Water rocket testing system and method

Abstract

The application belongs to the field of water rocket testing, and particularly relates to a water rocket testing system and method, which comprises a power source assembly, a thrust device, a support and a connecting pipe. The power source assembly comprises a sealed cylinder and an inflator connected with each other, and the sealed cylinder is provided with a water injection mechanism. The thrust device is arranged on the support, and the support is further provided with a sensor for monitoring the state of the thrust device. One end of the connecting pipe is connected in a cavity of the thrust device, and the other end extends into the bottom of the sealed cylinder. The testing system provided by the application can realize long-time stable pressure or variable pressure thrust experiment of the thrust device, and the pressure and water quantity in the cavity will not sharply decrease when the nozzle is opened as in the conventional thrust device, thereby the power parameters of the thrust device can be observed and studied for a long time, the influence of the flowmeter on the thrust is excluded during the thrust experiment of the thrust device, the mass flow and other related parameters can be measured with high precision, and data support is provided for scientific research, so that the related model can be better corrected.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of water rocket testing, and particularly relates to a water rocket testing system and method. BACKGROUND

[0002] The current water rocket testing system has limited testing precision because the water pressure and water volume in the system decrease sharply and the whole process is not stable, and stable flow testing under certain pressure and nozzle diameter cannot be achieved, so effective data cannot be obtained to provide data support for subsequent models. In addition, due to the gravity of water, most of the current water rocket testing systems are vertically placed by testing assembly, and the weight of water changes during testing. Even if a flow device is added at the nozzle to measure and calculate, the nozzle thrust is still affected. SUMMARY

[0003] The application aims to provide a water rocket testing system and method capable of continuously obtaining effective experimental data.

[0004] The application provides a water rocket testing system, which comprises a power source assembly, a thrust device, a support and a connecting pipe.

[0005] The power source assembly comprises a sealed cylinder and an air compressor connected with each other, and the sealed cylinder is provided with a water injection mechanism.

[0006] The thrust device is arranged on the support, and the support is further provided with a sensor for monitoring the state of the thrust device.

[0007] One end of the connecting pipe is connected to the cavity of the thrust device, and the other end extends into the bottom of the sealed cylinder.

[0008] Further, the thrust device is horizontally arranged on the support.

[0009] Further, the support is provided with a horizontal roller, and the thrust device body of the thrust device is arranged on the horizontal roller.

[0010] Further, the support is further provided with side rollers at positions on both sides of the thrust device body of the thrust device.

[0011] Further, the application further comprises a force transmission support and a pressure sensor, one end of the force transmission support is connected with the thrust device head of the thrust device, the other end of the force transmission support is provided with the pressure sensor, and the other end of the pressure sensor is fixedly connected with the support.

[0012] Further, the upper part of the sealed cylinder is further provided with a pressure reducing valve.

[0013] Furthermore, the present invention also includes a control valve provided on the nozzle of the thrust device.

[0014] Furthermore, the control valve includes a base portion, a rotating portion and an electromagnet;

[0015] The base portion is provided with a channel I communicating with the nozzle;

[0016] The rotating part is rotatably arranged on the base part, and a channel II is provided on the rotating part. When the rotating part rotates to a set position, the channel II is connected with the channel I.

[0017] The electromagnet is fixedly arranged on the base portion, and a matching block is protruding from the rotating portion. The matching block is magnetically attracted to the electromagnet.

[0018] Furthermore, the end of the base portion is a ball head, the rotating portion is a ball seat, and a reset torsion spring is provided at the hinge between the ball seat and the ball head. After the mating block is separated from the adsorption of the electromagnet, the reset torsion spring resets the ball seat to the extreme position, and channel II is connected with channel I.

[0019] The present invention also provides a water rocket thrust testing method, using the above-mentioned water rocket testing system, comprising the following steps:

[0020] S1. Inject a set amount of water into the sealing cylinder through the water injection mechanism, or continuously inject water;

[0021] S2. Pressurize the sealing cylinder through the inflator and maintain or adjust the pressure in the sealing cylinder;

[0022] S3. Open the nozzle of the thrust device, and the thrust device performs a thrust experiment to obtain and record sensor data.

