the aerodynamic drag of the rocket sled system, improving the thrust-to-weight ratio, and saving power.

[0008] Further, a fairing is arranged between the first support surface and the second support surface; the fairing is an isosceles triangular thick plate; a long strip-shaped recess is arranged at the vertex of the fairing; the reinforcing vertical plate is embedded in the long strip-shaped recess; a first recess and a second recess are respectively arranged at the two bottom corners of the fairing, so that the third vertical web of the first support surface and the third vertical web of the second support surface are respectively embedded in the first recess and the second recess; the included angle between the fairing and the plane on which the sled body chassis is located is 7°; the top surface of the fairing is provided with a fairing inclined surface; the function of the fairing is to reduce the aerodynamic drag of the rocket sled, increase the aerodynamic downforce of the rocket sled, and reduce the vibration value of the rocket sled.

[0009] Further, a recess is arranged on the top surface of the fairing; the top surface of the recess is provided with a detachable cover plate, facilitating the installation of a sled data recorder.

[0010] Further, the clamping ring support structure comprises a first clamping ring, a second clamping ring, a third clamping ring and a full-thread screw rod; the first clamping ring, the second clamping ring and the third clamping ring are all circular ring bodies; the longitudinal section of the first clamping ring, the second clamping ring and the third clamping ring are all isosceles trapezoids; the first clamping ring, the second clamping ring and the third clamping ring are coaxial; the included angle between the bottom and the height of the longitudinal section of the first clamping ring, the included angle between the bottom and the height of the longitudinal section of the second clamping ring and the included angle between the bottom and the height of the longitudinal section of the third clamping ring are all equal. The outer surface of the first clamping ring is provided with a first radial support lug and a second radial support lug; the first radial support lug and the second radial support lug are thin plates; the first radial support lug and the second radial support lug are coplanar; the plane on which the first radial support lug and the second radial support lug are located is coplanar with the axis of the first clamping ring; the outer surface of the second clamping ring is provided with a third radial support lug and a fourth radial support lug; the third radial support lug and the fourth radial support lug are thin plates; the third radial support lug and the fourth radial support lug are coplanar; the plane on which the third radial support lug and the fourth radial support lug are located is coplanar with the axis of the second clamping ring; the outer surface of the third clamping ring is provided with a fifth radial support lug and a sixth radial support lug; the fifth radial support lug and the sixth radial support lug are thin plates; the fifth radial support lug and the sixth radial support lug are coplanar; the plane on which the fifth radial support lug and the sixth radial support lug are located is coplanar with the axis of the third clamping ring; the top surface of the first radial support lug, the second radial support lug, the third radial support lug and the fourth radial support lug is provided with a threaded hole; a bolt is arranged in the threaded hole; the first radial support lug is provided with a first through hole parallel to the axis of the first clamping ring; the second radial support lug is provided with a second through hole parallel to the axis of the first clamping ring; the third radial support lug is provided with a third through hole parallel to the axis of the second clamping ring; the fourth radial support lug is provided with a fourth through hole parallel to the axis of the second clamping ring; a first full-thread screw rod is arranged in the first through hole and the third through hole; a second full-thread screw rod is arranged in the second through hole and the fourth through hole; one end of the first full-thread screw rod is fixedly connected with the bottom surface of the fifth radial support lug; one end of the second full-thread screw rod is fixedly connected with the bottom surface of the sixth radial support lug.

[0011] Further, the largest radius surface of the third clamping ring is the bottom surface; the bottom surface of the third clamping ring is provided with a back baffle; the back baffle is a circular ring-shaped thin plate; the inner ring radius of the back baffle is smaller than the inner ring radius of the bottom surface of the third clamping ring; the bottom surface of the third clamping ring is fixedly connected with the top surface of the back baffle.

[0012] Further, the bottom surface of the back baffle is provided with a test sample support rod; one end of the test sample support rod is fixedly connected with the bottom surface of the back baffle, and the other end of the test sample support rod is fixedly connected with the plane on which the sled bottom plate is located; the number of the test sample support rods is 2.

