Rocket aerodynamic flight experiment simulation device

Abstract

A rocket aerodynamic flight experiment simulation device, comprising a base, a rocket body arranged on the base, a rocket engine arranged in the rocket body, a booster arranged on the rocket body, and a gas supply mechanism arranged on the rocket body and used for providing power for the rocket body, a ventilation mechanism connected with the gas supply mechanism and used for driving a stabilizing mechanism, the stabilizing mechanism connected with the ventilation mechanism and used for keeping the rocket body stable, a lifting mechanism matched with the gas supply mechanism, the lifting mechanism being detachably connected with the booster, and the stabilizing mechanism being rotatably arranged in the rocket body. The rocket aerodynamic flight experiment simulation device can not only keep the rocket stable during flight, but also apply thrust to the rocket through air after the booster is separated from the rocket body, thereby reducing pollution to the environment.

Description

Technical Field

[0001] This invention relates to the field of rocket flight, and more specifically to a rocket aerodynamic flight experiment simulation device. Background Technology

[0002] Before a rocket can fly, it needs the reaction force of the working medium ejected by the rocket engine to propel it. The rocket engine is a jet engine that uses the impulse principle and its own propellant to start. It does not rely on external working medium to generate thrust and can fly inside or outside the atmosphere. The rocket launch requires not only a rocket engine but also a base.

[0003] In teaching or experiments, simulation devices are often needed to simulate rocket flight. When a rocket is in flight, it may deflect due to wind or other factors, changing its original direction. Most rocket flight simulation devices use the high-temperature and high-speed exhaust gas ejected during fuel combustion to generate thrust, enabling the rocket to launch and fly. However, this launch and flight method consumes a lot of heat, has low heat utilization, and the substances produced after fuel combustion have an impact on the environment. This invention addresses the above-mentioned technical problems. Summary of the Invention

[0004] This invention provides a rocket aerodynamic flight experiment simulation device, which can not only keep the rocket stable during flight, but also apply thrust to the rocket through air after the booster separates from the rocket body, thereby reducing environmental pollution.

[0005] A rocket aerodynamic flight experiment simulation device includes a base, a rocket body mounted on the base, a rocket engine mounted inside the rocket body, a booster mounted on the rocket body, an air supply mechanism mounted on the rocket body, a ventilation mechanism connected to the air supply mechanism, a stabilization mechanism connected to the ventilation mechanism and used to maintain the stability of the rocket body, and a lifting mechanism attached to the air supply mechanism, wherein the lifting mechanism is detachably connected to the booster.

[0006] The gas supply mechanism is used to provide power to the rocket body, and the ventilation mechanism is used to drive the stabilization mechanism, which is rotatably mounted inside the rocket body.

[0007] Furthermore, the stabilizing mechanism includes a fixed column vertically disposed within the rocket body, a rotating block rotatably disposed at the top of the fixed column, and several fan blades disposed on the side of the rotating block, with the bottom surface of the rotating column fixed to the top surface of the rotating block.

[0008] Furthermore, the ventilation mechanism includes a ventilation duct one disposed in the fixed column, a ventilation duct two disposed in the rotating block and communicating with the ventilation duct one, and a ventilation duct three disposed in the fan blade and communicating with the ventilation duct two;

[0009] The opening end of ventilation duct one is located on the top surface of the fixed column, the opening ends of ventilation duct two are respectively located on the bottom and side surfaces of the rotating block, and the opening end of ventilation duct three is located on one side and end face of the fan blade. The air supply mechanism is connected to the fixed column and communicates with ventilation duct one.

[0010] Furthermore, the gas supply mechanism includes a liquid air tank disposed on the outside of the rocket body, a gas supply pipe one connected to the liquid air tank at one end, the other end of the gas supply pipe one connected to the injection port at the tail end of the rocket body, a gas supply pipe two connected to the gas supply pipe one at one end, and the other end of the gas supply pipe two connected to the ventilation mechanism.

