A rocket flight simulation test platform

Abstract

This invention provides a rocket flight simulation experimental platform, comprising a vertically arranged lower and upper cylinder, a support structure at the bottom of the lower cylinder, a rocket model mounted on the support structure, an iris mechanism for providing wind speed, and a blower system connected to the bottom of the lower cylinder. The top of the lower cylinder is detachably connected to the bottom of the upper cylinder. The iris mechanism is connected to the rocket model and has a jet assembly. A top plate is located at the top of the upper cylinder, and a high-definition camera is mounted on the bottom surface of the top plate. The high-definition camera is connected to a display screen via a video cable. An air inlet pipe and an air outlet are located on the top plate. The jet assembly and the air inlet pipe are connected to the blower system. The rocket flight simulation experimental platform provided by this invention can simulate the effects of wind speed, air temperature, and tilt on the rocket's flight state. Through low-cost mechanical devices, it achieves multifunctional technical effects and has good versatility.

Description

Technical Field

[0001] This invention belongs to the field of rocket flight status detection, specifically relating to a rocket flight simulation experimental platform. Background Technology

[0002] Currently, most existing rocket propulsion experimental devices, especially those used in student experiments, primarily test the main parameters of the rocket propellant. However, testing of the rocket's flight status is extremely rare. Because rockets encounter many complex dynamic problems during launch and flight—for example, the effects of wind speed, air temperature, and tilt on the rocket's flight status—it is necessary to test the relative motion between the rocket and the air under simulated conditions, i.e., wind speed, air temperature, and tilt. Existing technologies often use simulations of rocket speed or wind speed, which are limited in function and cannot provide a comprehensive and effective simulation.

[0003] Therefore, this solution addresses the aforementioned technical problems by designing a rocket flight simulation experimental platform to achieve multi-functional technical effects. Summary of the Invention

[0004] The purpose of this invention is to provide a rocket flight simulation test platform that solves the technical problem of how to simulate the effects of wind speed, air temperature, and tilt on rocket flight status. Through low-cost mechanical devices, it achieves multifunctional technical effects and has good versatility.

[0005] A rocket flight simulation test platform includes a vertically arranged lower cylinder and an upper cylinder, a support structure disposed at the bottom of the lower cylinder, a rocket model disposed on the support structure, an iris mechanism for providing wind speed, and a blower system connected to the bottom of the lower cylinder. The top of the lower cylinder is detachably connected to the bottom of the upper cylinder. The iris mechanism is connected to the rocket model, and a jet assembly is disposed on the iris mechanism.

[0006] The top of the upper cylinder is provided with a top plate, and a high-definition camera is provided on the bottom surface of the top plate. The high-definition camera is connected to the display screen through a video cable. An air inlet pipe is provided on the top plate, and an air outlet is provided on the top plate.

[0007] The jet assembly and the air intake pipe are respectively connected to the blower system.

[0008] The rocket model includes a vertical section, a base horizontally positioned at the bottom of the vertical section, an airbag ring surrounding the outer side of the base, and a rubber ring surrounding the outer side of the airbag ring. The outer side of the rubber ring is coated with lubricating oil, and the lubricating oil slides in contact with the inner sides of the lower and upper vertical cylinders.

[0009] The blower system includes a blower connected to the bottom end of the lower cylinder via a blower pipe, an exhaust pipe connected to the blower pipe at one end, and a solenoid valve installed on the exhaust pipe.

[0010] The bottom end of the lower cylinder is provided with an air inlet, and one end of the air pipe is connected to the air inlet.

[0011] The iris recognition mechanism includes a horizontally arranged fixed ring, five drive shafts arranged in a ring array passing through the fixed ring, a cam rod connected to one end of the drive shaft, a gear on the drive shaft, a synchronous belt connected to the five gears, and a micro motor connected to one of the drive shafts. The bottom end of the drive shaft is rotatably disposed in the rubber ring.

[0012] The jet assembly is located at the other end of the cam rod, and the micro motor is mounted on the rubber ring.

[0013] The jet assembly includes a horizontally arranged jet head, a threaded post whose top end is connected to the jet head, and a bottom end of the threaded post connected to the cam rod. The five jet heads are connected to the blower through jet pipes.

[0014] The top end of the lower vertical cylinder and the bottom end of the upper vertical cylinder are respectively provided with a lower external thread and an upper external thread. The lower external thread and the upper external thread are respectively connected to the connecting ring. The inner side of the connecting ring is provided with an internal thread.

[0015] A support plate is vertically arranged on the outer side of the upper end of the lower tube, and a protective sleeve is coaxially arranged on the outer edge of the support plate. The upper end face of the protective sleeve is in detachable contact with the top plate.

