Horizontal flying water rocket, launching system and launching method

Abstract

The application belongs to the field of teaching demonstration supplies, and particularly relates to a horizontal flight water fire arrow, a launching system and a launching method, wherein the horizontal flight water fire arrow comprises an arrow body and a bend pipe; the arrow body is internally provided with a cavity, and the arrow body is further provided with a gas filling nozzle II and a nozzle which are in communication with the cavity; the bend pipe is arranged in the cavity, one end of the bend pipe is in communication with the nozzle, and the other end is arranged in abutment with the inner side wall of the cavity after being bent. The application can realize small-inclination or horizontal launching and flight of the water fire arrow by arranging the bend pipe, and provides a launching and flight mode which is different from conventional water fire arrows.

Description

Technical Field

[0001] This invention belongs to the field of teaching demonstration products, specifically relating to a horizontally flying water rocket, a launch system, and a launch method. Background Technology

[0002] Water rockets are used as a teaching tool for scientific research. Because they are inexpensive, can stimulate students' creativity, are fun, and are relatively safe due to the availability of water and air, water rocket design competitions are frequently held in junior high schools, high schools, and some universities.

[0003] Currently, water rockets can only be launched vertically or at a large angle due to the weight of water, and cannot be launched horizontally or at a small angle. In addition, the pressure of current water rockets is usually low, the propulsion system is not strong, and the weight of the rocket itself is large. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to provide a horizontally flying water rocket, a launch system and a launch method that can be launched and flown horizontally.

[0005] This invention provides a horizontally flying water rocket, comprising a rocket body and a curved tube;

[0006] The arrow body has a hollow cavity inside, and an air inlet II and a nozzle that communicate with the cavity are also provided on the arrow body;

[0007] The bent tube is installed inside the cavity, with one end connected to the nozzle and the other end bent to fit against the inner side wall of the cavity.

[0008] Furthermore, the present invention also includes a piston, which is slidably and sealingly disposed within the cavity and divides the cavity into a secondary cavity and a main cavity;

[0009] The inflation nozzle II and the nozzle are connected to the main cavity, and the rocket body is provided with an inflation nozzle I that is connected to the secondary cavity;

[0010] The bent tube is installed inside the main cavity. One end of the bent tube is connected to the nozzle, and the other end is bent and fitted to the inner side wall of the main cavity.

[0011] Furthermore, the present invention also includes an airbag disposed within the secondary cavity and communicating with the inflation nozzle I.

[0012] Furthermore, the bent pipe includes a liquid inlet, a bent connecting part, and a liquid outlet connected in sequence. The liquid inlet and the liquid outlet are arranged in parallel, and the inlet direction of the liquid inlet is parallel to the axis of the arrow body.

[0013] Furthermore, the nozzle is positioned on the central axis of the arrow body.

[0014] Furthermore, the nozzle includes a through hole I disposed on the arrow body and a plug disposed on the through hole I.

[0015] Furthermore, the present invention also includes a nozzle control mechanism for controlling the plug to block or open the through hole I.

[0016] The present invention also provides a launch system, including a horizontally flying water rocket and a launch platform, wherein the horizontally flying water rocket and the launch platform are connected by a guide rail slider.

[0017] Furthermore, the launch platform is mounted on a drone.

[0018] The present invention also provides a method for launching a horizontally flying water rocket, which uses a horizontally flying water rocket and includes the following steps:

[0019] A set volume of liquid is injected into the main chamber through the nozzle, and the nozzle is closed after the injection is complete.

[0020] The main chamber is pressurized to the set pressure through air inlet II, and the secondary chamber is pressurized to the set pressure through air inlet I;

[0021] Open the nozzle, and the water vapor ejected from the nozzle will generate a reaction force that propels the arrow forward.