[0011] The first gas supply pipe is provided with an inlet, which is connected to the first gas supply pipe, and the lifting mechanism is connected to the inlet.

[0012] Furthermore, a connecting block is vertically arranged inside the rocket body, and a through groove is vertically arranged inside the connecting block. The lifting mechanism includes a lifting rod slidably arranged in the through groove, a slot arranged at the tail end of the lifting rod, a baffle arranged at the top end of the lifting rod, and a second spring sleeved on the outside of the lifting rod with its top end arranged on the baffle. The bottom end of the second spring is arranged on the top surface of the connecting block. The plug is connected to the booster.

[0013] An air inlet is provided on the outer side of the rocket body, and the air inlet communicates with the interior of the rocket body. The baffle is used to block the air inlet. The side of the connecting rod is also connected to a vertically arranged plug, and the plug is inserted into the socket.

[0014] Furthermore, the booster includes a booster housing, an engine disposed below the booster housing, and a heat shield disposed inside the booster housing and located on the side of the engine. The inner side of the booster housing is connected to one end of a spring, and the other end of the spring is connected to the heat shield. A tail fin is disposed above the heat shield and is hinged to the side of the booster housing. A plug is disposed on the tail fin and is inserted into the slot.

[0015] Furthermore, a controller is installed inside the rocket body. The controller is connected to the rocket engine and also to a timer. The operator can pre-control the fuel in the booster, control the booster's working time, and input the data into the controller.

[0016] Furthermore, the base includes a base, a support frame disposed on the base and used to support the rocket body, and a support mechanism connected to the support frame. The base is provided with a support column connected to the support frame.

[0017] The support frame includes a receiving plate located above the support column, several support rods with their bottom ends set at the edge of the receiving plate, and several annular plates for preventing the rocket body from tilting. The several annular plates are sequentially sleeved on the support rods from bottom to top, and the bottom end of the booster abuts against the top surface of the receiving plate.

[0018] Furthermore, the bottom surface of the receiving plate is provided with a connecting lug, which is hinged to the side of the support column, and the bottom surface of the receiving plate is in contact with the support structure.

[0019] Furthermore, the support mechanism includes a plurality of cylinders disposed within the base, the cylinders being in contact with the bottom of the receiving plate.

[0020] The technical effects of this invention are as follows:

[0021] (1) The stabilizing mechanism of this scheme achieved the following results:

[0022] First: The blades and rotating column in the stabilization mechanism can maintain the stability of the rocket body during flight through the principle of gyroscopic effect, reducing the possibility of it flipping over during flight due to wind.

[0023] Second: The stabilization mechanism can work with the air intake. When the booster is not separated from the rocket body, outside air will enter the rocket body through the air intake and form a downward blowing wind, which will cause the fan blades in the stabilization mechanism to rotate, thereby driving the rotating column to rotate and keeping the rocket body stable.

[0024] Third: The stabilization mechanism can work in conjunction with the ventilation mechanism. After the boosters separate, the baffle rises to block the air intake. At the same time, the expanded air will enter the rocket body through the ventilation mechanism, allowing the stabilization mechanism to continue rotating, thus ensuring that the rocket body maintains stability during flight.

[0025] (2) The lifting mechanism in this solution achieves the following technical effects:

[0026] First: When the booster is not separated from the rocket body, on the one hand, the slot of the lifting rod cooperates with the plug on the booster to connect the booster to the lifting rod, thereby completing the connection with the rocket body; on the other hand, the plug connected to the lifting rod will be inserted into the socket of the first air supply pipe, blocking the flow of liquid air, preventing liquid air from flowing out of the first air supply pipe, and reducing the loss of liquid air.

[0027] Second: When the booster separates from the rocket body, the lifting rod rises under the action of spring two, completing the separation from the booster, and also driving the insertion block to rise. The insertion block separates from the insertion port, allowing the liquid air in the air supply pipe one to flow out, thereby enabling the rocket body to obtain thrust from the air.

