CN116486673B - Solid rocket and water rocket integrated two-stage model rocket - Google Patents
Solid rocket and water rocket integrated two-stage model rocket Download PDFInfo
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- CN116486673B CN116486673B CN202310740247.6A CN202310740247A CN116486673B CN 116486673 B CN116486673 B CN 116486673B CN 202310740247 A CN202310740247 A CN 202310740247A CN 116486673 B CN116486673 B CN 116486673B
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- 239000007787 solid Substances 0.000 title claims abstract description 127
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 title claims abstract description 114
- 238000012544 monitoring process Methods 0.000 claims description 26
- 238000000926 separation method Methods 0.000 claims description 21
- 230000005540 biological transmission Effects 0.000 claims description 19
- 230000006835 compression Effects 0.000 claims description 16
- 238000007906 compression Methods 0.000 claims description 16
- 238000007789 sealing Methods 0.000 claims description 16
- 239000004020 conductor Substances 0.000 claims description 11
- 230000008859 change Effects 0.000 claims description 9
- 239000000463 material Substances 0.000 claims description 7
- 238000010892 electric spark Methods 0.000 claims description 6
- 239000002360 explosive Substances 0.000 claims description 2
- 235000015842 Hesperis Nutrition 0.000 abstract description 5
- 235000012633 Iberis amara Nutrition 0.000 abstract description 5
- 238000011161 development Methods 0.000 abstract description 3
- 238000000034 method Methods 0.000 description 5
- 230000000694 effects Effects 0.000 description 3
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
- 238000010292 electrical insulation Methods 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 231100000956 nontoxicity Toxicity 0.000 description 2
- 239000004033 plastic Substances 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 238000010146 3D printing Methods 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 238000004026 adhesive bonding Methods 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 239000002390 adhesive tape Substances 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 238000007639 printing Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
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- G09B23/00—Models for scientific, medical, or mathematical purposes, e.g. full-sized devices for demonstration purposes
- G09B23/06—Models for scientific, medical, or mathematical purposes, e.g. full-sized devices for demonstration purposes for physics
- G09B23/08—Models for scientific, medical, or mathematical purposes, e.g. full-sized devices for demonstration purposes for physics for statics or dynamics
- G09B23/12—Models for scientific, medical, or mathematical purposes, e.g. full-sized devices for demonstration purposes for physics for statics or dynamics of liquids or gases
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02A—TECHNOLOGIES FOR ADAPTATION TO CLIMATE CHANGE
- Y02A90/00—Technologies having an indirect contribution to adaptation to climate change
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Abstract
The application relates to a two-stage model rocket integrating a solid rocket and a water rocket. The water rocket comprises a fairing, a water rocket body, a tail nozzle arranged at the lower end of the water rocket body, a solid rocket body, a separating piece and a pressure sensing ignition device; the lower end of the solid rocket body is detachably connected with the upper end of the water rocket body through a separating piece and is arranged between the water rocket body and the fairing; the pressure sensing ignition device is arranged at the upper end of the water rocket body and is contacted with solid rocket grains on the solid rocket body. Through the structure of the application, the principles and performances of the water rocket and the solid rocket can be comprehensively displayed, students can know two different model rockets through only one teaching aid, and case reference and experience reference are provided for innovation and development of interdisciplinary education projects.
Description
Technical Field
The application relates to the technical field of aero-model rockets, in particular to a solid rocket and water rocket integrated two-stage model rocket.
Background
In the past experimental process, the production of solid rocket grain fuel rockets and water rocket models is regarded as an important practical project in a plurality of aerospace courses, and the model rocket technology can be used for not only labor teaching, but also basic course teaching, deepen understanding of students on basic courses, and can help students learn and master the knowledge in the aspects of aerodynamics, flight mechanics and the like.
However, the ignition of the traditional solid rocket engine is finished by means of manual remote control ignition, and the method has the advantages of high feasibility, simplicity in operation and high cost performance. However, in the method, when the method is applied to secondary separation, the separation time cannot be accurately grasped by manual operation of an operator; in addition, the electric module is used for timing ignition, on one hand, a complex circuit is required to be designed, on the other hand, when the electric module is combined with a water rocket, the problems of short circuit and the like are easily caused by lower robustness of an electric control system, and the separation moment is not necessarily fixed after manual water injection, so that the ignition moment still has deviation.