[0013] Further, the bottom surface of the third vertical web of the first support surface and the third vertical web of the second support surface is provided with a second reinforcing cross plate; a T-shaped reinforcing structure is arranged between the third vertical web of the first support surface and the third vertical web of the second support surface.

[0014] The beneficial effects of the present application are:

[0015] 1.The advantage of the present application lies in that the truss structure design is adopted, the height of the bracket carrying the test warhead can reach 1.8m or above, sufficient space is left for the swing of the parachute rope after the opening of the supersonic heavy parachute, and the risk of damage of the parachute caused by the interference between the supersonic heavy parachute and the rocket sled track is avoided.

[0016] 2.The advantage of the present application lies in that the aerodynamic drag of the rocket sled as a whole is reduced, and the downward pressure of the rocket sled body is increased by the design of the combination of various fairing structures, so that the vibration value at the test warhead is greatly reduced.

[0017] 3.The advantage of the present application lies in that the rocket sled power configuration of the system can accelerate the recovered warhead to 2Ma-3Ma on the ground, can simulate the dynamic pressure environment of 200KPa or above at high altitude, and can meet the examination requirements of the supersonic heavy parachute.

[0018] 4.The advantage of the present application also lies in that through the aerodynamic layout design of the rocket sled system, the rocket sled body can be recovered without damage at 3Ma on the 16km rocket sled track, the rocket sled body can be repeatedly used, and the cost is saved. BRIEF DESCRIPTION OF DRAWINGS

[0019] Figure 1 It is a schematic diagram of a rocket sled test platform.

[0020] Figure 2 It is a schematic diagram of a rocket sled test platform column and column reinforcing structure.

[0021] Figure 3 It is a schematic diagram of the "wedge-shaped" fairing result of the rocket sled test platform.

[0022] Figure 4 It is a schematic diagram of the rear baffle of the rocket sled test platform.

[0023] Figure 5 It is a schematic diagram of the full-wire screw connection of the rocket sled test platform.

[0024] In the figure, 1 is a vertical web, 2 is a T-shaped reinforcing structure, 3 is a snap ring, 4 is a "wedge-shaped" triangular fairing plate, 5 is an X-shaped reinforcing structure, 6 is a limiting block, 7 is a full-wire screw, and 8 is a dynamic power-on system. DETAILED DESCRIPTION

[0025] The scheme adopted by a supersonic deceleration parachute rocket sled test platform is as follows:

[0026] The supersonic deceleration umbrella rocket sled test platform comprises a sled chassis, a support part, a fairing part, a snap ring support structure and a dynamic power supply system; the sled chassis is a double-track rocket sled; an engine is arranged at the rear end of the sled chassis in the navigation direction; the support part is arranged at the front end of the sled chassis in the navigation direction; the support part comprises a first support surface and a second support surface; the first support surface and the second support surface are truss structures; the first support surface and the second support surface are respectively arranged on both sides of the sled chassis in the forward direction; the first support surface and the second support surface have the same angle with the plane where the sled chassis is located; the upper chords of the first support surface and the second support surface are provided with the snap ring support structure; the dynamic power supply system is arranged on the sled chassis;

[0027] The first support surface and the second support surface are parallel chord trusses; the first support surface and the second support surface each comprise a first vertical web, a second vertical web and a third vertical web; one side of the second vertical web is the first vertical web, and the other side of the second vertical web is the third vertical web;

[0028] The bottom surface of the first vertical web of the first support surface and the bottom surface of the first vertical web of the second support surface are provided with a first reinforcing horizontal plate; a second reinforcing horizontal plate is arranged between the first vertical web of the first support surface and the first vertical web of the second support surface; the first reinforcing horizontal plate is parallel to the second reinforcing horizontal plate; a reinforcing vertical plate is arranged between the first reinforcing horizontal plate and the second reinforcing horizontal plate; the second reinforcing horizontal plate and the reinforcing vertical plate form a T-shaped reinforcing structure; the windward surfaces of the first reinforcing horizontal plate, the second reinforcing horizontal plate and the reinforcing vertical plate are respectively provided with inclined surfaces for reducing the aerodynamic resistance of the rocket sled system, improving the thrust-to-weight ratio and saving power;