[0028] Third: After the lifting boom is raised, the baffle set on the lifting boom will block the air intake, preventing external air from entering the rocket body and reducing the drag of the rocket body during flight;

[0029] (3) The gas supply mechanism in this scheme has achieved the following results:

[0030] First: When the liquid air flowing out of the gas supply mechanism encounters the high-temperature flame ejected from the nozzle, it will expand rapidly due to the heat, thereby providing thrust to the rocket body at the tail end, enabling the rocket to fly with a reduced fuel load, thus reducing environmental pollution.

[0031] Second: Some of the air that has expanded due to heat will be delivered to the ventilation mechanism through the second air supply pipe and ejected from the opening on the side of the fan blades, providing the fan blades with the power to rotate, thereby enabling the stabilizing mechanism to continue to work.

[0032] (4) The booster in this scheme has the following effects:

[0033] First: When the booster's engine is working, the flames and airflow it ejects will exert thrust on the heat shield on the side, causing the heat shield to rotate at a certain angle, so that the plug on the tail fin can be inserted into the slot, completing the connection with the rocket body, and enabling the booster to provide thrust for the rocket body to fly.

[0034] Second: When the booster runs out of fuel, the heat shield loses the thrust of the airflow and will rotate under the push of spring one, causing the tail fin connected to the heat shield to rotate, causing the plug to separate from the slot, thus completing the automatic separation of the booster from the rocket body.

[0035] (5) After the booster separates from the rocket body, the lifting mechanism will rise to enable the air supply mechanism to work. Then the air supplied by the air supply mechanism will drive the stabilization mechanism through the ventilation mechanism, thus realizing the integration of the working process. Attached Figure Description

[0036] Figure 1 This is a schematic diagram of the overall structure of the rocket body and booster in this invention.

[0037] Figure 2 This is a schematic diagram of a partial internal structure of the rocket body in this invention. Figure 1 .

[0038] Figure 3This is a schematic diagram of a partial internal structure of the rocket body in this invention. Figure 2 .

[0039] Figure 4 This is a schematic diagram of the booster structure in this invention.

[0040] Figure 5 This is a partial structural diagram of the booster's interior in this invention.

[0041] Figure 6 This is a schematic diagram of the base structure in this invention.

[0042] Figure 7 This is a partial structural diagram of the base in this invention.

[0043] The attached diagrams are as follows: 1. Rocket body; 2. Liquid air tank; 3. Tail fin; 4. Booster shell; 5. Air inlet; 6. Baffle; 7. Spring II; 8. Connecting block; 9. Fixing column; 10. Lifting rod; 11. Air supply pipe I; 12. Air supply pipe II; 13. Fan blade; 14. Rotating column; 15. Insert block; 16. Slot; 17. Plug; 18. Base; 20. Support rod; 21. Annular plate; 22. Receiving plate; 23. Output shaft; 24. Support column; 25. Connecting lug; 26. Spring I; 27. Heat shield; 28. Engine. Detailed Implementation

[0044] The technical solution of the present invention will be clearly and completely described below with reference to specific embodiments and accompanying drawings.

[0045] See Figure 1 A rocket aerodynamic flight experiment simulation device includes a base, a rocket body 1 mounted on the base, a rocket engine mounted inside the rocket body 1, a booster mounted on the rocket body 1, an air supply mechanism mounted on the rocket body 1 for providing power to the rocket body 1, a ventilation mechanism connected to the air supply mechanism for driving a stabilization mechanism, a stabilization mechanism connected to the ventilation mechanism for maintaining the stability of the rocket body 1, and a lifting mechanism attached to the air supply mechanism. The stabilization mechanism is rotatably mounted inside the rocket body 1.

[0046] Furthermore, the stabilizing mechanism includes a fixed column 9 vertically installed inside the rocket body 1, a rotating block rotatably installed at the top of the fixed column, and several fan blades 13 installed on the side of the rotating block. The bottom surface of the rotating column 14 is fixed to the top surface of the rotating block.