[0022] The beneficial effect of this invention is that, by setting up a curved tube, it can achieve small-angle or horizontal launch and flight of water rockets, providing a launch and flight method that differs from conventional water rockets. Attached Figure Description

[0023] Appendix Figure 1 This is a schematic diagram of the water rocket in this invention;

[0024] Appendix Figure 2 This is a frontal sectional view of the water rocket in this invention;

[0025] Appendix Figure 3 for Figure 2 A magnified view of a section at point A in the middle;

[0026] Appendix Figure 4 for Figure 2 A magnified view of a section at point B in the middle;

[0027] Appendix Figure 5 This is a schematic diagram of the launch platform in this invention;

[0028] Appendix Figure 6 This is a front view of the launch platform in this invention;

[0029] Appendix Figure 7 This is a side sectional view of the launch platform in this invention;

[0030] Appendix Figure 8This is a frontal sectional view of the water rocket in the present invention when it is installed on the launch platform;

[0031] Appendix Figure 9 for Figure 8 A close-up view of the mid-tail section;

[0032] Appendix Figure 10 This is a frontal cross-sectional view of the airbag in the water rocket after pressurization in this invention;

[0033] Appendix Figure 11 This is a frontal sectional view of the water rocket during takeoff in this invention;

[0034] Appendix Figure 12 for Figure 11 A close-up view of the mid-tail section;

[0035] Appendix Figure 13 This is a frontal sectional view of the water rocket separating from the launch platform in this invention;

[0036] Appendix Figure 14 for Figure 13 A close-up view of the mid-tail section;

[0037] Appendix Figure 15 This is a schematic diagram of the airborne water rocket in this invention.

[0038] In the diagram, 1-rocket body; 11-secondary cavity; 12-main cavity; 13-nose cone; 14-tail fin; 2-piston; 21-sealing ring; 3-inflation nozzle I; 4-inflation nozzle II; 5-nozzle; 51-through hole I; 52-plug; 6-bend; 61-liquid inlet; 62-bent connection; 63-liquid outlet; 7-launch platform; 71-guide rail plate; 72-mounting plate; 721-through hole II; 722-inflation through hole; 8-UAV; 9-nozzle control mechanism; 91-ring electromagnet; 92-electric control box; 10-liquid; 101-high pressure gas; 102-guide rail; 103-slider; 104-airbag. Detailed Implementation

[0039] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0040] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indication will also change accordingly.

[0041] Furthermore, in this invention, descriptions involving "first," "second," etc., are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0042] In this invention, unless otherwise explicitly specified and limited, the terms "connection," "fixed," etc., should be interpreted broadly. For example, "fixed" can mean a fixed connection, a detachable connection, or an integral part; it can mean a mechanical connection, an electrical connection, a physical connection, or a wireless communication connection; it can mean a direct connection or an indirect connection through an intermediate medium; it can mean the internal communication of two elements or the interaction between two elements, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0043] Furthermore, the technical solutions of the various embodiments of the present invention can be combined with each other, but only if they are feasible for those skilled in the art. If the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such combination of technical solutions does not exist and is not within the scope of protection claimed by the present invention.

[0044] As attached Figure 1-15 As shown, the present invention provides a horizontally flying water rocket, including a rocket body 1 and a curved tube 6;

[0045] The rocket body 1 has a hollow cavity inside. The rocket body 1 is also provided with an air inlet II4 and a nozzle 5 that communicate with the cavity. The air inlet II4 is used to pressurize the cavity and is preferably a one-way air inlet valve. The nozzle 5 is preferably located at one end of the rocket body 1 and is used to inject water into the cavity and to spray water vapor during flight to provide flight power.

[0046] The bent tube 6 is installed inside the cavity. One end of the bent tube 6 is connected to the nozzle 5, and the other end is bent and fitted to the inner side wall of the cavity.

[0047] By incorporating a bend 6, this invention enables water rockets to be launched and flown at small angles or horizontally, providing a launch and flight method distinct from conventional water rockets.

[0048] In one embodiment, the invention further includes a piston 2, which is slidably disposed in the cavity and divides the cavity into a secondary cavity 11 and a main cavity 12.

[0049] The inflation nozzle II4 and the nozzle 5 are connected to the main cavity 12, and the rocket body 1 is provided with an inflation nozzle I3 that is connected to the secondary cavity 11;

[0050] The bent tube 6 is installed inside the main cavity 12. One end of the bent tube 6 is connected to the nozzle 5, and the other end is bent and fitted to the inner side wall of the main cavity 12.

