Secondary model rocket for science popularization education based on acceleration ignition judgment

Abstract

The invention provides a secondary model rocket for science popularization education based on acceleration ignition judgment, and belongs to the field of science popularization education, a model comprises a secondary main body, an interstage section, a primary main body and avionics, the primary main body is located below the model, and the primary main body is connected with the secondary main body through the interstage section; the avionics adopts a secondary ignition judgment mode based on axial acceleration; the switch board is formed by arranging three toggle switches in parallel, and the closing directions of the adjacent switches are opposite. The second-level model rocket for science popularization education based on acceleration ignition judgment solves the problems that an existing model rocket for science popularization education is poor in second-level ignition and separation stability, low in safety, poor in parachute opening consistency, prone to faults, and lack of science popularization attraction due to the fact that product forms are all-round. The structure is greatly different from that of a real rocket, and deep explanation of spaceflight knowledge is not facilitated.

Description

Technical Field

[0001] This invention relates to the field of science education, and in particular to a second-stage model rocket for science education purposes based on acceleration ignition determination. Background Technology

[0002] In the field of science education, model rockets serve as an important practical teaching tool, widely used in science and technology innovation activities for primary and secondary school students. They must meet safety requirements for launch in simple, open spaces such as playgrounds, and the construction and operation process must offer good audience interaction. Typical domestic products in this field include single-stage model rockets such as "Little Hercules," "Divine Arrow," and "Long March 3." These products are simple in structure, easy to use, and relatively inexpensive, making them popular in science education. In addition, the "Flying Dream" rocket is another mainstream commercially available two-stage model rocket, but its performance in actual applications has been poor.

[0003] Existing model rocket technology suffers from numerous defects and shortcomings. Regarding second-stage ignition and separation, the "Flying Dream" rocket uses the first-stage engine's reverse-jet combustion to ignite the second-stage engine, frequently resulting in premature ignition or ignition failure. The second-stage delayed ignition scheme is essentially open-loop control, unable to prevent ignition timing anomalies, and cannot terminate second-stage ignition when the rocket's attitude, flight trajectory, or engine malfunctions, leading to extremely low safety. In terms of separation mechanisms, existing patents either rely on avionics-controlled separation mechanisms, resulting in high system complexity and low reliability, or the two stages are not fully connected, relying on drag or thrust for natural separation, posing a risk of accidental stage detachment during dramatic attitude changes. Regarding parachute deployment stability and safety, commercially available model rockets primarily rely on engine reverse-jet parachute deployment. This method demands stringent manufacturing skills, and reliable operation heavily depends on the experience and guidance of instructors. The use of scissors and glue in the manufacturing process is difficult to standardize, leading to poor consistency in finished products and frequent issues such as parachute burnout and deployment failure, compromising safety.

[0004] Most existing mainstream products use model rocket engine reverse-jet parachute recovery technology, and they are all very similar in terms of working method, structure, size, manufacturing method, and launch effect. After repeated participation in related activities, the audience may become bored. At the same time, the existing products differ significantly in structure from real sounding rockets and launch vehicles, which means that popular science based on physical objects can only cover superficial knowledge and is not conducive to in-depth explanation and teaching of aerospace-related knowledge. Summary of the Invention

[0005] The purpose of this invention is to provide a second-stage model rocket for popular science education purposes based on acceleration ignition determination. This invention solves the problems of existing model rockets for popular science education purposes, such as poor stability and low safety of second-stage ignition and separation, poor parachute opening consistency and easy failure, monotonous product form and lack of popular science appeal, and large differences in structure from real rockets, which are not conducive to in-depth explanation of aerospace knowledge.