[0047] Furthermore, the ventilation mechanism includes a ventilation duct 1 housed within the fixed column 9, a ventilation duct 2 housed within the rotating block and connected to the ventilation duct 1, and a ventilation duct 3 housed within the fan blade 13 and connected to the ventilation duct 2. Figure 2 The circle on the middle fan blade 13 is the opening end of ventilation duct three in this scheme;

[0048] The opening end of ventilation duct one is located on the top surface of the fixed column 9, the opening ends of ventilation duct two are located on the bottom and side surfaces of the rotating block respectively, and the opening end of ventilation duct three is located on one side and end face of the fan blade 13. The air supply mechanism is connected to the fixed column 9 and communicates with ventilation duct one.

[0049] See Figure 3 The gas supply mechanism includes a liquid air tank 2 located on the outside of the rocket body 1, a gas supply pipe 11 connected to the liquid air tank 2 at one end, the other end of the gas supply pipe 11 connected to the nozzle at the tail end of the rocket body 1, a gas supply pipe 2 at one end connected to the gas supply pipe 11, and the other end of the gas supply pipe 212 connected to the fixed column 9 and connected to the ventilation duct 1.

[0050] An inlet is provided on the gas supply pipe 11, and the inlet is connected to the gas supply pipe 11. The lifting mechanism is connected to the inlet.

[0051] See Figure 2 A connecting block 8 is vertically arranged inside the rocket body 1, and a through groove is vertically arranged inside the connecting block 8. The lifting mechanism includes a lifting rod 10 that is slidably arranged in the through groove, a slot 16 that is arranged at the tail end of the lifting rod 10, a baffle 6 that is arranged at the top end of the lifting rod 10, and a spring 7 that is sleeved on the outside of the lifting rod 10 and whose top end is arranged on the baffle 6. The bottom end of the spring 7 is arranged on the top surface of the connecting block 8, and the plug 17 is connected to the booster.

[0052] An air inlet 5 is provided on the outer side of the rocket body 1. The air inlet 5 is connected to the interior of the rocket body 1. A baffle 6 is used to block the air inlet 5. The side of the connecting rod is also connected to a vertically arranged insert 15. The insert 15 is inserted into the socket to block the flow of liquid air.

[0053] See Figure 4 , Figure 5 The booster includes a booster housing 4, an engine 28 located below the booster, and a heat shield 27 located inside the booster housing 4 and on the side of the engine 28. The inner side of the booster housing 4 is connected to one end of a spring 26, and the other end of the spring 26 is connected to the heat shield 27. A tail fin 3 is provided above the heat shield 27. The tail fin 3 is hinged to the side of the booster housing 4. A plug 17 is provided on the tail fin 3 and is inserted into a slot 16, thereby connecting the booster to the rocket body.

[0054] Furthermore, a controller is installed inside the rocket body 1. The controller is connected to the rocket engine and also to a timer. The operator can pre-control the fuel in the booster, control the booster's working time, and input the data into the controller.

[0055] See Figure 6The base includes a base 18, a support frame disposed on the base 18 for supporting the rocket body 1, and a support mechanism connected to the support frame. A support column 24 connected to the support frame is disposed on the base 18.

[0056] The support frame includes a receiving plate 22 located above the support column 24, several support rods 20 with their bottom ends set at the edge of the receiving plate 22, and several annular plates 21 for preventing the rocket body 1 from tilting. The several annular plates 21 are sequentially sleeved on the support rods 20 from bottom to top. The bottom end of the booster abuts against the top surface of the receiving plate 22. Preferably, in this embodiment, the top surface of the receiving plate 22 is provided with a top block. When placing the booster on the receiving plate 22, the heat insulation plate 27 can be separated by hand first, and then placed on the receiving plate 22. The top block is placed inside the several heat insulation plates 27 to hold the heat insulation plates 27 in place, preventing the heat insulation plates 27 from rotating under the push of the spring 26 and causing the plug 17 to fall out of the slot 16.