[0029] A fairing plate is arranged between the first support surface and the second support surface; the fairing plate is an isosceles triangular thick plate; a long strip-shaped groove is arranged at the vertex of the fairing plate; the reinforcing vertical plate is embedded in the long strip-shaped groove; a first groove and a second groove are respectively arranged at the two bottom corners of the fairing plate, so that the third vertical web of the first support surface and the third vertical web of the second support surface are respectively embedded in the first groove and the second groove; the angle between the fairing plate and the plane where the sled chassis is located is 7°; an inclined fairing surface is arranged on the top surface of the fairing plate; the function of the fairing plate is to reduce the aerodynamic resistance of the rocket sled, increase the aerodynamic downforce of the rocket sled and reduce the vibration value of the rocket sled;

[0030] A groove is arranged on the top surface of the fairing plate; a detachable cover plate is arranged on the top surface of the groove to facilitate the installation of a sled data recorder.

[0031] The clamping ring support structure comprises a first clamping ring, a second clamping ring, a third clamping ring and a full-thread screw rod; the first clamping ring, the second clamping ring and the third clamping ring are all circular ring bodies; the longitudinal section of the first clamping ring, the second clamping ring and the third clamping ring are all isosceles trapezoids; the first clamping ring, the second clamping ring and the third clamping ring are coaxial; the included angle between the bottom edge and the height of the longitudinal section of the first clamping ring, the included angle between the bottom edge and the height of the longitudinal section of the second clamping ring and the included angle between the bottom edge and the height of the longitudinal section of the third clamping ring are all equal. The outer surface of the first clamping ring is provided with a first radial ear and a second radial ear; the first radial ear and the second radial ear are thin plates; the first radial ear and the second radial ear are coplanar; the plane on which the first radial ear and the second radial ear are located is coplanar with the axis of the first clamping ring; the outer surface of the second clamping ring is provided with a third radial ear and a fourth radial ear; the third radial ear and the fourth radial ear are thin plates; the third radial ear and the fourth radial ear are coplanar; the plane on which the third radial ear and the fourth radial ear are located is coplanar with the axis of the second clamping ring; the outer surface of the third clamping ring is provided with a fifth radial ear and a sixth radial ear; the fifth radial ear and the sixth radial ear are thin plates; the fifth radial ear and the sixth radial ear are coplanar; the plane on which the fifth radial ear and the sixth radial ear are located is coplanar with the axis of the third clamping ring; the center of the top surface of the first radial ear, the second radial ear, the third radial ear and the fourth radial ear is provided with a threaded hole; a bolt is arranged in the threaded hole;

[0032] The first radial ear is provided with a first through hole parallel to the axis of the first clamping ring; the second radial ear is provided with a second through hole parallel to the axis of the first clamping ring; the third radial ear is provided with a third through hole parallel to the axis of the second clamping ring; the fourth radial ear is provided with a fourth through hole parallel to the axis of the first clamping ring; a first full-thread screw rod is arranged in the first through hole and the third through hole; a second full-thread screw rod is arranged in the second through hole and the fourth through hole; one end of the first full-thread screw rod is fixedly connected with the bottom surface of the fifth radial ear; one end of the second full-thread screw rod is fixedly connected with the bottom surface of the sixth radial ear;

[0033] The surface with the largest radius of the third clamping ring is the bottom surface; the bottom surface of the third clamping ring is provided with a back baffle; the back baffle is a circular ring-shaped thin plate; the inner ring radius of the back baffle is smaller than the inner ring radius of the bottom surface of the third clamping ring; the bottom surface of the third clamping ring is fixedly connected with the top surface of the back baffle;

[0034] The bottom surface of the back baffle is provided with a test object support rod; one end of the test object support rod is fixedly connected with the bottom surface of the back baffle, and the other end of the test object support rod is fixedly connected with the plane on which the sled bottom disc is located; the number of the test object support rods is 2;

[0035] The bottom surface of the third vertical web of the first support surface and the third vertical web of the second support surface is provided with a second reinforcing cross plate; a T-shaped reinforcing structure is arranged between the third vertical web of the first support surface and the third vertical web of the second support surface.