[0016] The base has several water inlet pipes arranged in a circular array. The bottom end of each water inlet pipe passes through the base, and the top end passes through the top plate and is connected to the water pump. A tension sensor is installed at the upper end of each water inlet pipe. The tension sensor is installed on the top plate, and the top plate is connected to the lifting structure.

[0017] The water pump is connected to the bottom end of the lower cylinder and is also connected to the water tank.

[0018] The lifting structure includes lifting cylinders respectively disposed on both sides of the upper cylinder, the bottom end of the lifting cylinder being disposed on the support plate, and between the upper cylinder and the protective cylinder.

[0019] A heating element is provided between the upper cylinder and the protective cylinder.

[0020] This invention achieves the following significant effects:

[0021] (1) This scheme includes a rocket model and a blower system, which work together to achieve the following technical effects:

[0022] First, an airbag ring and a rubber ring are set on the outside of the base of the rocket model. Under the expansion of the airbag, the rubber ring expands slightly outward, which helps the outer side of the rubber ring to stick tightly to the inner wall of the lower cylinder and form a closed space under the base. Under the action of the blower, the air pressure in the closed space increases, which pushes the rocket model to rise.

[0023] Secondly, it is equipped with airbags. Since the airbags are flexible structures and their interiors are filled with air, the movement of the rocket model becomes flexible. Under the action of external forces, the vertical parts and the base of the rocket model are more likely to shift, which is very close to the actual movement of the rocket and helps to improve the accuracy of the simulation results.

[0024] Third, it is equipped with a blower system, which not only serves to lift and lower the rocket model, but also connects to the jet assembly and air intake pipe. Through the jet assembly and air intake pipe, vertical and horizontal winds are generated in the upper and lower cylinders. The deflection of the rocket model under different wind directions can be observed through a high-definition camera, which helps to measure the impact of the relative wind speed on the rocket's flight status.

[0025] (2) This solution includes an iris recognition mechanism, which has the following technical advantages:

[0026] First, a jet head is installed on the cam rod, so that the jet head can be set towards the rocket model. At the same time, the jet head is connected to the cam rod through a threaded post, which achieves good fixation of the jet head.

[0027] Secondly, the five cam rods rotate simultaneously and can clamp the vertical part of the rocket model at the same time, so that the vertical part of the rocket model is in a vertical state, which helps to test the influence of the tilt degree on the rocket's flight state in subsequent tests.

[0028] (3) In this scheme, a water inlet pipe is installed on the base. The top of the water inlet pipe passes through the top plate and is connected to the water pump. The rocket model is raised by the recoil force of the water, which avoids the high temperature and safety problems caused by the rocket propulsion in the past. This idea is novel and ingenious and helps to save energy. Under the action of the lifting structure, the water inlet pipe is raised. At the same time, the upper end of the water inlet pipe is connected to a tension sensor. The tension sensor helps to measure the degree of tilt of the rocket model under different recoil forces. That is, the tilt tendency of the rocket model can be qualitatively analyzed by the readings on different tension sensors.

[0029] (4) A protective sleeve is provided. On the one hand, the lifting cylinder can be placed inside the protective sleeve to realize the lifting and lowering of the top plate, thereby realizing the lifting and lowering adjustment of the water inlet pipe to match the movement height of the rocket model.

[0030] In addition, the upper tube can be removed while the protective tube is retained. This allows the rocket model to float completely in mid-air under the recoil force of the water, which helps to enhance the simulation and visual effect. Attached Figure Description

[0031] Figure 1 This is a schematic diagram of the rocket simulation flight test platform in this invention.

[0032] Figure 2 This is a schematic diagram of the internal structure of the protective sleeve in this invention.

[0033] Figure 3 This is a schematic diagram of the connection structure between the rocket model and the iris mechanism and recoil structure in this invention.

[0034] Figure 4 This is a schematic diagram of the connection structure between the rocket model and the iris mechanism in this invention.

[0035] Figure 5 This is a schematic diagram of the rocket model in this invention.

[0036] Figure 6 This is a schematic diagram of the iris mechanism in this invention.

[0037] Figure 7 This is a schematic diagram of the connection structure of the top plate in this invention.

[0038] Figure 8 This is a schematic diagram of the connection structure between the upper and lower vertical cylinders in this invention.