Meanwhile, the traditional water rocket is manufactured by combining a plastic bottle with an adhesive tape, and has the advantages of simplicity in manufacturing, lower cost, better effect and the like. However, when the water rocket bottle body is applied to the project, the water rocket bottle body is in contact with flame sprayed by a solid rocket during separation, and the plastic bottle can be burnt out to cause failure in emission.
Disclosure of Invention
Based on the above, it is necessary to provide a two-stage model rocket integrating a solid rocket and a water rocket, which can realize a model rocket capable of displaying the principle and performance of the water rocket and the solid rocket only by one model, and accurately grasp the optimal ignition mode by a designed pressure sensing ignition device.
The two-stage model rocket integrated by the solid rocket and the water rocket comprises a water rocket body, a tail nozzle arranged at the lower end of the water rocket body, a solid rocket body, a separating piece and a pressure sensing ignition device;
the solid rocket body is detachably connected with the water rocket body, and is assembled and separated through a separating piece;
the pressure sensing ignition device is arranged at the upper end of the water rocket body and is contacted with solid rocket grains on the solid rocket body;
the pressure sensing ignition device comprises a body, wherein an ignition piece and a pressure monitoring assembly are arranged on the body;
the ignition piece is arranged towards the solid rocket body and is contacted with the solid rocket grain;
the pressure monitoring assembly is arranged towards the rocket body and is used for monitoring pressure change in the rocket cavity.
In one embodiment, the solid rocket body is of a cavity structure, and the lower end of the cavity body is sleeved with a solid rocket engine;
the solid rocket engine is provided with a through hole, and the solid rocket grain is arranged in the through hole.
In one embodiment, the pressure sensing ignition device further comprises: separating the transmission spring groove and the traction rope;
the separation transmission spring groove is formed in the body, a first spring is fixed in the groove, and the first spring has a pre-tightening state and a natural state;
when the first spring is in a pre-tightening state, one end of the haulage rope is connected with the pressure monitoring assembly, the other end of the haulage rope is connected with the solid rocket body, and the ignition piece is contacted with the end part of the solid rocket grain;
when the first spring is in a natural state, the traction rope is separated from the pressure monitoring assembly, and the ignition piece generates electric sparks to ignite the solid rocket grain.
In one embodiment, compression rods are arranged on the solid rocket engine, and the number of the compression rods corresponds to that of the separation transmission spring grooves;
when the water rocket body and the solid rocket engine are combined, the compression rod enters the separation transmission spring groove and is abutted against the first spring, so that the first spring is preloaded;
when the water rocket body is separated from the solid rocket engine, the first spring ejects the compression rod from the separation transmission spring groove through pretightening force, and the first spring is restored to a natural state.
In one embodiment, the pressure monitoring assembly comprises: a pressure chamber, a pressure piston and a connecting tube;
the pressure piston and the connecting pipe are respectively arranged at two sides of the pressure cavity;
the pressure piston is in sliding sealing fit with the pressure cavity;
one end of the connecting pipe is connected with the pressure cavity, and the other end of the connecting pipe is connected with the water rocket body and is used for monitoring pressure change in the water rocket cavity.
In one embodiment, the ignition element comprises a shell, and an ignition head negative electrode is arranged on the side wall of the shell; the end part of the shell is provided with an ignition head anode, when the first spring is changed from a pre-tightening state to a natural state, the negative electrode of the ignition head is contacted with the ignition head anode, and the ignition piece generates sparks to ignite the solid rocket grain.
In one embodiment, a conductive piston is arranged in the shell, and the shell and the conductive piston form sliding sealing fit;
a conductor bar is fixed on the conductive piston, and an ignition head anode and an ignition head are fixed at the upper end of the conductor bar;
the ignition head is provided with a connecting rope, when the first spring is changed from a pre-tightening state to a natural state, the connecting rope pulls the conductor bar to move upwards, so that the conductive piston moves upwards to be in contact with the negative electrode of the ignition head, an electric path is formed, and the ignition head generates sparks to ignite the solid rocket explosive column.
In one embodiment, the separating member has a sleeve structure, and the inner diameter of the separating member is adapted to the outer diameter of the solid rocket body and the outer diameter of the water rocket body, so that the lower end of the solid rocket body and the upper end of the water rocket body are respectively inserted into the two ends of the separating member.
In one embodiment, the water rocket body is made of PLA material.