[0023] The beneficial effect of the present invention is that the test system provided in this application can realize long-term pressure stabilization or variable pressure thrust experiments of water rockets. Unlike conventional water rockets, the pressure and water volume in the cavity will not drop sharply when the nozzle is opened. Therefore, it can maintain a long time to observe and study the power parameters of the water rocket. It can also test the water rocket power system to eliminate the influence of the flow meter on the thrust, and can measure related parameters such as mass flow with high precision, providing data support for scientific research, so as to better correct related models. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Attachment Figure 1 It is a structural schematic diagram of the present invention;

[0025] Attachment Figure 2 Schematic diagram of the structure of the bracket and water rocket part of the present invention;

[0026] Attachment Figure 3 This is a schematic diagram of the structure of the closed state of the control valve in the present invention;

[0027] Figure 2 is a schematic view of the control valve in the open state according to the present application. Figure 4 Figure 3 is a schematic view of the control valve in the closed state according to the present application.

[0028] Figure 4 is a schematic view of the control valve in the open state according to the present application. Figure 5 Figure 5 is a schematic view of the control valve in the closed state according to the present application.

[0029] Figure 6 is a schematic view of the control valve in the open state according to the present application. Figure 6 Figure 7 is a schematic view of the control valve in the closed state according to the present application.

[0030] In the figure, 1 - power source assembly; 11 - sealing cylinder; 111 - water injection mechanism; 12 - air inflator; 2 - thrust device; 21 - thrust device body; 22 - cavity; 23 - thrust device head; 24 - nozzle; 3 - support; 31 - horizontal roller; 32 - side roller; 4 - connecting pipe; 41 - hose; 5 - pressure sensor; 6 - force transmission support; 7 - pressure sensor; 8 - pressure reducing valve; 9 - control valve; 91 - base part; 911 - channel I; 92 - rotating part; 921 - channel II; 922 - matching block; 93 - electromagnet; 94 - reset torsional spring. DETAILED DESCRIPTION

[0031] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application.

[0032] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present application are only used to explain the relative positional relationship, movement condition, etc. between components in a certain posture (as shown in the drawings), and if the certain posture changes, the directional indications also change accordingly.

[0033] In addition, the description such as "first", "second" and the like in the present application is only for the purpose of description, and cannot be understood as indicating or implying the relative importance of the indicated technical features or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first", "second" can explicitly or implicitly include at least one of the features. In the description of the present application, the meaning of "multiple" is at least two, such as two, three, etc., unless otherwise specifically limited.

[0034] In the present application, unless otherwise explicitly specified and limited, the terms "connection", "fixation" and the like shall be understood broadly, for example, "fixation" can be fixed connection, or detachable connection, or integral; can be mechanical connection, or electrical connection, or physical connection, or wireless communication connection; can be direct connection, or indirect connection through intermediate medium, can be internal communication of two elements or interaction relationship between two elements, unless otherwise explicitly limited. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0035] In addition, the technical solutions among various embodiments of the present application can be combined with each other, but it must be based on the fact that a person skilled in the art can realize it, when the combination of technical solutions appears contradictory or unachievable, it should be considered that the combination of technical solutions does not exist, nor is it within the scope of protection required by the present application.

[0036] As shown in the accompanying drawings Figures 1-6 The present application provides a water rocket test system, which comprises a power source assembly 1, a thrust device 2, a support 3 and a connecting pipe 4. The power source assembly 1 is used to continuously provide power source for the thrust device 2, so that long-time pressure constant or pressure change thrust test can be carried out. The thrust device 2 is a tested part, which is generally the power component of a water rocket, can maintain thrust for a long time, provides state data, and provides test data for the research and development of the thrust device 2. The support 3 is used to fix the thrust device 2, so as to ensure that the thrust device 2 does not move substantially. The connecting pipe 4 is used to continuously deliver the power source of the power source assembly 1 to the thrust device 2.

[0037] The thrust device 2 comprises a thrust device body 21, a cavity 22 is arranged in the thrust device body 21. The front part of the thrust device body 21 is a thrust device head 23, and a nozzle 24 connected with the cavity 22 is arranged at the tail part of the thrust device body 21.

[0038] The power source assembly 1 comprises a sealed cylinder 11 and an inflator 12 connected with each other. The sealed cylinder 11 is provided with a water injection mechanism 111. The water injection mechanism 111 is used to inject water into the sealed cylinder 11, which can be continuous injection or one-time injection of the water amount required for test maintenance time. In the case of continuous injection, the injection pressure needs to be greater than or equal to the inflation pressure of the inflator 12 to avoid pressure relief. In theory, continuous injection can make the thrust device 2 continuously test the thrust. In the case of one-time injection, the water injection mechanism 111 can be an opening arranged at the top of the sealed cylinder 11 and a plug capable of sealing the opening. After the water in the sealed cylinder 11 is used up in one-time injection, one test is completed. The inflator 12 is preferably a high-pressure inflator, and its inflation port is connected to the top of the sealed cylinder 11 to pressurize the space above the water level in the sealed cylinder 11. The sealed cylinder 11 adopts a large-capacity sealed cylinder to ensure the test time.