[0006] To achieve the above objectives, the present invention provides a two-stage model rocket for popular science education purposes based on acceleration ignition determination. The model includes a two-stage main body, an interstage section, a first-stage main body, and avionics. The first-stage main body is located below the model and is connected to the second-stage main body through the interstage section. The secondary body includes a nose cone-load compartment, a load compartment floor, an avionics compartment, a parachute compartment, and a power section. These components are connected end-to-end with self-tapping screws to form the secondary body structure. The parachute compartment contains a parachute line connecting plate and a secondary parachute compartment torsion spring. The parachute line connecting plate is fixedly connected to the secondary body and to the main parachute lines of the secondary parachute. The secondary parachute compartment canopy is inserted into a slot in the parachute compartment. The secondary parachute compartment canopy is elastically connected to the parachute compartment via the secondary parachute compartment torsion spring. A servo motor is fixedly connected to the side of the parachute compartment. The servo motor output is connected to a servo motor rocker arm. The secondary parachute compartment canopy is constrained and locked by the servo motor rocker arm. The secondary parachute compartment canopy is connected to the head of the secondary parachute via a thin rope. The power section is equipped with a second-stage engine mount and a second-stage wing. The second-stage engine mount is fixed to the power section with fasteners. The second-stage model rocket engine is installed inside the second-stage engine mount. The second-stage wing is installed at the tail of the power section with self-tapping screws. The interstage section includes the interstage section body and the secondary connecting section. The top of the interstage section body is equipped with a positioning pin, which is inserted into the corresponding slot of the power section of the secondary body. The interstage section body is connected to the secondary body through the secondary connecting section. The interstage section body is fixedly connected with a flow guide plate, and a pad is set below the flow guide plate. The interstage section is locked to the primary and secondary bodies through a bolt-cotton rope sleeve assembly. The bolt-cotton rope sleeve assembly includes a nut, a lifting lug, a hexagonal stud, a bolt, and a cotton rope sleeve. The hexagonal stud is fixed to the interstage section body. The bolt passes through the lifting lug and is threaded to the hexagonal stud. The cotton rope sleeve is sleeved between the lifting lugs. Tightening the bolts tightens the cotton rope sleeve to achieve two-stage locking. The first-stage main body includes a first-stage engine mounting fixture and a first-stage wing. The first-stage engine mounting fixture is fixed inside the first-stage main body with fasteners. The first-stage model rocket engine is installed inside the first-stage engine mounting fixture. The first-stage wing is installed at the tail of the first-stage main body with self-tapping screws. The first-stage main body is equipped with a parachute compartment slot, in which the first-stage parachute compartment cover is inserted. In the two-stage connected state, it is limited and constrained by the second-stage wing of the second-stage main body. The first-stage main body is equipped with a parachute line fixing plate, which is connected to the main parachute lines of the first-stage parachute. A first-stage parachute compartment torsion spring is installed at the parachute compartment slot. The avionics system includes the main avionics unit, the switchboard, and the battery. The main avionics unit consists of a printed circuit board, a microcontroller, a six-axis sensor, a barometric pressure sensor, and peripheral components. The avionics system adopts a two-stage ignition determination method based on axial acceleration. The switchboard uses three toggle switches arranged in parallel, with adjacent switches closing in opposite directions.

[0007] Preferably, the main structure of the primary body, secondary body and inter-stage section is made of PLA or ABS plastic and is formed by 3D printing.

[0008] Preferably, the nose cone-load compartment is located on the top of the secondary main body, and the nose cone-load compartment can carry commonly used loads for popular science education; the avionics compartment is fixed with a pin-removable wall panel on the outside, and a battery fixing device is installed inside the power section. The avionics are fixed to the avionics compartment, and the battery fixing device is fixedly connected to the battery through a strip, and the battery is electrically connected to the avionics.

[0009] Preferably, the avionics system includes a disconnector and a disconnector panel. The disconnector is fixed to the disconnector panel, and the disconnector is connected to the launch pad by a rope. When the disconnector is inserted or disconnected, the second-stage engine ignition is locked by both hardware and software. When the disconnector falls off, a loudspeaker alarm is triggered.

[0010] Preferably, the axial acceleration determination logic is as follows: a determination acceleration is set, and when the six-axis sensor detects that the axial acceleration is less than the determination acceleration, the first-stage engine is determined to be burnt out.