Compared with the prior art, the two-stage model rocket integrating the solid rocket and the water rocket has the following effects:
1. the solid rocket is connected to the water rocket in a specific mode, through the combination, the principle and the performance of the water rocket and the solid rocket can be comprehensively displayed, two different model rockets can be known to students through only one teaching aid, and case reference and experience reference are provided for innovation and development of interdisciplinary education projects;
2. the pressure sensing ignition device can find the optimal ignition time of the solid rocket according to the internal air pressure change of the water rocket, so as to realize the automatic ignition of the solid rocket;
3. the rocket body of the water rocket is made of PLA material, has excellent impact toughness, wear resistance, wide use temperature range, good dimensional stability, excellent electrical insulation and no toxicity; by adopting the material, the feasibility and the safety of the experiment are greatly ensured.
Drawings
FIG. 1 is a front view of a two-stage model rocket integrated with a water rocket, provided in one embodiment;
FIG. 2 is a schematic diagram of a two-level model rocket of a solid rocket and water rocket integration according to one embodiment;
FIG. 3 is a front isometric view of a pressure sensing ignition device provided in one embodiment;
FIG. 4 is a back isometric view of a pressure sensing ignition device provided in one embodiment;
FIG. 5 is a cross-sectional view of a pressure sensing ignition device provided in one embodiment;
FIG. 6 is an isometric view of a pressure monitoring assembly provided by one embodiment;
FIG. 7 is a schematic view of an igniter structure according to one embodiment;
reference numerals illustrate: a fairing 1;
the solid rocket comprises a solid rocket body 2, a solid rocket engine 21, a solid rocket grain 22, a solid rocket tail 23 and a compression rod 24;
the water rocket comprises a water rocket body 3, a tail nozzle 31 and a water rocket tail wing 32;
a separating member 4;
the pressure sensing ignition device 5, the body 51, the split transmission spring groove 512, the traction rope 513, the first spring 514 and the traction rope hole 516;
the pressure monitoring assembly 52, the pressure chamber 521, the sealing member 522, the pressure rod 523, the second spring 524, the connecting tube 525, the fixing base 526;
the ignition element 53, the housing 531, the ignition head cathode 532, the ignition head anode 533, the ignition head 534, the conductive piston 535, the conductor bar 536, and the connection cord 537.
Detailed Description
The present application will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present application more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the application.
It should be noted that all directional indicators (such as up, down, left, right, front, and rear … …) in the embodiments of the present application are merely used to explain the relative positional relationship, movement, etc. between the components in a particular posture (as shown in the drawings), and if the particular posture is changed, the directional indicator is changed accordingly.
Furthermore, descriptions such as those referred to as "first," "second," and the like, are provided for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implying an order of magnitude of the indicated technical features in the present disclosure. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In the description of the present application, the meaning of "plurality" means at least two, for example, two, three, etc., unless specifically defined otherwise.
In the present application, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; either directly or indirectly, through intermediaries, or both, may be in communication with each other or in interaction with each other, unless expressly defined otherwise. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art according to the specific circumstances.
The application designs a two-stage model rocket combining solid rocket grain 22 and a water rocket. The model can combine the solid rocket grain 22 rocket model and the water rocket model into one rocket, comprehensively show the principle and the performance of the water rocket and the solid rocket, and can realize that two different model rockets can be known only through one model. Aiming at the current research situation of the model rocket, the practical value of the model rocket is deeply excavated, and based on the characteristics and limitations of the traditional model rocket, the designed model rocket has the advantages of simple structure, convenient installation, easy maintenance and low cost, and provides case reference and experience reference for the innovation and development of the interdisciplinary education project.
In one embodiment, as shown in fig. 1-7, the application provides a two-stage model rocket structure integrating a solid rocket and a water rocket, which comprises a fairing 1, a solid rocket body 2, a water rocket body 3, a tail nozzle 31, a separating piece 4 and a pressure sensing ignition device 5. The fairing 1 is of a cone structure and is arranged at the top end of the whole model rocket and used for maintaining aerodynamic shape so as to reduce resistance. The lower end of the parachute is fixed with the upper end of the solid rocket body 2 in a splicing way, so that the fairing 1 is separated from the solid rocket body 2 when the rocket reaches the highest point, and then the parachute is opened, and the parachute can be fixed in a mode of being convenient to separate, such as gluing, splicing and the like. The solid rocket body 2 and the water rocket body 3 are detachably connected and are combined and separated through the separating piece 4. The separating piece 4 is of a sleeve structure, and the inner diameter is matched with the outer diameter of the solid rocket body 2 and the outer diameter of the water rocket body 3, so that the lower end of the solid rocket body 2 and the upper end of the water rocket body 3 are conveniently inserted into the two ends of the separating piece 4 respectively. The two ends of the sleeve of the separating piece 4 can be assembled with the solid rocket body 2 and the water rocket body 3 by adopting any one or any two combination modes of buckling, threads, clamping grooves, plugging and the like. As shown in fig. 3, the separating member 4 of the present embodiment has a structure in which one end is provided with a slot, the other end is inserted, and after the one end provided with the slot is aligned with the solid rocket tail 23, the slot is clamped into the solid rocket tail 23, and the other end is directly inserted into the water rocket body 3.