[0039] The thrust device 2 is arranged on the support 3, and sensors for monitoring the state of the thrust device 2 are also arranged on the support 3. The sensors can be a pressure sensor 5, a pressure sensor 7, a temperature sensor, a camera, etc. The pressure sensor 5 is used to monitor the thrust of the thrust device 2. The pressure sensor 7 is used to monitor the pressure in the cavity 22 of the thrust device 2. The temperature sensor and the camera can be used to monitor the temperature and icing state of the nozzle 24 of the thrust device 2. The state data of the thrust device 2 is obtained and recorded. Other sensors that can obtain the state of the water rocket thrust device 2 can also be used. Finally, the thrust pressure data is obtained, and the parameters of the thrust device 2 are obtained, which provides support for the design of water rockets and the like.

[0040] One end of the connecting pipe 4 is connected in the cavity 22 of the thrust device 2, and the other end extends into the bottom of the sealing cylinder 11. Preferably, a flexible pipe 41 is connected at the end of the connecting pipe 4 close to the thrust device 2, so as to avoid resistance during the thrust experiment of the thrust device 2 and affect the test precision. In a preferred embodiment, the flexible pipe 41 is perpendicular to the axis of the upper cavity 22 of the thrust device 2, so that the water jet of the flexible pipe 41 is perpendicular to the water jet direction of the nozzle 24, and the thrust formed by the water counter-thrust and the thrust formed by the flexible pipe 41 do not interfere with each other, thereby improving the test precision. The end of the connecting pipe 4 extending into the bottom of the sealing cylinder 11 is below the water level of the sealing cylinder 11, so that the entire sealing cylinder 11 and the inflator 12 serve as a continuous power source for the thrust device 2, and finally realize long-time stable pressure test or long-time variable pressure test. Stable pressure test can obtain stable and reliable thrust experimental data of the thrust device 2, and variable pressure test can simulate the thrust experimental state of the real thrust device 2 and obtain the thrust data of a certain thrust device 2. Specifically, during stable pressure test, the test system can test the flow under a certain pressure and nozzle diameter for a long time, and the pressure and water volume in the cavity 22 of the thrust device 2 will not decrease sharply when the nozzle 24 is opened (in a traditional thrust device, the internal pressure and water capacity will decrease exponentially when the nozzle is opened, and the thrust time is short), so as to maintain a relatively long time to observe and study the temperature change and icing condition caused by the sharp pressure change (the cavity 22 maintains a certain high pressure state, and the pressure decreases sharply after being sprayed from the nozzle 24). The test can also test the thrust device during the thrust experiment, which eliminates the influence of the flowmeter on the thrust, can obtain the stable relationship curve of thrust, pressure and flow, and can obtain higher precision measurement quality flow and other related parameters, which provides data support for scientific research, so as to better correct the related model.

[0041] The test system provided by the application can realize long-time stable pressure or variable pressure thrust experiment of the thrust device 2. The stable pressure thrust experiment can be realized by maintaining the pressure in the sealed cylinder 11 through the inflator 12, and the variable pressure thrust experiment can be realized by adjusting the pressure in the sealed cylinder 11 through the inflator 12. Unlike the conventional thrust device, the pressure and water quantity in the cavity 22 are not sharply reduced when the nozzle 24 is opened, so that the dynamic parameters of the thrust device 2 can be observed and studied for a long time. In addition, the influence of the flow meter on the thrust is excluded when the thrust experiment of the thrust device is performed (in the current test method, a flow device is generally added at the nozzle to measure and calculate, which will affect the thrust of the nozzle). The mass flow and other related parameters can be measured with high precision to provide data support for scientific research, so that the related model can be better corrected.

[0042] In one specific embodiment, the thrust device 2 is horizontally arranged on the support 3. Since the water rocket is generally used for vertical thrust experiment, the current thrust device 2 is generally used for vertical thrust experiment. The related parameters and data of the thrust device 2 for horizontal thrust experiment are still relatively few. The test system can well realize the horizontal thrust experiment test of the thrust device 2. In addition, the thrust device 2 is changed to horizontal thrust experiment, which breaks the influence of the change of the water weight, the weight of the container shell and other supports on the thrust test accuracy and complexity when the thrust device 2 is tested in the vertical state. That is, the influence of the change of the gravity of the water mass on the thrust is excluded when the thrust experiment of the thrust device 2 is performed, so that the accuracy and precision of the thrust test of the thrust device 2 are greatly improved.