[0039] The attached diagram is labeled as follows: 1. Lower cylinder; 2. Water pump; 3. Water tank; 4. Exhaust pipe; 5. Blower; 6. Solenoid valve; 7. Support plate; 72. Lifting cylinder; 8. Protective cylinder; 81. Connecting ring; 82. Upper cylinder; 9. Top plate; 91. High-definition camera; 10. Air inlet pipe; 11. Water inlet pipe; 12. Tension sensor; 13. Rocket model; 131. Base; 132. Airbag ring; 133. Rubber ring; 14. Iris recognition mechanism; 141. Fixing ring; 142. Cam rod; 143. Jet head; 144. Threaded column; 145. Drive shaft; 146. Synchronous belt; 15. Support column; 16. Base plate. Detailed Implementation

[0040] To more clearly illustrate the technical features of this solution, the following detailed implementation method will be used to explain the solution.

[0041] To more clearly illustrate the technical features of this solution, the following detailed implementation method will be used to explain the solution.

[0042] See Figures 1-8A rocket flight simulation test platform includes a vertically arranged lower cylinder 1 and upper cylinder 82, a support structure set at the bottom of the lower cylinder 1, a rocket model 13 set on the support structure, an iris mechanism 14 for providing wind speed, and a blower system connected to the bottom of the lower cylinder 1. The top of the lower cylinder 1 is detachably connected to the bottom of the upper cylinder 82. The iris mechanism 14 is connected to the rocket model 13, and a jet assembly is provided on the iris mechanism 14.

[0043] The top of the upper cylinder 82 is provided with a top plate 9, and a high-definition camera 91 is provided on the bottom surface of the top plate 9. The high-definition camera 91 is connected to the display screen through a video cable. An air inlet pipe 10 is provided on the top plate 9, and an air outlet is provided on the top plate 9.

[0044] The jet assembly and the air intake pipe 10 are respectively connected to the blower system.

[0045] More preferably, the support structure includes a horizontally arranged base plate 16 and several vertically arranged support columns 15 on the base plate 16. The rocket model 13 is detachably arranged on the support columns 15, thus forming a space between the bottom end of the lower cylinder and the rocket model 13. Under the action of the blower, the air pressure in the space rises, driving the rocket model 13 to rise.

[0046] The rocket model 13 includes a vertical part, a base 131 horizontally set at the bottom of the vertical part, an airbag ring 132 surrounding the outer side of the base 131, and a rubber ring 133 surrounding the outer side of the airbag ring 132. The outer side of the rubber ring 133 is coated with lubricating oil, and the lubricating oil slides in contact with the inner side of the lower vertical cylinder 1 and the upper vertical cylinder 82.

[0047] The blower system includes a blower 5 connected to the bottom of the lower cylinder 1 via a blower pipe, an exhaust pipe 4 connected to the blower pipe at one end, and a solenoid valve 6 installed on the exhaust pipe 4.

[0048] The bottom end of the lower cylinder 1 is provided with an air inlet, and one end of the air pipe is connected to the air inlet.

[0049] The iris recognition mechanism 14 includes a horizontally arranged fixed ring 141, five drive shafts 145 arranged in a ring array passing through the fixed ring 141, a cam rod 142 connected to one end of the drive shaft 145, a gear arranged on the drive shaft 145, a synchronous belt 146 connected to the five gears, and a micro motor connected to one of the drive shafts 145. The bottom end of the drive shaft 145 is rotatably arranged in a rubber ring 133.

[0050] The other end of the cam rod 142 is equipped with a jet assembly, and the micro motor is mounted on the rubber ring 133.

[0051] The jet assembly includes a horizontally positioned jet head 143, a threaded post 144 whose top end is connected to the jet head 143, and a cam rod 142 whose bottom end is connected to the threaded post 144. The five jet heads 143 are connected to the blower 5 through jet pipes.

[0052] The top end of the lower vertical cylinder 1 and the bottom end of the upper vertical cylinder 82 are respectively provided with a lower external thread and an upper external thread. The lower external thread and the upper external thread are respectively connected to the connecting ring 81. The inner side of the connecting ring 81 is provided with an internal thread.

[0053] A support plate 7 is vertically installed on the outer side of the upper end of the lower tube 1. A protective tube 8 is coaxially installed on the outer edge of the support plate 7. The upper end face of the protective tube 8 is in separable contact with the top plate 9.

[0054] A number of water inlet pipes 11 are arranged in a circular array on the base 131. The bottom end of the water inlet pipe 11 passes through the base 131, and its top end passes through the top plate 9 and is connected to the water pump 2. A tension sensor 12 is provided at the upper end of the water inlet pipe 11. The tension sensor 12 is located on the top plate 9, and the top plate 9 is connected to the lifting structure.