The pressure sensing ignition device 5 is fixed at the upper end of the water rocket body 3 and is partially or completely arranged in the cavity of the water rocket body 3; above which is in contact with solid rocket grains 22.
Specifically, the solid rocket body 2 and the water rocket body 3 are both in a cavity structure, wherein the solid rocket engine 21 is arranged in the cavity of the solid rocket body 2 and near the lower end, and can be fixed by means of threads, bolts or bolts and the like. The solid rocket engine 21 is provided with a through hole, and the solid rocket grain 22 is inserted into the through hole and is generally fixed by glue, and can be more firmly fixed by adopting iron wire winding and other modes. Meanwhile, four solid rocket tails 23 are symmetrically arranged at the tail end of the solid rocket body 2, four water rocket tails 32 are symmetrically arranged at the tail end of the water rocket body 3 and used for guaranteeing the stability of the states of the solid rocket body 2 and the water rocket body 3 after being lifted off, the tails can be fixed at the tail end of the rocket body in an adhesive mode, and notches can be formed in the tail end of the solid rocket body 2 or the tail end of the water rocket body 3, and the tails are fixed in a plug-in mode.
The pressure sensing ignition device 5 is a cylinder structure which is matched with the structure of the rocket body 3, so that the pressure sensing ignition device 5 is not firm enough to prevent the contact with water after being fixed, and the pressure sensing ignition device 5 is fixed at the upper end of the rocket body 3 in a threaded connection mode, and a sealing ring can be additionally arranged if necessary, so that the effect of ensuring air tightness and firm combination is achieved. The pressure sensing ignition device 5 comprises a body 51, and a pressure monitoring assembly 52, an ignition piece 53, a separation transmission spring groove 512 and a traction rope 513 are arranged on the body 51.
The body 51 is fixed on the water rocket body 3, the pressure monitoring assembly 52 is arranged on the side facing the water rocket body 3, and the ignition piece 53 is arranged on the side facing the solid rocket body 2. The pressure monitoring assembly 52 monitors the pressure change in the water rocket body 3; when the pressure change reaches a set value, the solid rocket grains 22 on the solid rocket body 2 are ignited by the ignition member 53. The plurality of separation transmission spring grooves 512 are uniformly distributed in the body 51 along a ring shape, are of a cylindrical cavity structure with one end closed and the other end open, and are open towards the rocket body 3. A first spring 514 is fixed in the cavity, a compression rod 24 is oppositely arranged on the solid rocket body 2, and the thickness of the compression rod 24 is matched with the opening of the separation transmission spring groove 512. When the solid rocket body 2 is combined with the water rocket body 3, the compression rod 24 is aligned with the separation transmission spring groove 512, the compression rod 24 enters the separation transmission spring groove 512 and compresses the first spring 514, the traction rope 513 is connected with the pressure monitoring assembly 52, and the ignition piece 53 is contacted with the end part of the solid rocket grain 22 of the solid rocket body 2. When the solid rocket body 2 is separated from the water rocket body 3, the first spring 514 ejects the compression rod 24 from the separation transmission spring groove 512, the traction rope 513 is separated from the pressure monitoring component 52, the ignition piece 53 is conducted in a circuit, and electric sparks are generated to ignite the solid rocket grains 22 of the solid rocket body 2, so that ignition is automatically completed.
The pressure monitoring assembly 52 includes a pressure chamber 521, a pressure piston, a connecting tube 525 and a fixing base 526; the pressure piston and the connecting pipe 525 are arranged on two sides of the pressure cavity 521, the pressure cavity 521 is fixed on the body 51 through the fixing base 526, the pressure piston is in sliding sealing fit with the pressure cavity 521, one end of the connecting pipe 525 is connected with the pressure cavity 521, and the other end of the connecting pipe 525 stretches into the water rocket body 3 to be used for monitoring the air pressure change of the water rocket body 3.