[0057] See Figure 7 The bottom surface of the receiving plate 22 is provided with a connecting ear 25, which is hinged to the side of the support column 24, and the bottom surface of the receiving plate 22 is in contact with the support structure.

[0058] Furthermore, the support mechanism includes several cylinders disposed within the base 18, which contact the bottom of the receiving plate 22.

[0059] The working process of this invention is as follows:

[0060] Adjust the cylinder to change the height of the cylinder output shaft 23, so that the support frame and the rocket body 1 are tilted at a certain angle. After adjusting the angle, prepare for launch. At this time, the plug 17 is inserted into the slot 16, and the booster is connected to the lifting mechanism. Then, start the timer and booster to ignite the booster and launch. The booster will propel the rocket body 1 to fly. At this time, the thrust of the jet air is greater than the thrust of the spring 26.

[0061] During flight, some airflow from the outside of the rocket body 1 enters the rocket body 1 through the air inlet 5, forming a wind that blows towards the fan blade 13, causing the fan blade 13 to rotate, which in turn drives the rotating column 14 to rotate, keeping the rocket body 1 stable. Preferably, in this embodiment, the top surface of the rotating column 14 is rotatably connected to one end of the connecting shaft, and the other end of the connecting shaft is located inside the rocket body 1.

[0062] When the booster runs out of fuel, the heat shield 27 will rotate through the hinge between the tail fin 3 and the booster housing 4 under the push of the spring 26, thereby causing the tail fin 3 connected to the heat shield 27 to rotate and the plug 17 to separate from the slot 16. Preferably, the side of the booster housing 4 is provided with an opening slot corresponding to the tail fin 3, so that the tail fin 3 can move in the opening slot when it rotates. At this time, the timer time is the time preset by the operator in the controller, and the controller will start the rocket launcher.

[0063] After the plug 17 separates from the slot 16, the baffle 6 rises under the push of the second spring 7, blocking the air inlet 5 and reducing the drag during rocket flight. The baffle 6 will also drive the lifting rod 10 to rise, causing the plug block 15 connected to the lifting rod 10 and located in the first air supply pipe 11 to rise. The liquid air in the liquid air tank 2 will flow into the jet port at the tail end of the rocket body 1 along the first air supply pipe 11.

[0064] When liquid air comes into contact with the high-temperature flame and airflow ejected from the rocket body 1, it will expand due to heat, thereby applying thrust to the tail end of the rocket body 1. Part of the expanded air will enter the ventilation duct 1 through the second air supply pipe 12, and then pass through the second and third ventilation ducts in sequence, and be blown out from the opening end on the side of the third ventilation duct, thereby applying power to the fan blade 13, so that the fan blade 13 can continue to drive the rotating column 14 to rotate, thereby enabling the rocket body 1 to continue to remain stable.

[0065] The above embodiments are merely preferred embodiments of the present invention. Those skilled in the art can obtain other embodiments from the above embodiments without creative effort. Therefore, this application not only protects the above embodiments, but also protects the scope consistent with the principles and features of this solution.

