Secondary water rocket automatic separation device based on gravity-inertial reference system equivalence principle

Abstract

The invention provides a two-stage rocket automatic separation device based on the gravity-inertial reference system equivalence principle. The two-stage rocket automatic separation device comprises a first-stage rocket body, a second-stage rocket body, a sealing device and a separation device. The sealing device is characterized in that the sealing device is fixed at bottle openings of the first-stage rocket body and the second-stage rocket body, and pressure is injected into the rocket bodies through a one-way air valve of the sealing device. The first-stage rocket body can be launched after the constraint of the sealing device is relieved; the counter-acting force sprayed out of the internal liquid provides the thrust for the whole rocket body to rise. For the second-stage rocket body, the sealing device is fixed to the rocket body through the buckle component of the separating device. Before launching, due to the fact that the second-stage rocket body has certain weight, a spring component at the bottom of the separating device is in a compressed state, and the separating device cannot be triggered. Within a period of time after launching, the lift force of the first-stage rocket body is transmitted to the second-stage rocket body through a spring at the bottom of the separation device, and the spring is still in a compressed state. And until the lift force of the first-stage rocket body is smaller than the elastic force of the spring, the separating device can be started to relieve the constraint on the sealing device of the second-stage rocket body, so that the launching of the second-stage rocket body is realized. The two-stage rocket body independent pressurization mode is adopted, traditional hose connection is not needed, and other user-defined parts are allowed to be added between the two stages of rocket bodies. The water rocket mode that counter-acting force is provided through liquid pressurization is not depended on, and the water rocket can be suitable for launching of various types of rockets. The device is simple in structure, convenient to operate, environment-friendly, safe and stable.

Description

Technical Field

[0001] The invention relates to a water rocket, in particular to a two-stage water rocket separation device. Background Art

[0002] Water rockets are model rocket aircraft based on the Newtonian action-reaction principle, powered by air pressure and water, and are often used in comprehensive science and practice activities for young people. The water rocket launch process is safe and environmentally friendly, with no toxic side effects, and helps to improve participants' logical thinking and hands-on skills, and deepen their understanding of physical principles. The structure and principle of traditional water rockets are relatively simple, generally using a carbonated beverage bottle as the main body of the rocket, and there are certain limitations in the shooting height. Since it does not contain a two-stage separation device, there is a certain gap between the traditional device and the actual multi-stage rocket principle, and the requirements for hands-on skills are relatively low, making it difficult to arouse the interest of senior students in spacecraft.

[0003] Existing two-stage water rocket separation devices generally connect the first and second stages of the rocket body through an inflatable hose. Chinese patent CN106384551A discloses a two-stage rocket body launch device that uses the air pressure of the first stage rocket body and the friction of the inflatable hose to control. This device is only applicable to water rockets based on the air pressure power principle, has poor scalability, and cannot install other device components between the two stages of the rocket body. Chinese patent CN103136988A discloses a two-stage separation device related to air resistance, which has certain requirements for the launch environment and wind speed; and the two stages of the rocket body are still connected by pipes, which cannot be used to separate rockets of other power types. Summary of the invention

[0004] The purpose of the present invention is to overcome the shortcomings and deficiencies of the prior art and to provide a two-stage rocket automatic separation device based on the gravitational-inertial reference system equivalence principle, comprising a first-stage rocket body, a second-stage rocket body, a sealing device and a separation device.