Specifically, the pressure chamber 521 is provided with a first through hole and a second through hole penetrating therethrough on both sides thereof, respectively. The first through hole is adapted to the outer wall of the connecting pipe 525 in size, so that the connecting pipe 525 is conveniently inserted into the first through hole and connected with the inner cavity of the pressure cavity 521, and in order to ensure air tightness, an air-tight rubber ring is additionally arranged at the connecting position.
The pressure piston comprises a sealing piece 522, a pressure rod 523 and a second spring 524, wherein the sealing piece 522 is arranged in the pressure cavity 521 and is in sliding sealing fit with the pressure cavity 521, one end of the pressure rod 523 is fixed on the sealing piece 522, the other end of the pressure rod 523 extends out of the second through hole, and a traction rope 513 is sleeved near the end of the pressure rod. The second spring 524 is fixed to the sealing member 522 and the pressure chamber 521 at both ends thereof, respectively, and when the air pressure in the pressure chamber 521 is changed, the second spring 524 is shifted between a pre-tensioned state and a natural state, thereby driving the sealing member 522 to reciprocate with the pressure lever 523.
The fixed base 526 is also provided with a third through hole corresponding to the second through hole, and the pressure rod 523 extends from the second through hole, is inserted into the third through hole, and is in clearance fit with the third through hole. The traction rope 513 is sleeved on the pressure rod 523 and is positioned between the second through hole and the third through hole. It should be noted that, the body 51 is further provided with a traction rope hole 516, one end of the traction rope 513 is sleeved on the pressure rod 523, and the other end of the traction rope penetrates through the traction rope hole 516 and then is connected with the solid rocket body 2, so that the connection stability of the water rocket body 3 and the solid rocket body 2 can be further ensured.
One end of the connecting pipe 525 is connected with the inner cavity of the pressure cavity 521, the other end is inserted into the water rocket body 3, and the same air pressure is formed between the water rocket body 3 and the pressure cavity 521. When the water rocket body 3 works, the pressure in the initial water rocket body 3 is larger, and the pressure chamber 521 also has larger atmospheric pressure, so that the sealing piece 522 is compressed, the second spring 524 is in a pre-tightening state, and the pressure rod 523 is inserted into the third through hole; after the rocket body 3 is launched, the pressure in the rocket body 3 is gradually reduced, the air pressure of the pressure cavity 521 is also gradually reduced, the second spring 524 is changed into a natural state from a pre-tightening state, so that the compression sealing piece 522 is pushed to move towards the pressure cavity 521, the pressure rod 523 is driven to be separated from the third through hole, and the traction rope 513 is separated from the pressure rod 523.
The ignition piece 53 is arranged on one side close to the solid rocket body 2, is coaxially fixed on the body 51 and comprises a shell 531, an ignition head negative electrode 532 is arranged on the side wall of the shell 531, a conductive piston 535 is arranged inside the ignition piece, the conductive piston 535 is in sliding sealing fit with the inner wall of the shell 531, a conductor bar 536 is fixed on the conductive piston 535, and an ignition head positive electrode 533 and an ignition head 534 are fixed on the conductor bar 536. When the first spring 514 is shifted from the pre-tightening state to the natural state, the connecting rope 537 pulls the conductor bar 536 to move upwards, so that the conductive piston 535 contacts with the negative electrode 532 of the ignition head, the negative electrode 532 of the ignition head and the positive electrode 533 of the ignition head form an electric path, the ignition head 534 generates electric sparks, the solid rocket grain 22 of the solid rocket body 2 is ignited, and the solid rocket grain is separated from the solid rocket body 2 after automatic ignition is completed.
In one embodiment, the tail nozzle 31 is fixed at the lower end of the rocket body 3 in a threaded connection mode, and in order to ensure air tightness, an air-tight rubber ring can be additionally arranged at the connecting position.
In one embodiment, the rocket body 3 is manufactured by adopting PLA material through 3D printing, and the rocket body manufactured by the method has excellent performance, excellent impact toughness, wear resistance, wide use temperature range, good dimensional stability, excellent electrical insulation and no toxicity. By adopting the material, the feasibility and the safety of the experiment are greatly ensured.
In one embodiment, the application describes how a solid rocket and water rocket integrated two-stage model rocket can be demonstrated.