[0011] Preferably, the secondary body adopts a lateral electronically controlled parachute deployment scheme. The canopy of the secondary parachute compartment is inserted into the parachute compartment slot and is constrained and locked by the servo arm. When the parachute is deployed, the avionics control servo drives the servo arm to rotate and release the constraint. The canopy of the secondary parachute compartment is released under the elastic force of the parachute compartment torsion spring, and the secondary parachute is pulled out simultaneously. The main parachute line of the secondary parachute is attached to the parachute line connecting plate, and the parachute line connecting plate is fixedly connected to the secondary body.

[0012] Therefore, the present invention employs the above-mentioned second-stage model rocket for popular science education purposes based on acceleration ignition determination, and the technical effects are as follows: 1. Improved stability of two-stage ignition and separation: Triple safety measures are added based on axial acceleration to avoid ignition abnormalities. The bolt-cotton rope thermal separation structure is simple and firmly connected, and the interstage section can be quickly replaced and reused.

[0013] 2. Stable and consistent parachute opening: Two-stage 3D printing molding, the first stage relies on the wing limit and torsion spring for parachute opening, and the second stage uses a servo motor and torsion spring for electric control of parachute opening, eliminating reliance on human experience and reducing the probability of failure.

[0014] 3. Strong popular science appeal and interactivity: Two-stage ignition achieves "relay propulsion", with strong audio-visual impact, avionics support data monitoring and analysis, and the payload bay can be customized for experiments, enhancing the sense of participation. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of a second-stage model rocket for popular science education purposes based on acceleration ignition determination, according to the present invention. Figure 2This is a schematic diagram of the main structure of the second stage of a model rocket for popular science education purposes based on acceleration ignition determination according to the present invention; (a) is a front view; (b) is a half-sectional view; (c) is a side view; Figure 3 This is a schematic diagram of the interstage section structure of a second-stage model rocket for popular science education purposes based on acceleration ignition determination according to the present invention; (a) is a front view; (b) is a half-sectional view; Figure 4 This is a schematic diagram of the main structure of the first stage of a second-stage model rocket for popular science education purposes based on acceleration ignition determination, according to the present invention; (a) is a front view; (b) is a half-sectional view; Figure 5 This is a schematic diagram illustrating the implementation method of locking the second-stage engine ignition in hardware on a second-stage model rocket for popular science education purposes based on acceleration ignition determination according to the present invention. Figure 6 This invention provides a schematic diagram of the axial acceleration-time curve of a second-stage model rocket for popular science education purposes, based on acceleration ignition determination. Figure 7 This is a schematic diagram of the second-stage ignition determination procedure for a second-stage model rocket for popular science education purposes based on acceleration ignition determination, according to the present invention.

[0016] Figure Labels 1. Secondary body; 2. Interstage section; 3. Primary body; 101. Nose cone-load compartment; 102. Load compartment floor; 103. Avionics compartment; 104. Parachute compartment; 105. Secondary parachute compartment canopy; 106. Power section; 107. Secondary missile wing; 108. Wiring terminal; 109. Secondary model rocket engine; 110. Secondary engine fixture; 111. Parachute line connection plate; 112. Servo rocker arm; 113. Servo; 114. Pin-off panel; 115. Battery mounting fixture; 116. 117. Power and control components; 201. Secondary parachute; 202. Secondary connecting section; 203. Interstage section body; 204. Guide plank; 205. Pad; 206. Nut; 207. Lifting lug; 208. Cotton rope sleeve; 209. Hexagonal stud; 201. Bolt; 301. First-stage parachute compartment canopy; 302. First-stage missile wing; 303. First-stage engine mounting fixture; 304. First-stage model rocket engine; 305. Parachute rope fixing plate; 306. Parachute compartment torsion spring; 307. First-stage parachute. Detailed Implementation

[0017] The technical solution of the present invention will be further described below with reference to the accompanying drawings and embodiments.