[0005] The technical solution for achieving the purpose of the present invention is: a sealing device is fixed at the bottle mouth of the primary and secondary arrow bodies, and pressure is injected into the arrow body through the one-way air valve of the sealing device. For the primary arrow body, it can be launched after the sealing device is released; the reaction force of the internal liquid spraying provides the thrust for the overall rise of the arrow body. For the secondary arrow body, the sealing device is fixed to the arrow body by the buckle component of the separation device. Before launching, due to the certain weight of the secondary arrow body, the spring component at the bottom of the separation device is in a compressed state and will not trigger the separation device. For a period of time after launching, the lifting force of the primary arrow body is transmitted to the secondary arrow body through the spring at the bottom of the separation device, and the spring is still in a compressed state. Until the lifting force of the primary arrow body is less than the elastic force of the spring, the separation device will be activated, the constraint on the sealing device of the secondary arrow body will be released, and the launching of the secondary arrow body will be realized. The device utilizes the gravitational-inertial reference system equivalence principle to ensure that the secondary arrow body is not activated before launching and during the propulsion of the primary arrow body. The lever principle is used in the core separation device: to ensure that after the second-stage rocket body is pressurized, the snap-fit ​​component of the separation device can provide sufficient constraints for the sealing device, and at the same time the elastic force of the spring component is sufficient to release the constraints of the snap-fit ​​component.

[0006] Compared with the prior art, the present invention has the following advantages and effects: 1. It adopts a method of independently pressurizing the two-stage rocket body, without the need for traditional hose connection, allowing other custom components to be added between the two-stage rocket body, and there are no special requirements for the shape and size of the two-stage rocket body; 2. The water rocket mode does not rely on liquid pressurization to provide reaction force, and can be applied to various types of rocket launches; 3. It has low requirements on the launch environment and is also applicable in vacuum and underwater environments; 4. It has a simple structure, is easy to operate, is green and environmentally friendly, and is safe and stable. BRIEF DESCRIPTION OF THE DRAWINGS

[0007] Figure 1 This is an overall schematic diagram of the two-stage water rocket device.

[0008] Figure 2 (a) Schematic diagram of the sealing device, (b) the state before the separation device takes effect, and (c) the state after the separation device takes effect.

[0009] Figure 1 The components are: 1. fairing, 2. second stage rocket body, 3. two-stage rocket body connecting sleeve, 4. separation device, 5. second stage rocket body sealing device, 6. rocket tail, 7. first stage rocket body, 8. first stage rocket body sealing device, 9. sealing device buckle.

[0010] Figure 2The components are: (a) 7-1. The first-stage arrow body bottle mouth protrusion, 8-1. The sealing device one-way air valve, 8-2. The sealing device rubber plug. (b) 2-1. The second-stage arrow body bottle mouth protrusion, 4-1. The separation device traction rope, 4-2. The separation device buckle, 4-3. The separation device spring, 5-1. The sealing device one-way air valve, 5-2. The sealing device rubber plug. DETAILED DESCRIPTION

[0011] In this embodiment, refer to Figure 1 The two-stage water rocket based on the gravitational-inertial reference system equivalence principle is composed of a first-stage body 7, a second-stage body 2, sealing devices 5 and 8, and a separation device 4. The connecting sleeve 3 is fixed to the first-stage body 7, and the first-stage body 7 and the second-stage body 2 are combined together through the connecting sleeve 3. The fairing 1 is fixed on the second-stage body 2, and the rocket tail 6 is fixed on the connecting sleeve 3. The sealing device 8 is connected to the bottle mouth of the first-stage body 7. The sealing device 5 is connected to the bottle mouth of the second-stage body 2.

[0012] refer to Figure 2 , the bottom of the separation device buckle 4-2 is fixed to the bottom of the sealing device rubber plug 5-2, and the top of the separation device buckle 4-2 is stuck on the bottle mouth protrusion 2-1 of the secondary arrow body 2, thereby providing additional constraints for the sealing device 5. The two ends of the separation device traction rope 4-1 are respectively connected to the bottom of the separation device spring 4-3 and the extension arm of the separation device buckle 4-2. The top of the separation device spring 4-3 is fixed to the bottom of the sealing device rubber plug 5-2, and the bottom of the separation device spring 4-3 is placed on the top of the primary arrow body 7. When the separation device spring 4-3 is in a compressed state, the separation device traction rope 4-1 is in a relaxed state. When the separation device spring 4-3 is in an extended state, the separation device buckle 4-2 is pulled to move to both sides by the separation device traction rope 4-1, thereby releasing the constraint on the sealing device 5.