[0043] Specifically, the gravity of the water in the cavity 22 of the thrust device 2 changes all the time when the thrust device 2 is tested vertically, and the water flow is not easy to measure. Even if the flow meter is installed and the thrust is determined by flow conversion, due to the sharp change of the water pressure and water capacity, the measurement accuracy is limited, and the installation of the flow meter itself also interferes with the thrust size. The application can perform horizontal thrust experiment, which can avoid the problem that the thrust size of the thrust device 2 cannot be determined due to the change of the gravity of the water and other factors, and also avoids the way of determining the thrust by installing a flow sensor to test the water flow. The test in the horizontal state is directly the size of the thrust, which is simple, direct and accurate, and is not affected by the water weight, thereby further providing more accurate and reliable theoretical data.

[0044] In one specific embodiment, the support 3 is provided with a horizontal roller 31, and the thrust device body 21 of the thrust device 2 is arranged on the horizontal roller 31, so that the friction of the movement of the thrust device 2 can be reduced, and the friction can affect the thrust data of the thrust device 2.

[0045] In one specific embodiment, the support 3 is further provided with lateral rollers 32 on both sides of the thrust device body 21 of the thrust device 2. By providing the lateral rollers 32, the lateral friction of the thrust device 2 is reduced while the thrust direction of the thrust device 2 is maintained.

[0046] In one specific embodiment, the application further comprises a force transmission support 6 and a pressure sensor 5. One end of the force transmission support 6 is connected to the thrust device head 23 of the thrust device 2, and the other end is provided with the pressure sensor 5. The other end of the pressure sensor 5 is fixedly connected to the support 3. In this embodiment, the pressure sensor 5 can obtain the thrust of the thrust device 2 during the thrust experiment by being provided. The sequential arrangement of the support 3, the pressure sensor 5, the force transmission support 6 and the thrust device 2 can enable the pressure sensor 5 to accurately obtain the thrust of the thrust device 2 during the thrust experiment while maintaining the stability of the entire thrust device 2.

[0047] In one specific embodiment, the application further comprises a pressure sensor 7 for monitoring the pressure in the cavity 22 of the thrust device 2, which can obtain the pressure information in the thrust device 2 in real time.

[0048] In one specific embodiment, the upper part of the sealing cylinder 11 is further provided with a pressure relief valve 8. During stable pressure testing, the pressure in the sealing cylinder 11 can be balanced. When the inflation amount of the inflator 12 exceeds the set pressure, the pressure relief valve 8 starts to work until the pressure is released to the set pressure.

[0049] In one specific embodiment, the application further comprises a control valve 9 arranged on the nozzle 24 of the thrust device 2, which can actively control the opening of the nozzle 24 and can control the start of the test.

[0050] In one specific embodiment, the control valve 9 comprises a base part 91, a rotating part 92 and an electromagnet 93.

[0051] The base part 91 is provided with a channel I 911 which communicates with the nozzle 24;

[0052] The rotating part 92 is rotatably arranged on the base part 91. A sealing ring is further arranged between the rotating part 92 and the base part 91 to prevent water flow from between the rotating part 92 and the base part 91, so as to improve the sealing effect. The rotating part 92 is provided with a channel II 921. When the rotating part 92 is rotated to a set position, the channel II 921 communicates with the channel I 911. The rotating part 92 has at least two rotation limit positions. When the rotating part 92 is at the first limit position, the channel I 911 is completely isolated from the channel II 921. When the rotating part 92 is at the second limit position, the channel II 921 coaxially communicates with the channel I 911.

[0053] The electromagnet 93 is fixedly arranged on the base part 91, the rotating part 92 is arranged with a matching block 922 protruding therefrom, the matching block 922 is arranged to be magnetically attracted to the electromagnet 93, when the electromagnet 93 and the matching block 922 are magnetically attracted to each other, the channel I 911 is completely isolated from the channel II 921, after the electromagnet 93 loses power, the rotating part 92 rotates to the second limit position, the channel I 911 is communicated with the channel II 921, in this way, before the electromagnet 93 loses power, the rotating part 92 bears the pressure in the cavity 22, and the electromagnet 93 and the matching block 922 do not bear the pressure.