And 102, measuring and calculating the internal air pressure as the trigger value of the pressure sensor ignition device when the water rocket reaches the highest point. Specifically, after printing a water rocket body by using PLA materials, a water rocket is independently manufactured, and a pressure sensor and a height meter are arranged at the top of the water rocket to perform a plurality of flight tests. Drawing the measured pressure change value and the corresponding height value into a graph, so as to obtain an average pressure value in the water rocket after the water rocket reaches the highest point, and taking the average pressure value as a set value of a pressure sensor in the pressure ignition device; when the pressure sensor measures the value of the water rocket inside (namely the water rocket reaches the highest position), the power is supplied so as to ignite.
Step 104, assembling the pressure sensing ignition device. After the ignition member 53 and the pressure monitoring unit 52 are fixed in the body 51, the first spring 514 is mounted in the separate transmission spring groove 512.
And 106, finishing rocket assembly. The fairing 1, the solid rocket body 2, the solid rocket tail 23, the solid rocket engine 21 and the solid rocket grain 22 are tightly combined to be assembled into the secondary solid grain rocket. The water rocket body 3, the water rocket tail wing 32, the tail nozzle 31 and the pressure sensing ignition device 5 are tightly combined and assembled into the primary water rocket.
Step 108, bolting the hauling cable. The two traction ropes are sleeved on the pressure rod 523, respectively pass through the two traction rope holes 516 on the pressure sensing ignition device 5, and then are bolted and tied with the solid rocket engine 21, so that the primary water rocket is connected with the secondary solid rocket, and the compression rod 24 on the solid rocket body 2 enters the separation transmission spring groove 512 and compresses the first spring 514.
Step 110, mounting of the separating element 4. The four clamping grooves on the separating piece 4 are aligned with the four solid rocket tail fins 23, and then the lower end of the sleeve is inserted outside the primary water rocket, so that the rocket is integrally assembled.
Step 112, water is injected to pressurize and prepare before firing. After water is injected into the water rocket body 3 before launching (approximately at one third of the volume of the rocket body), the air in the water rocket body 3 is pressurized by an inflator, and when the barometer shows that the air pressure in the rocket body is approximately 10 atmospheres, the pressurization is stopped. At this time, the second spring 524 inside the pressure monitoring assembly 52 is compressed, and the pressure sensor 661 senses the elastic force from the spring. The security personnel are excluded from being alerted, and the surrounding environment is ensured to meet the emission condition.
Step 114, start the flight test. And opening a safety bolt of the water rocket launching frame, pressing a launching handle, and launching the rocket.
In step 116, the pressure sensing ignition device 5 ignites. The rocket continuously rises, when the maximum height of the primary water rocket is reached after all water flows in the water rocket are sprayed out, the pressure in the rocket body is reduced, the elasticity of a second spring 524 in the pressure monitoring assembly 52 is reduced, the pressure piston is driven to move, a traction rope 513 is separated from a pressure rod 523, a connecting rope 537 on an ignition member 53 senses the tensile force, a conductor bar 536 is pulled, thereby driving a conductive piston 535 to move, an electric path is formed between an ignition head anode 533 and an ignition head cathode 532, and an electric spark is generated by an ignition head 34 to discharge an electric spark to ignite a solid rocket grain 22.
Step 118, rocket separation. The solid rocket grain 22 ejects flame to quickly blow the traction rope 513 and the connecting rope 537, the first spring 514 is not limited any more, the pre-tightening state is changed into the natural state, the first-stage water rocket moves downwards under the elasticity of the spring, the second-stage solid rocket moves upwards under the elasticity of the spring and the thrust of the rocket engine, and the separation piece 4 is removed from the limitation, so that the second-stage separation is realized. The solid rocket continues to rise.
Step 120, recovering the device. And automatically opening the parachute after the second-stage solid rocket rises to the maximum height, so as to realize soft landing. And parts are recovered in time after the floor is set, so that no parts are lost and damaged.
The technical features of the above embodiments may be arbitrarily combined, and all possible combinations of the technical features in the above embodiments are not described for brevity of description, however, as long as there is no contradiction between the combinations of the technical features, they should be considered as the scope of the description.
The above examples illustrate only a few embodiments of the application, which are described in detail and are not to be construed as limiting the scope of the application. It should be noted that it will be apparent to those skilled in the art that several variations and modifications can be made without departing from the spirit of the application, which are all within the scope of the application. Accordingly, the scope of protection of the present application is to be determined by the appended claims.