[0018] Unless otherwise defined, the technical or scientific terms used in this invention shall have the ordinary meaning as understood by one of ordinary skill in the art to which this invention pertains.

[0019] Example 1 like Figure 1 As shown, the present invention provides a two-stage model rocket for popular science education purposes based on acceleration ignition determination. The model includes a two-stage main body 1, an interstage section 2, a first-stage main body 3, and avionics. The first-stage main body 3 is located below the model and is connected to the second-stage main body 1 through the interstage section 2.

[0020] like Figure 2 As shown, the secondary main body 1 consists of a nose cone-payload compartment 101, a payload compartment floor 102, an avionics compartment 103, a parachute compartment 104, and a power section 106. These components are connected end-to-end with self-tapping screws to form a stable secondary main structure. The advantage of this connection method is its ease of assembly and disassembly, facilitating the demonstration and explanation of the internal structure in educational settings. Simultaneously, the self-tapping screw connection ensures the integrity and stability of the structure during flight, resisting overloads, aerodynamic loads, and vibrations.

[0021] The head cone-load chamber 101 is located on top of the secondary main body 1 and can carry commonly used loads for science education. Its connection with the load chamber bottom 102 provides a stable installation space for the loads, making it convenient to change different loads according to science education needs, thus enhancing the model's science education flexibility and interactivity.

[0022] The avionics bay 103 is fixed to a release pin panel 114 on its outer side. The release pin is attached to the release pin panel 114 and connected to the launch pad via a rope. This connection method achieves a dual hardware and software lock-in function for the second-stage engine ignition. When the release pin is inserted or removed, the second-stage engine cannot ignite. Only when the release pin falls off (the rocket leaves the launch pad) is the lock-in state released and a loudspeaker alarm triggered, greatly improving the safety of the launch process and avoiding dangerous situations such as accidental ignition.

[0023] The avionics are fixed inside the avionics compartment 103, and the power section 106 is equipped with a battery fixing device 115. The battery is fixedly connected to the battery fixing device 115 by a strip, and the battery is electrically connected to the avionics. The strip fixing method is simple and reliable, which can effectively prevent the battery from shifting due to vibration during flight, ensuring the stability of the avionics power supply and providing continuous and reliable energy support for the various electronic functions of the model rocket.

[0024] The parachute line connecting plate 111 inside the parachute compartment 104 is fixedly connected to the secondary body 1, and the parachute line connecting plate 111 is connected to the main parachute lines of the secondary parachute 117. This fixed connection method ensures that the secondary parachute 117 can withstand the impact force of the model when it is deployed, and prevents the parachute lines from falling off. The secondary parachute compartment canopy 105 is inserted into the slot of the parachute compartment 104. The secondary parachute compartment canopy 105 is elastically connected to the parachute compartment 104 through the secondary parachute compartment torsion spring, and is simultaneously constrained and locked by the servo rocker arm 112. The secondary parachute compartment canopy 105 is also connected to the head of the secondary parachute 117 through a thin rope. The combination of flexible connection and servo locking ensures the airtightness of the parachute canopy and enables rapid response during parachute deployment. By driving the rocker arm with the servo to release the constraint, the canopy is released under the force of the torsion spring, and the second-stage parachute 117 is pulled out simultaneously, realizing lateral electronically controlled parachute deployment. This eliminates the reliance on manufacturing skills and human experience required for traditional engine-assisted parachute deployment, and improves the consistency and reliability of parachute deployment.

[0025] The second-stage engine mount 110 on the power section 106 is secured with fasteners and houses the second-stage model rocket engine 109. The second-stage fins 107 are mounted on the tail of the power section 106 using self-tapping screws. The fasteners and self-tapping screws provide a secure and reliable connection, ensuring effective transmission of thrust generated by the second-stage engine during operation. Simultaneously, the stable mounting of the second-stage fins 107 ensures their proper functioning and contributes to the stability of the rocket's flight attitude.