[0054] In one specific embodiment, the end of the base part 91 is a ball head, the rotating part 92 is a ball seat, the ball seat and the ball head are arranged with a reset torsional spring 94 at the hinged position, after the matching block 922 is separated from the magnetic attraction of the electromagnet 93, the reset torsional spring 94 resets the ball seat to the limit position, the channel II 921 is communicated with the channel I 911, in this embodiment, after the electromagnet 93 loses power, the reset force of the reset torsional spring 94 drives the rotating part 92 to rotate to the second limit position, and then the channel I 911 is quickly communicated with the channel II 921.

[0055] The application also provides a water rocket thrust test method, characterized by using a water rocket test system, including the following steps:

[0056] S1, injecting a set amount of water into the sealed cylinder 11 through the water injection mechanism 111, or continuously injecting water;

[0057] S2, pressurizing the sealed cylinder 11 through the air compressor 12, and maintaining or adjusting the pressure in the sealed cylinder 11;

[0058] S3, opening the nozzle 24 of the thrust device 2, the thrust device 2 performs thrust experiment, and the data of the sensor is acquired and recorded.

[0059] The contents not described in detail in the specification belong to the prior art known to those skilled in the art.

Claims

1. A water rocket test system, characterized in that: It includes a power source assembly (1), a thrust device (2), a bracket (3) and a connecting pipe (4); The power source assembly (1) comprises a sealing cylinder (11) and an inflator (12) connected to each other, and a water injection mechanism (111) is provided on the sealing cylinder (11); The thrust device (2) is arranged on a bracket (3), and a sensor for monitoring the state of the thrust device (2) is also arranged on the bracket (3); One end of the connecting pipe (4) is connected to the cavity (22) of the thrust device (2), and the other end extends into the bottom of the sealing cylinder (11); The thrust device (2) is horizontally arranged on the bracket (3); The end of the connecting pipe (4) close to the thrust device (2) is connected via a hose (41), and the hose (41) is perpendicular to the axis of the upper cavity (22) of the thrust device (2), so that the water spraying direction of the hose (41) is perpendicular to the water spraying direction of the nozzle (24).

2. The water rocket test system according to claim 1, wherein: A horizontal roller (31) is provided on the bracket (3), and a thrust device body (21) of the thrust device (2) is provided on the horizontal roller (31).

3. The water rocket testing system according to claim 2, wherein: The bracket (3) is further provided with side rollers (32) at positions on both sides of the thrust device body (21) of the thrust device (2).

4. The water rocket testing system according to any one of claims 1 to 3, characterized in that: It also includes a force transmission bracket (6) and a pressure sensor (5), one end of the force transmission bracket (6) is connected to the thrust device head (23) of the thrust device (2), and the other end is provided with the pressure sensor (5), and the other end of the pressure sensor (5) is fixedly connected to the bracket (3).

5. The water rocket testing system according to any one of claims 1 to 3, characterized in that: A pressure reducing valve (8) is also provided on the upper portion of the sealing cylinder (11).

6. The water rocket testing system according to any one of claims 1 to 3, characterized in that: It also includes a control valve (9) arranged on the nozzle (24) of the thrust device (2).

7. The water rocket testing system according to claim 6, wherein: The control valve (9) comprises a base portion (91), a rotating portion (92) and an electromagnet (93); The base portion (91) is provided with a channel I (911) communicating with the nozzle (24); The rotating portion (92) is rotatably disposed on the base portion (91), and a channel II (921) is provided on the rotating portion (92). When the rotating portion (92) rotates to a set position, the channel II (921) is communicated with the channel I (911); The electromagnet (93) is fixedly arranged on the base portion (91), and a matching block (922) is protruding from the rotating portion (92), and the matching block (922) and the electromagnet (93) are magnetically attracted.

8. The water rocket testing system according to claim 7, wherein: The end of the base portion (91) is a ball head, and the rotating portion (92) is a ball seat. A reset torsion spring (94) is provided at the hinge between the ball seat and the ball head. After the matching block (922) is separated from the adsorption of the electromagnet (93), the reset torsion spring (94) resets the ball seat to the extreme position, and the channel II (921) is connected to the channel I (911).

9. A water rocket thrust test method, characterized in that: Using the water rocket testing system according to any one of claims 1 to 8 comprises the following steps: S1. Injecting a set amount of water into the sealing cylinder (11) through the water injection mechanism (111), or continuously injecting water; S2, pressurizing the sealing cylinder (11) through the inflator (12), and maintaining or adjusting the pressure in the sealing cylinder (11); S3. Open the nozzle (24) of the thrust device (2), and the thrust device (2) performs a thrust experiment, and obtains and records the data of the sensor.

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