[0036] The application will be further described below in connection with specific embodiments and drawings.

[0037] The application is mainly directed to a rocket sled test platform designed for performance examination of a supersonic heavy parachute system, which can realize simulation requirements of various supersonic heavy parachutes on dynamic pressure, speed and acceleration through different power configurations; through power supply system design, the supersonic heavy parachute system is provided with multiple action electric signals to complete actions such as ejection inflation and main parachute bag pull-out of the supersonic heavy parachute, and to examine and verify the performance of the supersonic heavy parachute system.

[0038] The application is a rocket sled test platform suitable for a supersonic heavy parachute system, which is in the form of a double-track whole sled structure, the front end of the sled body is a truss structure composed of three columns, the tested warhead is connected with the columns through three snap rings respectively, the sled body chassis is designed with a triangular fairing plate and a dynamic power-on system; the rear of the sled body is mainly a motor fixing structure, including a motor fixing snap ring and a motor head fairing cap and the like.

[0039] The application is further realized in that: the front and middle snap rings are conical rings, the ring body widths are 120mm and 100mm respectively, the rear snap ring is a conical upper and lower ring, the ring body width is 100mm, and the half-cone angles of the three snap rings are all between 5° and 15°, so as to adapt to the shape of the tested warhead. In order to prevent small displacement of the tested warhead in the heading direction from causing gaps in the circumferential direction of the conical ring and causing limit failure, holes are opened in the heading direction of the ears of the front and middle snap rings, the front and middle snap rings are connected through a full-thread screw rod and connected to the rear column, and a backward force is pre-added to make the conical ring clamp the tested warhead and ensure the limit.

[0040] The application is further realized in that: the three columns are all made of BS steel plate tailor-welded, the column height can reach 1.8m, and the included angle between the column and the upper surface of the whole beam is about 80°, which can provide lateral vertical support for the tested warhead. The front and rear columns are reinforced through a T-shaped structure, and the single-side columns are reinforced through an X-shaped structure. Limiting blocks are designed on the front and middle columns to limit the tested warhead left and right. The windward surface of the front column and the windward surface of the T-shaped reinforcing structure are designed with a triangular fairing structure, which is used to reduce the aerodynamic resistance of the rocket sled system, improve the thrust-to-weight ratio, and save power.

[0041] The application is further realized in that: the chassis "wedge-shaped" fairing structure is mainly used to reduce the aerodynamic resistance of the rocket sled, increase the aerodynamic downforce of the rocket sled, and reduce the vibration value of the rocket sled. The cross-sectional shape is triangular, the fairing angle is 7°, and the fairing plate is made of BS-960 with a thickness of 3mm, and is welded with an upper cover plate, a side sealing plate, a bottom plate and longitudinal and transverse ribs. The fairing plate is provided with a detachable cover plate, which facilitates the installation of a sled-mounted data logger inside the fairing.

[0042] The implementation of the present application also lies in that the skid chassis is composed of four integral beams, eight slide shoes and a plurality of square tubes, the slide shoes are respectively installed at both ends of the integral beams, the integral beams are connected through square steel and square tubes, the integral beams are processed from integral Q345 steel plates to provide sufficient rigidity and strength for the chassis, the slide shoes are processed from 30CrMnSiNi2A steel after heat treatment to provide sufficient constraint force between the chassis and the track, and the square tubes are longitudinally connected with the six integral beams to connect the whole chassis as a whole.