[0055] The water pump 2 is connected to the bottom of the lower cylinder 1 through solenoid valve 1 and to the water tank 3 through solenoid valve 2. The water pump 2 draws water out of the water tank 3 and introduces it into the water inlet pipe 11. The bottom of the water inlet pipe 11 sprays water downward and forms a recoil force. When the water in the water tank 3 is drained, solenoid valve 1 is opened to draw water out of the lower cylinder 1, forming a water circulation state, which helps to save water resources.

[0056] The lifting structure includes lifting cylinders 72 respectively installed on both sides of the upper cylinder 82. The bottom end of the lifting cylinder 72 is installed on the support plate 7 and between the upper cylinder 82 and the protective cylinder 8.

[0057] A heating element is installed between the upper tube 82 and the protective tube 8 to detect the movement status of the rocket model under high-temperature conditions. The impact of temperature on launch is primarily reflected in the thousands of components of the rocket. These components each have a suitable temperature range for normal operation; once the temperature exceeds this range, the components will cease functioning, thus affecting the rocket launch. Therefore, miniature components can be appropriately placed inside the rocket model. These components do not participate in the rocket launch but can be used to determine or simulate their operating conditions under high temperatures, providing data reference for actual rocket launch scenarios.

[0058] The specific working process of this invention is as follows:

[0059] This design includes a rocket model 13 and a blower system, which work together. An airbag ring 132 and a rubber ring 133 are provided on the outer side of the base 131 in the rocket model 13. Under the expansion of the airbag, the rubber ring 133 expands slightly outward, which helps the outer side of the rubber ring 133 to stick tightly to the inner wall of the lower cylinder 1 and form a closed space below the base 131. Under the action of the blower 5, the air pressure in the closed space increases, which pushes the rocket model 13 upward.

[0060] Since the airbag is a flexible structure and its interior is filled with air, the movement of the rocket model 13 becomes flexible. Under the action of external forces, the vertical part and the base 131 in the rocket model 13 are more likely to shift, which is very close to the actual movement of the rocket and helps to make the simulation results more accurate.

[0061] Equipped with a blower system, it not only serves to lift and lower the rocket model 13, but also connects to the jet assembly and air intake pipe 10. Through the jet assembly and air intake pipe 10, vertical and horizontal winds are generated in the upper and lower cylinders. The deflection of the rocket model 13 under different wind conditions is observed through the high-definition camera 91, which helps to measure the influence of the relative wind speed on the rocket's flight status.

[0062] This design includes an iris mechanism 14 and a jet head 143 on a cam rod 142, which allows the jet head 143 to face the rocket model 13. The jet head 143 is connected to the cam rod 142 via a threaded post 144, thus achieving good fixation of the jet head 143.

[0063] The five cam rods 142 rotate simultaneously and can clamp the vertical part of the rocket model 13 at the same time, so that the vertical part of the rocket model 13 is in a vertical state, which helps to test the influence of the tilt degree on the rocket's flight state in subsequent tests.

[0064] In this design, a water inlet pipe 11 is installed on the base 131. The top of the water inlet pipe 11 passes through the top plate 9 and is connected to the water pump 2. The rocket model 13 is raised by the recoil force of the water, which is a water jet propulsion system. This avoids the high temperature and safety problems caused by the previous use of rocket propulsion systems. This design is novel and ingenious and helps to save energy. Under the action of the lifting structure, the water inlet pipe 11 is raised. At the same time, the upper end of the water inlet pipe 11 is connected to the tension sensor 12. The tension sensor 12 helps to measure the degree of tilt of the rocket model 13 under different recoil forces. That is, the tilt tendency of the rocket model 13 can be quantitatively and qualitatively analyzed by the readings on different tension sensors 12, or the magnitude of the tension caused by the deflection angle of the rocket model under different wind directions. The experimental phenomena can be observed through a high-definition camera. At this time, the lifting structure is needed to raise the top plate to a certain height so that the height of the rocket model 13 can be easily adjusted and the tension sensor 12 can show the corresponding reading.

[0065] The protective sleeve 8 is provided so that the lifting cylinder 72 can be placed inside the protective sleeve 8 to lift the top plate 9, thereby realizing the lifting and adjustment of the water inlet pipe 11 to match the movement height of the rocket model 13.

[0066] In addition, the upper tube 82 can be removed while the protective tube 8 is retained. In this way, when the rocket model 13 is subjected to the recoil force of the water, it can be completely suspended in mid-air, which helps to enhance the simulation and visual effect.

[0067] An anemometer or temperature sensor can be installed inside the upper cylinder to detect wind speed and temperature. The installation location of the anemometer or temperature sensor can be determined according to the actual situation, and will not be described in detail here.