[0051] In this embodiment, by sealing and sliding the piston 2 within the cavity, the cavity is divided into a secondary cavity 11 and a main cavity 12 that are isolated from each other. Before flight, a set volume of liquid 10 is first injected into the main cavity 12 through the nozzle 5. After injection, the nozzle is closed, and then the remaining space in the main cavity 12 is pressurized through the inflation nozzle II 4. After pressurization is complete, the secondary cavity 11 is pressurized through the inflation nozzle I 3. At this time, according to the pressure changes in the secondary cavity 11 and the main cavity 12, the piston 2 will move along the cavity axis and maintain... To ensure pressure balance between the secondary chamber 11 and the main chamber 12, the pressure of the main chamber 12 can be regulated by pressurizing the secondary chamber 11. At the same time, the initial position of the piston 2 can be controlled by controlling the pressure applied to the secondary chamber 11. Alternatively, the secondary chamber 11 can be pressurized first, and then the main chamber 12 can be pressurized to adjust the initial position of the piston 2. Specifically, the initial position of the piston 2 is usually located at 1 / 3 to 1 / 2 of the chamber length to avoid occupying too much of the volume of the main chamber 12 and to increase the water capacity.

[0052] During flight, the liquid 10 and high-pressure gas 101 injected into the main cavity 12 are ejected through the nozzle 5, generating thrust on the rocket body 1. Since the water in the main cavity 12 is connected to the nozzle 5 via the bend 6, the water rocket can be launched and flown at a small angle or horizontally. During flight, as the pressure in the main cavity 12 gradually decreases, the pressure in the secondary cavity 11 becomes higher than that in the main cavity 12, pushing the piston 2 towards the main cavity 12. This maintains pressure balance in the main cavity 12, ensuring sufficient thrust during flight. The system operates smoothly and partially compensates for the pressure loss in the main cavity 12, ensuring the thrust provided by the main cavity 12 and further enhancing the kinetic energy and speed of the water rocket. Simultaneously, the volume of the main cavity 12 gradually decreases, preventing the water level of the remaining liquid 10 within the main cavity 12 from dropping too quickly or too low. Under certain conditions, the water level in the main cavity 12 can accumulate and rise during horizontal flight, ensuring that the water level remains above the diameter of the liquid inlet 61 of the bend 6. This allows water to be smoothly ejected from the bend 6 throughout the entire jetting process, maintaining the kinetic energy and speed of the water rocket. Conventional rockets launch vertically upwards from the ground. This results in a significant decrease in internal pressure and a large mass. Furthermore, upward flight requires overcoming both air resistance and gravity, leading to high speeds and a sharp drop in velocity, resulting in short flight times and low speeds. This embodiment effectively overcomes these problems.

[0053] In addition, at the same flight distance and speed, the liquid 10 volume in this invention can be less than that required by conventional water rockets, thereby reducing the water rocket's own weight and further increasing the flight distance and speed.

[0054] In one embodiment, the bend 6 includes a liquid inlet 61, a bent connecting part 62, and a liquid outlet 63 connected in sequence. The liquid inlet 61 and the liquid outlet 63 are arranged in parallel, and the inlet direction of the liquid inlet 61 is parallel to the axis of the rocket body 1. At this time, the rocket body 1 is placed horizontally, the liquid 10 is located in the lower part of the main cavity 12, and the high-pressure gas 101 is located in the upper part of the main cavity 12. The high-pressure gas 101 will push the liquid 10 into the liquid inlet 61 and the bent connecting part 62 in sequence, and finally spray it out at the liquid outlet 63 to form the thrust of the water rocket. In this embodiment, the two parallel liquid inlet 61 and liquid outlet 63 are connected by the bent connecting part 62, which can avoid pressure loss along the way and reduce kinetic energy loss. At the same time, the inlet direction of the liquid inlet 61 being parallel to the axis of the rocket body 1 facilitates the inflow of liquid 10.

[0055] In one embodiment, the curved tube 6 is rotatably connected to the inner wall of the rocket body 1, or the curved connecting part 62 is rotatably connected to the liquid outlet part 63. In this way, when the rocket body 1 rotates along its own axis, the liquid 10 and the liquid inlet part 61 of the curved tube 6 are rotated to the lower part of the main cavity 12 by gravity, ensuring the stability of the liquid 10 ejection, thereby realizing the horizontal rotation flight of the water rocket.

[0056] In one embodiment, the nozzle 5 is disposed on the central axis of the rocket body 1 to ensure that the spray center is located on the axis of the water rocket, thereby ensuring the flight stability of the water rocket and ensuring that the water rocket is driven to fly horizontally in a straight line in terms of thrust.