[0026] like Figure 3 As shown, the interstage section 2 includes an interstage section body 202 and a secondary connecting section 201. The top of the interstage section body 202 is equipped with a positioning pin, which engages with the corresponding slot of the power section 106 of the secondary body 1. This engagement method enables rapid lateral positioning of the interstage section and the secondary body, ensuring accurate connection. The interstage section body 202 is connected to the secondary body 1 via the secondary connecting section 201, achieving axial connection between the two stages.

[0027] Interstage section 2 is locked to the primary stage body 3 and the secondary stage body 1 via a bolt-and-rope assembly. This assembly includes a nut 205, a lug 206, a hexagonal stud 208, a bolt 209, and a rope sleeve 207. The hexagonal stud 208 is fixed to the interstage section body 202. The bolt 209 passes through the lug 206 and is threadedly connected to the hexagonal stud 208. The rope sleeve 207 is fitted between the lugs 206. Tightening the bolt 209 tensions the rope sleeve 207, achieving two-stage locking. This bolt-and-rope thermal separation structure has many advantages: it is simple in structure, has a strong connection, effectively prevents accidental separation of the two stages during flight, and allows for smooth separation of the two stages after the primary engine burns out. Furthermore, the interstage section can be quickly replaced and reused, reducing the cost of science education.

[0028] The interstage section main body 202 is fixedly connected to a guide plank 203. A pad 204 is placed below the guide plank 203. The guide plank 203 directly bears the exhaust jet of the second-stage rocket engine, guiding the jet to all sides and preventing the jet from penetrating the plastic structure downwards. The pad 204 raises the guide plank 203 to a height slightly lower than the cotton rope sleeve 207, so that the guided jet directly impacts the cotton rope sleeve 207, improving the speed and reliability of first- and second-stage separation.

[0029] like Figure 4 As shown, the first-stage body 3 includes a first-stage engine mounting bracket 303 and a first-stage wing 302. The first-stage engine mounting bracket 303 is fixed inside the first-stage body 3 with fasteners, and the first-stage model rocket engine 304 is installed inside. The first-stage wing 302 is installed at the tail of the first-stage body 3 with self-tapping screws. Similar to the connection design of the second-stage body, the fasteners and self-tapping screws ensure the stability of the first-stage engine and wing installation. The first-stage wing 302 provides sufficient stability for the rocket's flight, ensuring a successful launch.

[0030] The primary body 3 has a parachute compartment slot, into which the primary parachute compartment cover 301 is inserted. In the two-stage connected state, it is constrained by the secondary wings 107 of the secondary body 1. The primary body 3 contains a parachute line fixing plate 305, which connects to the main parachute lines of the primary parachute 307. A primary parachute compartment torsion spring 306 is located at the parachute compartment slot and connected to the primary parachute compartment cover 301. This wing-constrained, torsion spring-opening design is ingenious, requiring no additional electronic control devices. When the two stages separate, the constraint of the primary parachute compartment cover 301 is released, and it automatically opens under the elastic force of the torsion spring 306, releasing the primary parachute 307 and achieving safe recovery of the primary body. This design reduces structural complexity and the probability of failure, ensuring reliable parachute opening.

[0031] The avionics system comprises the main avionics unit, a switchboard, and a battery. The main avionics unit consists of a printed circuit board, a microcontroller, a six-axis sensor, a barometric pressure sensor, and peripheral components. The switchboard uses three toggle switches arranged in parallel, with adjacent switches closing in opposite directions. This switch arrangement offers redundancy, preventing power outages caused by a single switch tripping due to vibration or overload during flight. This improves the reliability of the avionics system and ensures the normal operation of all control functions of the model rocket. The avionics system employs a second-stage ignition determination method based on axial acceleration. Axial acceleration is detected by the six-axis sensor, providing accurate criteria for second-stage ignition and ensuring timely and reliable ignition.