[0043] The implementation of the present application also lies in that the power supply system is designed to provide multiple action electric signals for the supersonic heavy parachute, and the power supply system is mainly composed of a cutting knife and a threading pipe.

[0044] The present application is a rocket sled test platform, as shown in Figure 1 The present application is a rocket sled test platform, as shown in Figure 2 The present application is a rocket sled test platform, as shown in Figure 3 The present application is a rocket sled test platform, as shown in Figure 4 The present application is a rocket sled test platform, as shown in Figure 5 The present application is a rocket sled test platform, as shown in

[0045] When the present application is used in the opening parachute test of a certain supersonic heavy parachute, the mass of the test projectile is about 300 kg, the maximum speed of the test product is about 850 m / s, the height of the test product is greater than 1.8 m (the distance from the test product axis to the track upper surface), and five rocket engines are installed on the rocket sled system.

[0046] In conclusion, the rocket sled test platform of the application comprises a stand column, a fairing, a power supply system, a snap ring, an engine fixing assembly and a chassis. The test projectile is fixed on the stand column through the snap ring, and the number of the snap ring, the support height of the test projectile, the number of the power supply system and the number of the engine are determined according to the test requirements. The test platform can meet the needs of supersonic heavy parachute rocket sled test.

Claims

1. A hypersonic decelerating parachute rocket sled test platform, characterized by: The application relates to a double-track rocket sled system, which comprises a sled chassis, a support part, a rectifier part, a clasp support structure and a dynamic power-on system; the sled chassis is a double-track rocket sled; an engine is arranged at the rear end of the sled chassis in the navigation direction; a support part is arranged at the front end of the sled chassis in the navigation direction; the support part comprises a first support surface and a second support surface; the first support surface and the second support surface are truss structures; the first support surface and the second support surface are arranged on the two sides of the sled chassis in the advancing direction respectively; the included angle between the first support surface and the second support surface and the plane where the sled chassis is located is the same; the upper chords of the first support surface and the second support surface are provided with the clasp support structure; and the dynamic power-on system is arranged on the sled chassis.

2. The hypersonic decelerating parachute rocket sled test platform according to claim 1, characterized in that: The first support surface and the second support surface are parallel chord trusses; the first support surface and the second support surface each comprise a first vertical web, a second vertical web and a third vertical web; one side of the second vertical web is the first vertical web, and the other side of the second vertical web is the third vertical web; the bottom surface of the first vertical web of the first support surface and the bottom surface of the first vertical web of the second support surface are provided with a first reinforcing horizontal plate.

3. The hypersonic decelerating parachute rocket sled test platform according to claim 2, characterized in that: A second reinforcing horizontal plate is arranged between the first vertical web of the first support surface and the first vertical web of the second support surface; the first reinforcing horizontal plate is parallel to the second reinforcing horizontal plate; a reinforcing vertical plate is arranged between the first reinforcing horizontal plate and the second reinforcing horizontal plate; and the second reinforcing horizontal plate and the reinforcing vertical plate form a T-shaped reinforcing structure.

4. The hypersonic decelerating parachute rocket sled test platform according to claim 1, wherein: The bottom surfaces of the third vertical web of the first support surface and the third vertical web of the second support surface are provided with a second reinforcing horizontal plate; and a T-shaped reinforcing structure is arranged between the third vertical web of the first support surface and the third vertical web of the second support surface.

5. The hypersonic decelerating parachute rocket sled test platform according to claim 3 or claim 4, characterized in that: The windward surfaces of the first reinforcing horizontal plate, the second reinforcing horizontal plate and the reinforcing vertical plate are respectively provided with inclined surfaces, which are used for reducing the aerodynamic resistance of the rocket sled system, improving the thrust-to-weight ratio and saving power.