[0057] In one embodiment, the present invention further includes an airbag 104 disposed in the secondary cavity 11 and communicating with the inflation nozzle I3. In this embodiment, pressurizing the airbag 104 instead of pressurizing the secondary cavity 11 can reduce the sliding sealing requirements of the piston 2. Specifically, the airbag 104 is made of elastic plastic material and is inflated and pressurized through the inflation nozzle I3. After the airbag 104 expands, it fits against the cavity wall of the secondary cavity 11 and expands. When the piston 2 moves, the space of the secondary cavity 11 increases laterally, and the airbag 104 expands accordingly until the pressure inside the airbag 104 is equal to the pressure inside the main cavity 12.

[0058] In one embodiment, the nozzle 5 includes a through hole I 51 disposed on the arrow body 1 and a plug 52 disposed on the through hole I 51. The combination of the plug 52 and the through hole I 51 can ensure the simple structure of the nozzle 5, and at the same time facilitate the control of the blocking and opening of the through hole I 51. Specifically, before water is injected into the main cavity 12, the plug 52 is opened and water is injected into the main cavity 12 through the through hole I 51. After water is injected, the through hole I 51 is blocked by the plug 52 to ensure the sealing of the main cavity 12. Then, the secondary cavity 11 and the main cavity 12 are pressurized.

[0059] In one embodiment, the invention further includes a nozzle control mechanism 9 for controlling the plug 52 to block or open the through hole I 51, so as to control the water rocket to start flight. In a specific embodiment, the nozzle control mechanism 9 adopts a combination of annular electromagnet 91 and electrical control box 92. The electrical control box 92 is used to control the annular electromagnet 91 to be energized and de-energized. At this time, the plug 52 is made of iron material, such as iron. The annular electromagnet 91 is set on the water rocket launch platform 7 and located at the through hole I 51. After the plug 52 is inserted into the through hole I 51, the electrical control box 92 controls the annular electromagnet 91 to be energized and attract the plug 52 to fix the position of the plug 52 and keep the plug 52 blocking the through hole I 51. When it is necessary to control the water rocket to start flight, the electrical control box 92 controls the annular electromagnet 91 to be de-energized, and the plug 52 loses its restraining force. At this time, the liquid 10 is thrust by the high-pressure gas 101 and is ejected from the bend 6 to form thrust and realize the flight of the water rocket. In this embodiment, the plug 52 and the through hole I 51 can be sealed by a sealing ring. Thus, the opening of the nozzle 5 does not waste the thrust of the liquid 10, which can save a small amount of thrust and increase the flight distance of the water rocket. In addition, the combination of the nozzle 5 and the nozzle control mechanism 9 is also quite simple and convenient. It can be released simply and reliably with just one control command. The reusability and low cost of the water rocket are also retained.

[0060] In one embodiment, the cavity is a cylindrical cavity, which facilitates the sealing and sliding fit of the piston 2, and the arrow body 1 is also cylindrical in shape. The front part of the arrow body 1 is provided with a head cone 13, and the rear part of the arrow body 1 is provided with a tail fin 14 to improve the flight effect.

[0061] In one embodiment, a sealing ring 21 is provided on the side wall of the piston 2, and the sealing ring 21 contacts the inner wall of the cavity to improve the sealing effect of the piston 2.

[0062] The present invention also provides a launch system, including a horizontally flying water rocket and a launch platform 7, wherein the horizontally flying water rocket and the launch platform 7 are connected by a guide rail slider, and further includes a nozzle control mechanism 9 for controlling the opening and operation of the nozzle 5.