[0032] like Figures 5-7As shown, the second-stage ignition determination method based on axial acceleration is as follows: During the flight of the second-stage rocket in the dense atmosphere at low altitude, when the first-stage engine (assembly) burns out, the rocket will immediately begin to decelerate drastically under the influence of air resistance and gravity. The axial acceleration (with the direction from the tail to the nose cone as positive) will jump from a relatively large positive value to a very large negative value in a short period of time. During the period from the burnout of the first-stage engine to the establishment of effective thrust by the second-stage engine... Inside, the rocket's speed will undergo a rapid decrease. The amount of speed reduction during this process is... The function, and with Positive correlation. Obviously, to ensure efficiency, speed, and launch altitude, we want the time delay from first-stage burnout to second-stage ignition to be as short as possible.

[0033] Based on the characteristic of the sudden change in axial acceleration at the moment of burnout, and relying on the MPU6500 six-axis sensor and the bmp180 pressure sensor, this invention proposes an innovative method for determining the second stage ignition of a model rocket—based on axial acceleration.

[0034] To ensure "The time required to burn out the first-stage engine needs to be determined as quickly and accurately as possible in real time. When the rocket is stationary on the launch pad, the axial acceleration measured by the accelerometer is the acceleration due to gravity." (The actual measurement value of the sensor is the acceleration in the launch coordinate system and) (The vector sum, hereinafter assumed to be superposition); when the first-stage engine is working, the axial acceleration remains several times upward. Even more than ten times The high value; after the first stage of burnout, the axial acceleration changes abruptly and rapidly drops to a very large negative value. Mathematically, we can take the criterion acceleration. When the sensor detects an axial acceleration less than At that time, it was considered that the first stage of combustion was exhausted.

[0035] Considering practicalities, given the occasional errors in sensor data and the potential for sudden acceleration changes due to external forces before launch, it's impossible to use "measured acceleration < judgment acceleration" as the sole criterion for issuing the second-stage ignition command (otherwise, it might lead to second-stage ignition on the launch pad). To prevent accidental ignition, severe yaw, and other accidents, this project also uses three backup conditions for second-stage ignition determination: "pin detachment," "barometric altitude," and "rocket attitude." Furthermore, a loudspeaker sounds an alarm upon pin detachment to warn personnel, maximizing safety and reliability.

[0036] The overall workflow of a model rocket can be roughly divided into four stages: pre-launch preparation, launch and first-stage flight, second-stage ignition determination and separation, and recovery.

[0037] Pre-launch preparation phase: Assemble the second-stage main body 1, interstage section 2, and first-stage main body 3 according to the assembly requirements, ensuring all components are securely connected. Install the first-stage model rocket engine 304 into the first-stage engine mounting bracket 303, and the second-stage model rocket engine 109 into the second-stage engine mounting bracket 110, checking for stable engine installation. After charging the avionics system batteries, secure them to the battery mounting bracket 115 using straps, ensuring proper electrical connection between the batteries and avionics. Based on public education needs, load the corresponding public education payloads into the nose cone-payload compartment 101, close the first-stage parachute hatch 301 and the second-stage parachute hatch 105, ensuring the second-stage parachute hatch 105 is restrained and locked by the servo arm 112.

[0038] Launch and First-Stage Flight Phase: The assembled model rocket is placed on the launch pad, ensuring a reliable connection between the release pin and the launch pad via tethers. The release pin is inserted into the release mechanism, and the second-stage engine ignition is secured by both hardware and software to ensure safety before ignition. The launch procedure is initiated, and the first-stage model rocket engine 304 ignites, generating thrust to propel the entire rocket into the air. During ascent, the first-stage fin 302 and the second-stage fin 107 ensure flight stability. The avionics system operates in real time, with six-axis sensors and barometric pressure sensors continuously collecting data on the rocket's acceleration, altitude, and attitude, transmitting this data to the microcontroller for analysis and processing.