6. The hypersonic decelerating parachute rocket sled test platform according to claim 1, characterized in that: A rectifier plate is arranged between the first support surface and the second support surface; the rectifier plate is an isosceles triangular thick plate; a long-strip-shaped groove is arranged at the top of the rectifier plate; the reinforcing vertical plate is embedded into the long-strip-shaped groove; a first groove and a second groove are arranged at the two bottom corners of the rectifier plate respectively, so that the third vertical web of the first support surface and the third vertical web of the second support surface are embedded into the first groove and the second groove respectively; the included angle between the rectifier plate and the plane where the sled chassis is located is 7 degrees; and an inclined rectifier surface is arranged on the top surface of the rectifier plate; the rectifier plate is used for reducing the aerodynamic resistance of the rocket sled, increasing the aerodynamic downforce of the rocket sled and reducing the vibration value of the rocket sled.

7. The hypersonic decelerating parachute rocket sled test platform according to claim 6, characterized in that: A groove is arranged on the top surface of the rectifier plate; a detachable cover plate is arranged on the top surface of the groove, so that a sled data recorder can be conveniently installed.

8. The hypersonic decelerating parachute rocket sled test platform according to claim 1, characterized in that: The clamping ring support structure comprises a first clamping ring, a second clamping ring, a third clamping ring and a full-thread screw rod; the first clamping ring, the second clamping ring and the third clamping ring are all circular ring bodies; the longitudinal section of the first clamping ring, the second clamping ring and the third clamping ring are all isosceles trapezoids; the first clamping ring, the second clamping ring and the third clamping ring are coaxial; the included angle between the base and the height of the longitudinal section of the first clamping ring, the included angle between the base and the height of the longitudinal section of the second clamping ring and the included angle between the base and the height of the longitudinal section of the third clamping ring are all equal; the outer surface of the first clamping ring is provided with a first radial ear and a second radial ear; the first ear and the first ear are thin plates; the first ear and the second ear are coplanar; the plane where the first ear and the second ear are located is coplanar with the axis of the first clamping ring; the outer surface of the second clamping ring is provided with a third radial ear and a fourth radial ear; the third ear and the fourth ear are thin plates; the third ear and the fourth ear are coplanar; the plane where the third ear and the fourth ear are located is coplanar with the axis of the second clamping ring; the outer surface of the third clamping ring is provided with a fifth radial ear and a sixth radial ear; the fifth ear and the sixth ear are thin plates; the fifth ear and the sixth ear are coplanar; the plane where the fifth ear and the sixth ear are located is coplanar with the axis of the third clamping ring; the center position of the top surface of the first ear, the second ear, the third ear and the fourth ear is provided with a threaded hole; a bolt is arranged in the threaded hole; the first ear is provided with a first through hole parallel to the axis of the first clamping ring; the second ear is provided with a second through hole parallel to the axis of the first clamping ring; the third ear is provided with a third through hole parallel to the axis of the second clamping ring; the fourth ear is provided with a fourth through hole parallel to the axis of the first clamping ring; a first full-thread screw rod is arranged in the first through hole and the third through hole; a second full-thread screw rod is arranged in the second through hole and the fourth through hole; one end of the first full-thread screw rod is fixedly connected with the bottom surface of the fifth ear; one end of the second full-thread screw rod is fixedly connected with the bottom surface of the sixth ear.

9. The hypersonic decelerating parachute rocket sled test platform according to claim 8, characterized in that: The surface with the largest radius of the third clamping ring is the bottom surface; the bottom surface of the third clamping ring is provided with a back baffle; the back baffle is a circular ring thin plate; the inner ring radius of the back baffle is smaller than the inner ring radius of the bottom surface of the third clamping ring; the bottom surface of the third clamping ring is fixedly connected with the top surface of the back baffle.

10. The hypersonic decelerating parachute rocket sled test platform according to claim 9, characterized in that: The bottom surface of the back baffle is provided with a test sample support rod; one end of the test sample support rod is fixedly connected with the bottom surface of the back baffle, and the other end of the test sample support rod is fixedly connected with the plane where the sled bottom disc is located; the number of the test sample support rods is 2.

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