[0063] This launch system can provide a certain degree of guidance for the straight flight of the water rocket during takeoff, preventing the water rocket from deviating from its course. In addition, it provides installation space for the nozzle control mechanism 9. Specifically, the launch platform 7 includes a guide rail plate 71 and a mounting plate 72. The mounting plate 72 is perpendicular to the guide rail plate 71 and is located at one end of the guide rail plate 71. A guide rail 102 is provided on the side of the guide rail plate 71 near the mounting plate 72. A slider 103 is provided on the upper part of the rocket body 1, and the slider 103 is slidably engaged in the guide rail 102. The mounting plate 72 has a through hole II 721 at its center. A ring electromagnet 91 is located on the outside of the through hole II 721. The mounting plate 72 also has an inflation through hole 722. When the tail of the arrow body 1 slides to the mounting plate 72, the through hole I 51 and the through hole II 721 are aligned, and the inflation nozzle II 4 is aligned with the inflation through hole 722. After water is injected through the through hole I 51, the plug 52 is inserted from the through hole II 721 into the through hole I 51. The electrical control box 92 controls the ring electromagnet 91 to be energized to fix the position of the plug 52. In addition, when the plug 52 and the through hole 51 are simply sealed together, the radial fitting force of the plug 52 and the through hole 51 meets the sealing requirements, but the axial fitting force of the plug 52 and the through hole 51 is small. When the pressure inside the cavity is large, the rocket body 1 will be vibrated and fly forward while the plug 52 remains in place. Therefore, the plug 52 can be pressurized with the through hole 51, or a rocket body position fixing mechanism can be set on the guide rail and the slider to prevent the rocket body 1 from flying forward actively after the secondary cavity 11 and the main cavity 12 are pressurized. The rocket body positioning mechanism can be an electromagnet mounted on the guide rail plate 71. In this case, the slider 103 is made of iron. The electromagnet is controlled by the control box 92 to fix the position of the slider 103 at the set position of the guide rail 102. When the water rocket is installed on the launch platform 7, the control box 92 controls the electromagnet to attract the slider 103 and limit the position of the slider 103, and controls the annular electromagnet 91 to attract the plug 52 and limit the position of the plug 52. When the water rocket is started, the control box 92 controls the electromagnet and the annular electromagnet 91 to be de-energized at the same time. As the plug 51 is released, the slider 103 moves along the guide rail 102.

[0064] In one embodiment, the launch platform 7 is mounted on a drone 8, enabling airborne horizontal launch of the water rocket. The drone 8 can be a rotary-wing or fixed-wing drone. In this embodiment, the water rocket can utilize the power and potential energy of the drone 8 to achieve a longer flight distance and higher speed. Furthermore, because the water rocket can achieve horizontal launch and flight, it can be launched using the drone 8, thus achieving high-speed flight at low cost for related scientific research or entertainment purposes. Additionally, in this embodiment, the flight driving force of the water rocket does not exert a reverse thrust on the drone 8. The force exerted by the rocket body 1 on the drone 8 is the frictional force of the slider 103 on the guide rail 102, which is negligible. Therefore, the launch platform 7 can launch stably, and the launch moment will not generate a large force on the drone 8, ensuring the safety of the drone 8.

[0065] The present invention also provides a method for launching a horizontally flying water rocket, which uses a horizontally flying water rocket and includes the following steps:

[0066] A set volume of liquid 10 is injected into the main chamber 12 through nozzle 5, and nozzle 5 is closed after the injection is completed.

[0067] The main chamber 12 is pressurized to the set pressure through the air inlet II4, and the secondary chamber 11 is pressurized to the set pressure through the air inlet I3;

[0068] Open nozzle 5, and the water vapor ejected from nozzle 5 will generate a reaction force that propels the arrow body 1 forward.

[0069] like Figures 11-14 As shown, during the flight of the water rocket, the volume of the secondary cavity 11 gradually increases, while the volume of the main cavity 12 gradually decreases. The water level in the main cavity 12 remains basically unchanged, or even accumulates and rises, ensuring that the flight has continuous and reliable kinetic energy.

[0070] The specific working principle of a particular embodiment of the present invention is as follows:

[0071] First, the required amount of liquid 10 is injected into the main cavity 12 through the through hole I. Then, the rocket body 1 is mounted on the launch platform 7 of the UAV 8. After installation, the plug 52 is inserted into the through hole I 51 and fixed by the annular electromagnet 91, while simultaneously sealing the main cavity 12 of the rocket body 1. Then, the control box 92 controls the position of the electromagnet fixing slider 103.

[0072] Then, the main cavity 12 is inflated and pressurized through the inflation nozzle II4 at the rear end. Figure 8 state);

[0073] After pressurization is achieved, the air bladder 104 is inflated and pressurized through the inflation nozzle I3 at the front end of the rocket body 1. At this time, the air bladder 104 expands and pushes the piston 2 to move. The piston 2 stops after moving to a certain position, usually at 1 / 3 to 1 / 2 of the length of the rocket body 1. Figure 10 state);

[0074] When the annular electromagnet 91 is de-energized by the control box 92, the slider 103 is released from its position lock, and the plug 52 will fly backward under the pressure of the main cavity 12. Figure 11 (State), therefore, the liquid 10 in the main cavity 12 will also be ejected from the through hole I 51 under pressure ( Figure 13 (In this state), a counter-thrust is generated, propelling the water rocket forward. The pressure in the main chamber 12 decreases, causing the secondary chamber 11 to push the piston 2 backward, maintaining the pressure and water level in the main chamber 12. Liquid 10 is introduced through the curved pipe 6 into the center of the rocket body 1 and ejected backward, maintaining flight thrust and speed.