[0039] Second-stage ignition determination and separation phase: When the first-stage model rocket engine 304 burns out, the rocket's axial acceleration drops sharply. The six-axis sensor detects that the axial acceleration is less than the set threshold acceleration, and the microcontroller determines that the first-stage engine has burned out. If the atmospheric pressure altitude is greater than the safety altitude and the attitude is within limits, a second-stage ignition command is issued. If the attitude exceeds limits multiple times consecutively, the ignition command is locked, and ignition is no longer attempted, avoiding danger and improving safety. The second-stage model rocket engine 109 ignites, generating thrust. Simultaneously, the cotton rope is burned off under the impact of the second-stage engine jet, achieving separation of the first-stage main body 3 from the second-stage main body 1 and the interstage section 2.

[0040] Recovery Phase: After the primary body 3 separates from the secondary body, the limiting constraint of the primary parachute canopy 301 is released, and it automatically opens under the elastic force of the primary parachute torsion spring 306. The primary parachute 307 deploys under the action of airflow, carrying the primary body 3 down slowly, achieving safe recovery of the primary body. The secondary body 1 continues to fly. When the predetermined parachute deployment conditions are met, the avionics control servo 113 drives the servo arm 112 to rotate, releasing the constraint on the secondary parachute canopy 105. The secondary parachute canopy 105 detaches under the elastic force of the secondary parachute torsion spring, and the secondary parachute 117 is simultaneously pulled out by a thin rope. After the secondary parachute 117 deploys, it carries the secondary body 1 and the interstage section 2 down slowly, achieving safe recovery of the secondary body and the interstage section.

[0041] Therefore, this invention adopts a two-stage model rocket for popular science education purposes based on acceleration ignition determination. The avionics uses axial acceleration as the core determination criterion, combined with altitude and attitude detection to form a triple insurance to achieve two-stage ignition control. The switch board adopts a redundant design with three toggle switches connected in parallel and adjacent closing directions in opposite directions. It also has a hardware and software dual-ignition lock-up mechanism for disengagement and pin release, as well as a buzzer warning mechanism. The interstage section achieves stable locking and smooth thermal separation of the two stages through a bolt-cotton rope sleeve assembly. The first stage adopts a wing-limiting-torsion spring parachute deployment method, and the second stage adopts a servo-torsion spring lateral electronically controlled parachute deployment scheme. The nose cone-payload compartment can carry customized popular science payloads. This invention effectively solves the problems of poor stability, low safety, poor parachute deployment consistency, insufficient popular science appeal, and large differences in structure from real rockets in existing model rockets. It combines reliability, interactivity, and educational value.

[0042] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and not to limit them. Although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can still be made to the technical solutions of the present invention, and these modifications or equivalent substitutions cannot cause the modified technical solutions to deviate from the spirit and scope of the technical solutions of the present invention.