Claims

1. A rocket aerodynamic flight experiment simulation device comprising a base, a rocket body (1) provided on the base, a rocket engine provided in the rocket body (1), a booster provided on the rocket body (1), characterized in that, It also includes an air supply mechanism disposed on the rocket body (1) and used to provide power to the rocket body (1), a ventilation mechanism connected to the air supply mechanism and used to drive the stabilization mechanism, a stabilization mechanism connected to the ventilation mechanism and used to maintain the stability of the rocket body (1), and a lifting mechanism attached to the air supply mechanism. The lifting mechanism is detachably connected to the booster, and the stabilization mechanism is rotatably disposed inside the rocket body (1). The stabilizing mechanism includes a fixed column (9) vertically disposed within the rocket body (1), a rotating block rotatably disposed at the top of the fixed column (9), and several fan blades (13) disposed on the side of the rotating block. The bottom surface of the rotating column (14) is fixed to the top surface of the rotating block. The ventilation mechanism includes a ventilation duct 1 located in the fixed column (9), a ventilation duct 2 located in the rotating block and connected to the ventilation duct 1, and a ventilation duct 3 located in the fan blade (13) and connected to the ventilation duct 2. The opening end of the ventilation duct one is located on the top surface of the fixed column (9), the opening ends of the ventilation duct two are respectively located on the bottom surface and side surface of the rotating block, the opening end of the ventilation duct three is located on one side and end face of the fan blade (13), the air supply mechanism is connected to the fixed column (9) and communicates with the ventilation duct one. The gas supply mechanism includes a liquid air tank (2) located outside the rocket body (1), a gas supply pipe (11) with one end connected to the liquid air tank (2), the other end of the gas supply pipe (11) being connected to the nozzle at the tail end of the rocket body (1), a gas supply pipe (2) with one end connected to the gas supply pipe (11), and the other end of the gas supply pipe (2) being connected to the fixed column (9) and connected to the ventilation duct (1). The first gas supply pipe (11) is provided with an inlet, the inlet is connected to the first gas supply pipe (11), and the lifting mechanism is connected to the inlet; A connecting block (8) is vertically arranged inside the rocket body (1), and a through groove is vertically arranged inside the connecting block (8). The lifting mechanism includes a lifting rod (10) slidably arranged in the through groove, a slot (16) arranged at the tail end of the lifting rod (10), a baffle (6) arranged at the top end of the lifting rod (10), a second spring (7) sleeved on the outside of the lifting rod (10) and with its top end arranged on the baffle (6). The bottom end of the second spring (7) is arranged on the top surface of the connecting block (8), and the plug (17) is connected to the booster. An air inlet (5) is provided on the outside of the rocket body (1), and the air inlet (5) is connected to the inside of the rocket body (1). The side of the lifting rod (10) is connected to the plug (15) through a connecting rod, and the plug (15) is inserted into the socket. The booster includes a booster housing (4), an engine (28) disposed below the booster housing (4), and a heat shield (27) disposed inside the booster housing (4) and located on the side of the engine (28). The inner side of the booster housing (4) is connected to one end of a spring (26), and the other end of the spring (26) is connected to the heat shield (27). A tail fin (3) is disposed above the heat shield (27), and the tail fin (3) is hinged to the side of the booster housing (4). A plug (17) is disposed on the tail fin (3), and the plug (17) is inserted into the slot (16).

2. The rocket-powered flight experimental simulation apparatus according to claim 1, characterized by The rocket body (1) is equipped with a controller, which is connected to the rocket engine and also connected to a timer.

3. The rocket-powered aerodynamic flight experiment simulation apparatus of claim 1, wherein, The base includes a base (18), a support frame disposed on the base (18) for supporting the rocket body (1), and a support mechanism connected to the support frame. The base (18) is provided with a support column (24) connected to the support frame. The support frame includes a receiving plate (22) located above the support column (24), a number of support rods (20) with their bottom ends set at the edge of the receiving plate (22), and a number of annular plates (21) for preventing the rocket body (1) from tilting. The number of annular plates (21) are sequentially sleeved on the support rods (20) from bottom to top, and the bottom end of the booster abuts against the top surface of the receiving plate (22).

4. The rocket-powered flight experimental simulation apparatus according to claim 3, characterized by The bottom surface of the receiving plate (22) is provided with a connecting ear (25), which is hinged to the side of the support column (24), and the bottom surface of the receiving plate (22) is in contact with the support mechanism.

5. The rocket-powered aerodynamic flight experiment simulation apparatus of claim 3, wherein, The support mechanism includes a plurality of cylinders disposed in the base (18), the cylinders being in contact with the bottom of the receiving plate (22).

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