[0013] When installing the whole, first inject 1 / 3 of water into the first-stage arrow body 7, plug the sealing device 8, and fix it on the first-stage arrow body bottle mouth protrusion 7-1 through the sealing device buckle 9. Figure 1 Similarly, inject 1 / 3 of water into the secondary rocket body 2, plug the sealing device 5, and fix it with the separation device buckle 4-2. Figure 1 The direction shown is placed above the first-stage arrow body and fixed by the two-stage arrow body connecting sleeve 3. The spring 4-3 of the separation device is in a compressed state by the gravity of the second-stage arrow body to ensure that the second-stage arrow body will not be launched. A rubber hose is used to inject air pressure into the first-stage arrow body 7 and the second-stage arrow body 2 through the one-way air valves 5-1 and 8-1 of the sealing device and retain it in the arrow body.

[0014] During launch, the sealing device buckle 9 of the first-stage body 7 is released, and the water rocket as a whole will accelerate upward under the push of the first-stage body 7. At this time, the spring 4-3 of the separation device between the first-stage body and the second-stage body is still in a compressed state, and the constraint of the separation device 4 on the sealing device 5 is still effective. This process embodies the equivalence principle of the gravitational-inertial reference system. As the thrust provided by the first-stage body 7 decreases, the overall acceleration of the water rocket also decreases. When it reaches a certain level, driven by the elastic force of the separation device spring 4-3, the separation device buckle 4-2 moves sideways, releasing the constraint on the sealing device 5-2, thereby launching the second-stage body 2 and realizing the automatic separation of the two-stage water rocket.

Claims

1. A two-stage water rocket automatic separation device based on the gravitational-inertial reference system equivalence principle, comprising a first-stage rocket body, a second-stage rocket body, a sealing device and a separation device. Its characteristics are: The first-stage arrow body and the second-stage arrow body are combined through a connecting sleeve; sealing devices are provided at the bottle mouths of the first-stage arrow body and the second-stage arrow body; the sealing devices are fixed to the arrow body by buckles; and a separation device is added to the sealing device of the second-stage arrow body.

2. The two-stage water rocket automatic separation device based on the gravitational-inertial reference system equivalence principle according to claim 1 is characterized in that: The sealing device comprises a rubber plug and a one-way air valve, which retains the injected gas in the arrow body.

3. The two-stage water rocket automatic separation device based on the gravitational-inertial reference system equivalence principle according to claim 1 is characterized in that: The separation device comprises a buckle, a traction rope and a spring. The bottom of the buckle of the separation device is fixed to the bottom of the rubber plug of the sealing device, and the top of the buckle of the separation device is clamped on the protrusion of the secondary arrow body bottle mouth, providing additional constraints for the sealing device. Two ends of the separation device traction rope are respectively connected to the bottom of the separation device spring and the separation device buckle extension arm. The top of the separation device spring is fixed to the bottom of the sealing device rubber plug, and the bottom of the separation device spring is placed on the top of the first-stage arrow body. The separation device buckle extension arm ensures that the buckle component of the separation device can provide sufficient restraint for the sealing device after the second-stage arrow body is pressurized, and the elastic force of the spring component is sufficient to release the restraint of the buckle component.

4. The two-stage water rocket automatic separation device based on the gravitational-inertial reference system equivalence principle according to claim 1 is characterized in that: Based on the gravitational-inertial reference frame equivalence principle, the spring of the separation device is kept in a compressed state before launch and during the propulsion of the first stage. When the spring of the separation device is in a compressed state, the traction rope of the separation device is in a relaxed state and will not trigger the separation device. When the spring of the separation device is in an extended state, the separation device buckle is pulled to move to both sides by the separation device traction rope, thereby releasing the constraint on the sealing device and launching the secondary arrow body.

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