[0068] The technical features of this invention not described can be implemented by or using existing technology, and will not be repeated here. Of course, the above description is not a limitation of this invention, and this invention is not limited to the examples above. Any changes, modifications, additions or substitutions made by those skilled in the art within the scope of this invention should also be within the protection scope of this invention.

[0069] The technical features of this invention not described can be implemented by or using existing technology, and will not be repeated here. Of course, the above description is not a limitation of this invention, and this invention is not limited to the examples above. Any changes, modifications, additions or substitutions made by those skilled in the art within the scope of this invention should also be within the protection scope of this invention.

Claims

1. A rocket flight simulation test platform, characterized in that, It includes a vertically arranged lower cylinder (1) and upper cylinder (82), a support structure set at the bottom of the lower cylinder (1), a rocket model (13) set on the support structure, an iris mechanism (14) for providing wind speed, and a blower system connected to the bottom of the lower cylinder (1). The top of the lower cylinder (1) is detachably connected to the bottom of the upper cylinder (82). The iris mechanism (14) is connected to the rocket model (13). An air jet assembly is provided on the iris mechanism (14). The top of the upper cylinder (82) is provided with a top plate (9), and a high-definition camera (91) is provided on the bottom surface of the top plate (9). The high-definition camera (91) is connected to the display screen through a video cable. An air inlet pipe (10) is provided on the top plate (9), and an air outlet is provided on the top plate (9). The jet assembly and the air intake pipe (10) are respectively connected to the blower system; The rocket model (13) includes a vertical part, a base (131) horizontally disposed at the bottom end of the vertical part, an airbag ring (132) surrounding the outer side of the base (131), and a rubber ring (133) surrounding the outer side of the airbag ring (132). The outer side of the rubber ring (133) is coated with lubricating oil, and the lubricating oil slides in contact with the inner side of the lower vertical cylinder (1) and the upper vertical cylinder (82). The blower system includes a blower (5) connected to the bottom end of the lower cylinder (1) via a blower pipe, an exhaust pipe (4) connected to the blower pipe at one end, and a solenoid valve (6) installed on the exhaust pipe (4). The bottom end of the lower vertical cylinder (1) is provided with an air inlet, and one end of the air pipe is connected to the air inlet; The iris mechanism (14) includes a horizontally arranged fixed ring (141), five drive shafts (145) arranged in a ring array passing through the fixed ring (141), a cam rod (142) with one end connected to the drive shaft (145), a gear arranged on the drive shaft (145), a synchronous belt (146) connected to the five gears, and a micro motor connected to one of the drive shafts (145). The bottom end of the drive shaft (145) is rotatably arranged in the rubber ring (133). The other end of the cam rod (142) is provided with the jet assembly, and the micro motor is provided on the rubber ring (133); The jet assembly includes a horizontally arranged jet head (143), a threaded post (144) whose top end is connected to the jet head (143), the bottom end of the threaded post (144) being connected to the cam rod (142), and five jet heads (143) being connected to the blower (5) through jet pipes; The base (131) is provided with a plurality of water inlet pipes (11) arranged in a ring array. The bottom end of the water inlet pipe (11) passes through the base (131), and its top end passes through the top plate (9) and is connected to the water pump (2). A tension sensor (12) is provided at the upper end of the water inlet pipe (11). The tension sensor (12) is provided on the top plate (9). The top plate (9) is connected to the lifting structure. The water pump (2) is connected to the bottom end of the lower cylinder (1) and to the water tank (3).

2. The rocket flight simulation test platform according to claim 1, characterized in that, The top end of the lower vertical cylinder (1) and the bottom end of the upper vertical cylinder (82) are respectively provided with a lower external thread and an upper external thread. The lower external thread and the upper external thread are respectively connected to the connecting ring (81). The inner side of the connecting ring (81) is provided with an internal thread.

3. The rocket flight simulation test platform according to claim 2, characterized in that, A support plate (7) is vertically arranged on the outer side of the upper end of the lower tube (1), and a protective tube (8) is coaxially arranged on the outer edge of the support plate (7). The upper end face of the protective tube (8) is in detachable contact with the top plate (9).

4. The rocket flight simulation test platform according to claim 3, characterized in that, The lifting structure includes lifting cylinders (72) respectively disposed on both sides of the upper cylinder (82), the bottom end of the lifting cylinder (72) is disposed on the support plate (7), and between the upper cylinder (82) and the protective cylinder (8).

5. The rocket flight simulation test platform according to claim 4, characterized in that, A heating element is provided between the upper cylinder (82) and the protective cylinder (8).

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