[0075] The contents not described in detail in this specification are existing technologies known to those skilled in the art.

Claims

1. A horizontal flight water rocket, characterized in that, The arrow body (1) and the elbow (6) are included. The arrow body (1) is internally hollowly provided with a cavity, and the arrow body (1) is further provided with a gas charging nozzle II (4) and a nozzle (5) which are communicated with the cavity. The elbow (6) is arranged in the cavity, one end of the elbow (6) is communicated with the nozzle (5), and the other end is arranged after being bent and adhering to the inner side wall of the cavity. Further, a piston (2) is arranged in the cavity in a sealed sliding mode, and the cavity is divided into a sub-cavity (11) and a main cavity (12). The gas charging nozzle II (4) and the nozzle (5) are communicated with the main cavity (12), and the arrow body (1) is provided with a gas charging nozzle I (3) which is communicated with the sub-cavity (11). The elbow (6) is arranged in the main cavity (12), one end of the elbow (6) is communicated with the nozzle (5), and the other end is arranged after being bent and adhering to the inner side wall of the main cavity (12). Before flight, a liquid (10) with a set volume is injected into the main cavity (12) through the nozzle (5), the nozzle is closed after the injection is completed, the remaining space in the main cavity (12) is pressurized through the gas charging nozzle II (4), and the sub-cavity (11) is pressurized after the pressurization is completed, at this time, according to the pressure changes in the sub-cavity (11) and the main cavity (12), the piston (2) moves along the axis of the cavity and ensures the pressure balance of the sub-cavity (11) and the main cavity (12). During flight, the liquid (10) and high-pressure gas (101) in the main cavity (12) are sprayed through the nozzle (5) and form a flight thrust on the arrow body (1) in the flight process, as the pressure of the main cavity (12) gradually decreases, at this time, the pressure of the sub-cavity (11) is higher than that of the main cavity (12) and pushes the piston (2) to move to the main cavity (12), maintains the pressure balance of the main cavity (12), stabilizes the thrust in the flight process, and partially supplements the pressure loss of the main cavity (12), ensures the thrust provided by the main cavity (12), and improves the kinetic energy and speed of the water rocket.

2. The horizontal flight water rocket according to claim 1, wherein Further, a gas bag (104) is arranged in the sub-cavity (11) and communicated with the gas charging nozzle I (3).

3. The horizontal flight water rocket according to claim 1 or 2, wherein The elbow (6) includes a liquid inlet portion (61), a bent connecting portion (62) and a liquid outlet portion (63) which are connected in sequence, the liquid inlet portion (61) and the liquid outlet portion (63) are arranged in parallel, and the inlet direction of the liquid inlet portion (61) is parallel to the axis of the arrow body (1).

4. The horizontal flight water rocket according to claim 1 or 2, wherein The nozzle (5) is arranged on the central axis of the arrow body (1).

5. The horizontal flight water rocket according to claim 1 or 2, wherein The nozzle (5) includes a through hole I (51) arranged on the arrow body (1) and a plug (52) arranged on the through hole I (51).

6. The horizontal flight water rocket of claim 5, wherein, Further, a nozzle control mechanism (9) is arranged to control the plug (52) to block or open the through hole I (51).

7. A transmitting system characterized by, The horizontal flight water rocket and the launching platform (7) are connected through a guide rail sliding block.

8. The launching system as claimed in claim 7, characterized in that, The launching platform (7) is arranged on an unmanned aerial vehicle (8).

9. A horizontal flight water rocket launching method, using the horizontal flight water rocket according to claim 1, including the following steps: Injecting liquid (10) into the main cavity (12) through the nozzle (5) with a set volume, and closing the nozzle (5) after the injection is completed; Pressurizing the main cavity (12) to a set pressure through the inflation nozzle II (4), and pressurizing the auxiliary cavity (11) to a set pressure through the inflation nozzle I (3); Opening the nozzle (5), and the water vapor ejected from the nozzle (5) forms a reaction force to push the arrow body (1) to move forward.

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