Claims

1. A second-stage model rocket for popular science education purposes based on acceleration ignition determination, characterized in that, The model includes a secondary main body, an inter-level section, a primary main body, and avionics. The primary main body is located at the bottom of the model and is connected to the secondary main body through the inter-level section. The secondary body includes a nose cone-load compartment, a load compartment floor, an avionics compartment, a parachute compartment, and a power section. These components are connected end-to-end with self-tapping screws to form the secondary body structure. The parachute compartment contains a parachute line connecting plate and a secondary parachute compartment torsion spring. The parachute line connecting plate is fixedly connected to the secondary body and to the main parachute lines of the secondary parachute. The secondary parachute compartment canopy is inserted into a slot in the parachute compartment. The secondary parachute compartment canopy is elastically connected to the parachute compartment via the secondary parachute compartment torsion spring. A servo motor is fixedly connected to the side of the parachute compartment. The servo motor output is connected to a servo motor rocker arm. The secondary parachute compartment canopy is constrained and locked by the servo motor rocker arm. The secondary parachute compartment canopy is connected to the head of the secondary parachute via a thin rope. The power section is equipped with a second-stage engine mount and a second-stage wing. The second-stage engine mount is fixed to the power section with fasteners. The second-stage model rocket engine is installed inside the second-stage engine mount. The second-stage wing is installed at the tail of the power section with self-tapping screws. The interstage section includes the interstage section body and the secondary connecting section. The top of the interstage section body is equipped with a positioning pin, which is inserted into the corresponding slot of the power section of the secondary body. The interstage section body is connected to the secondary body through the secondary connecting section. The interstage section body is fixedly connected with a flow guide plate, and a pad is set below the flow guide plate. The interstage section is locked to the primary and secondary bodies through a bolt-cotton rope sleeve assembly. The bolt-cotton rope sleeve assembly includes a nut, a lifting lug, a hexagonal stud, a bolt, and a cotton rope sleeve. The hexagonal stud is fixed to the interstage section body. The bolt passes through the lifting lug and is threaded to the hexagonal stud. The cotton rope sleeve is sleeved between the lifting lugs. Tightening the bolts tightens the cotton rope sleeve to achieve two-stage locking. The first-stage main body includes a first-stage engine mounting fixture and a first-stage wing. The first-stage engine mounting fixture is fixed inside the first-stage main body with fasteners. The first-stage model rocket engine is installed inside the first-stage engine mounting fixture. The first-stage wing is installed at the tail of the first-stage main body with self-tapping screws. The first-stage main body is equipped with a parachute compartment slot, in which the first-stage parachute compartment cover is inserted. In the two-stage connected state, it is limited and constrained by the second-stage wing of the second-stage main body. The first-stage main body is equipped with a parachute line fixing plate, which is connected to the main parachute lines of the first-stage parachute. A first-stage parachute compartment torsion spring is installed at the parachute compartment slot. The avionics system includes the main avionics unit, the switchboard, and the battery. The main avionics unit consists of a printed circuit board, a microcontroller, a six-axis sensor, a barometric pressure sensor, and peripheral components. The avionics system adopts a two-stage ignition determination method based on axial acceleration. The switchboard uses three toggle switches arranged in parallel, with adjacent switches closing in opposite directions.

2. The second-stage model rocket for popular science education purposes based on acceleration ignition determination according to claim 1, characterized in that, The main structures of the primary body, secondary body, and inter-level sections are made of PLA or ABS plastic and are formed by 3D printing.

3. A second-stage model rocket for popular science education purposes based on acceleration ignition determination according to claim 1, characterized in that, The nose cone-payload compartment is located on top of the secondary main body and can carry payloads commonly used in science education. The avionics compartment is fixed with a pin-detachable wall panel on the outside, and the power section is equipped with a battery fixing device. The avionics are fixed to the avionics compartment, and the battery fixing device is fixed to the battery through a strip. The battery is electrically connected to the avionics.

4. A second-stage model rocket for popular science education purposes based on acceleration ignition determination according to claim 1, characterized in that, The avionics system includes a release plate and a release pin panel. The release plate is fixed to the release pin panel, and the release pin is connected to the launch pad by a tether. When the release pin is inserted into or removed, the second-stage engine ignition is locked by both hardware and software. When the release pin falls off, a loudspeaker beeping warning is triggered.

5. A second-stage model rocket for popular science education purposes based on acceleration ignition determination according to claim 1, characterized in that, The axial acceleration determination logic is as follows: set the determination acceleration, and when the six-axis sensor detects that the axial acceleration is less than the determination acceleration, determine that the first-stage engine has burned out.

6. A second-stage model rocket for popular science education purposes based on acceleration ignition determination according to claim 1, characterized in that, The second-stage main body adopts a lateral electronically controlled parachute deployment scheme. The canopy of the second-stage parachute compartment is inserted into the parachute compartment slot and is restrained and locked by the servo arm. When the parachute is deployed, the avionics control servo drives the servo arm to rotate and release the restraint. The canopy of the second-stage parachute compartment is released under the elastic force of the parachute compartment torsion spring, and the second-stage parachute is pulled out simultaneously. The main parachute line of the second-stage parachute is attached to the parachute line connecting plate, and the parachute line connecting plate is fixedly connected to the second-stage main body.

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