Claims (9)
1. The two-stage model rocket integrating the solid rocket and the water rocket comprises a water rocket body and a tail nozzle arranged at the lower end of the water rocket body, and is characterized by further comprising the solid rocket body, a separating piece and a pressure sensing ignition device;
the solid rocket body is detachably connected with the water rocket body, and is assembled and separated through a separating piece;
the pressure sensing ignition device is arranged at the upper end of the water rocket body and is contacted with solid rocket grains on the solid rocket body;
the pressure sensing ignition device comprises a body, wherein an ignition piece and a pressure monitoring assembly are arranged on the body;
the ignition piece is arranged towards the solid rocket body and is contacted with the solid rocket grain;
the pressure monitoring assembly is arranged towards the rocket body and is used for monitoring pressure change in the rocket cavity.
2. The solid rocket and water rocket integrated two-stage model rocket of claim 1, wherein: the solid rocket body is of a cavity structure, and the lower end of the cavity body is sleeved with a solid rocket engine;
the solid rocket engine is provided with a through hole, and the solid rocket grain is arranged in the through hole.
3. A solid rocket and water rocket integrated two-stage model rocket according to claim 1 or 2, wherein the pressure sensing ignition device further comprises: separating the transmission spring groove and the traction rope;
the separation transmission spring groove is formed in the body, a first spring is fixed in the groove, and the first spring has a pre-tightening state and a natural state;
when the first spring is in a pre-tightening state, one end of the haulage rope is connected with the pressure monitoring assembly, the other end of the haulage rope is connected with the solid rocket body, and the ignition piece is contacted with the end part of the solid rocket grain;
when the first spring is in a natural state, the traction rope is separated from the pressure monitoring assembly, and the ignition piece generates electric sparks to ignite the solid rocket grain.
4. A solid rocket and water rocket integrated two-stage model rocket as recited in claim 3, wherein compression rods are arranged on said solid rocket engine, and the number of said compression rods corresponds to said separate transmission spring grooves;
when the water rocket body and the solid rocket engine are combined, the compression rod enters the separation transmission spring groove and is abutted against the first spring, so that the first spring is preloaded;
when the water rocket body is separated from the solid rocket engine, the first spring ejects the compression rod from the separation transmission spring groove through pretightening force, and the first spring is restored to a natural state.
5. A solid rocket and water rocket integrated two-stage model rocket according to claim 4, wherein said pressure monitoring assembly comprises: a pressure chamber, a pressure piston and a connecting tube;
the pressure piston and the connecting pipe are respectively arranged at two sides of the pressure cavity;
the pressure piston is in sliding sealing fit with the pressure cavity;
one end of the connecting pipe is connected with the pressure cavity, and the other end of the connecting pipe is connected with the water rocket body and is used for monitoring pressure change in the water rocket cavity.
6. A solid rocket and water rocket integrated two-stage model rocket according to claim 3, wherein said ignition member comprises a casing, said casing side wall being provided with an ignition head cathode; the end part of the shell is provided with an ignition head anode, when the first spring is changed from a pre-tightening state to a natural state, the negative electrode of the ignition head is contacted with the ignition head anode, and the ignition piece generates sparks to ignite the solid rocket grain.
7. The two-stage model rocket integrated with a water rocket as recited in claim 6, wherein a conductive piston is arranged in the shell, and the shell and the conductive piston form sliding sealing fit;
a conductor bar is fixed on the conductive piston, and an ignition head anode and an ignition head are fixed at the upper end of the conductor bar;
the ignition head is provided with a connecting rope, when the first spring is changed from a pre-tightening state to a natural state, the connecting rope pulls the conductor bar to move upwards, so that the conductive piston moves upwards to be in contact with the negative electrode of the ignition head, an electric path is formed, and the ignition head generates sparks to ignite the solid rocket explosive column.
8. The two-stage model rocket integrated with a water rocket according to claim 1 or 2, wherein the separating member has a sleeve structure, and the inner diameter of the sleeve structure is adapted to the outer diameter of the solid rocket body and the outer diameter of the water rocket body, so that the lower end of the solid rocket body and the upper end of the water rocket body are respectively inserted into the two ends of the separating member.
9. The two-stage model rocket integrated with a water rocket according to claim 1 or 2, wherein the water rocket body is made of PLA material.
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