Simulation training rocket
By designing a simulated training rocket, including the rocket body, pyrotechnic system, attitude control simulation components, etc., the problems of high cost and poor operating experience of existing simulated training rockets have been solved, and full-scene, full-process actual operation simulation and high-frequency training have been achieved.
Patent Information
- Application Number
- CN202510565588.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-30
- Publication Date
- 2025-09-19
AI Technical Summary
Existing simulation training rockets are expensive and difficult to train operational details, virtual reality training systems are expensive, and software simulation calculations lack the actual operational experience.
A simulated training rocket is designed, including a rocket body, pyrotechnic system, attitude control simulation components, control system and measurement system. The simulated engine is consistent with the real rocket, providing a practical operation experience, and meeting the needs of on-the-job operators through detachable connections.
It realizes risk-free actual operation simulation of the entire scene and the entire process, provides actual operation experience, exercises operation details, reduces costs, and meets the needs of high-frequency repeated use.
Smart Images
Figure CN120667980A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the technical field of training rockets, in particular to a simulation training rocket. Background Art
[0002] Solid rockets are characterized by high risk and irreversibility because their propellants enter the space launch site in a pre-packaged mode. This makes it difficult for test and launch personnel to conduct high-frequency, repeatable live-fire training. They usually use simulated training rockets instead of live ammunition for training.
[0003] Among existing simulated training rockets, one method uses a virtual reality training system. Personnel can complete training in a virtual environment built indoors without having to go to the actual rocket launch site. This method uses virtual reality technology to build a realistic rocket launch scene, including the layout of the launch site and the appearance details of the rocket, with strong simulation. However, the sensors and other related equipment it relies on are expensive, and subsequent maintenance costs are high, resulting in extremely high costs for long-term use. In addition, virtual scenes make it difficult to train operational details, and the training effect for actual operators is poor.
[0004] The other method is to use software for simulation calculations. This method mainly simulates and calculates various parameters and physical phenomena in the rocket launch process by establishing mathematical models and algorithms. The personnel input relevant data and operating instructions on the computer, and the software will output the simulation results in real time, thereby realizing simulation training of the rocket launch process. This method significantly reduces costs, but this method lacks actual operating experience and is only suitable for theoretical teaching or auxiliary demonstrations.
[0005] Therefore, the existing simulation training rockets, if using the virtual reality training system, have the defects of high cost and difficulty in training operational details. If using software simulation calculation, although the cost problem is solved, there is still the defect of lack of actual operating experience. Summary of the Invention
[0006] In view of this, the present invention provides a simulation training rocket to solve the problem that the existing simulation training rocket is difficult to train operation details, has poor training effect for job operators, and lacks actual operation experience.
[0007] In the first aspect, the present invention provides a simulated training rocket, comprising: a rocket body, comprising an arrow, a shaft and a tail section, the arrow and the tail section being detachably connected to the shaft, respectively, and the shaft having a simulated engine; a pyrotechnic system, comprising a first simulated pyrotechnic unit, the first simulated pyrotechnic unit being arranged at the connection position between the shaft and the arrow; an attitude control simulation component, arranged inside the arrow, the attitude control simulation component having a simulated tank; a control system, arranged inside the arrow, and electrically connected to the first simulated igniter and the first simulated pyrotechnic unit; a measurement system, arranged inside the arrow, and electrically connected to the first simulated igniter and the first simulated pyrotechnic unit.
[0008] Beneficial effects: By setting up a simulated training rocket to replace the real rocket during training, job operators can use the simulated training rocket to complete a series of rocket-related tasks, thereby achieving training effects. At the same time, the simulated training rocket can meet the needs of high frequency and repeated use, replacing the virtual reality or software simulation calculation method used in related technologies for training, and realizing risk-free actual operation simulation of full-scene and full-process tasks, providing actual operation experience, and exercising operation details, which has a good training effect on job operators.
[0009] Beneficial effect: By setting up a simulation training rocket, the simulation training rocket includes a rocket body composed of an arrow, a body and a detachably connected tail section, a simulated engine arranged at the body, a first simulated pyrotechnic unit arranged between the body and the arrow, and an attitude control simulation component, a control system and a measurement system arranged in the arrow, the contact and disassembly needs of the actual operators are met, and the disassembly and assembly feel and the contact experience are consistent with those of a real rocket, providing a practical operation experience; at the same time, the pyrotechnic component (the first simulated igniter and the first simulated pyrotechnic unit) is electrically connected to the control system and the measurement system respectively, meeting the requirements of the pyrotechnic component resistance test and providing a practical operation experience; in addition, the overall simulation training rocket can also meet the field operation requirements such as rocket hoisting, transporting onto a vehicle, erecting and launching (simulated operation, not actual launching) with the help of ground support equipment in daily simulation training, that is, meeting the practical operation needs of the operators; the structural characteristics and electrical characteristics of each simulated component in the training simulation rocket are consistent with those of the real rocket, training the operation details, and the training effect is good, while being safe and reliable.
[0010] Beneficial effects: The simulated training rocket can also meet the needs of teaching and training on basic principles and technical methods related to solid rockets, such as the structural composition of solid rockets, the working principles of on-board equipment, flight control principles (attitude control simulation components), and on-board fault analysis, thereby reducing costs; the simulated training rocket can complete field operation needs such as rocket lifting, transporting onto vehicles, and erecting and launching (simulated operations, not actual launch) through ground support equipment combined with a mobile launch platform; the power system (simulated engine), liquid propulsion attitude control power system (attitude control simulation components), and pyrotechnic system (including but not limited to the first simulated pyrotechnic unit) of this simulated training rocket all use simulated parts, which ensures the safety and reliability of the simulated training rocket when used while meeting the actual operation training.
[0011] In an optional embodiment, the arrow includes a fairing front cover, a transfer cabin, a propulsion control cabin and a fairing rear cover; the attitude control simulation component, the control system and the measurement system are all arranged in the propulsion control cabin; the transfer cabin connects the fairing front cover and the propulsion control cabin, the fairing rear cover is arranged on the periphery of the propulsion control cabin, and the end of the fairing rear cover is connected to the transfer cabin; a first simulation separation component is also provided in the arrow, the first simulation separation component includes a simulation cylinder and a second simulation pyrotechnic part, the second simulation pyrotechnic part is arranged at the connection position between the fairing front cover and the transfer cabin, the simulation cylinder is arranged in the fairing front cover, and is arranged close to the transfer cabin.
[0012] In an optional embodiment, the simulated engine includes a first-stage engine, a second-stage engine and a third-stage engine; the arrow body also includes a transition section, a first interstage section and a second interstage section; the first end of the first-stage engine is detachably connected to the tail section, and the second end is detachably connected to the first interstage section; the first end of the second-stage engine is connected to the first interstage section, and the second end is detachably connected to the second interstage section; the first end of the third-stage engine is connected to the second interstage section, and the second end is detachably connected to the transition section; the side of the transition section facing away from the third-stage engine is connected to the rear cover of the fairing.
[0013] In an optional embodiment, the pyrotechnic system further includes a third simulated pyrotechnic unit and a fourth simulated pyrotechnic unit, wherein the third simulated pyrotechnic unit is located at the connection position between the transition section and the third-stage engine, and the fourth simulated pyrotechnic unit is located at the connection position between the first-stage engine and the first interstage section.
[0014] In an optional embodiment, it further includes a second simulated separation component, which includes a fifth simulated pyrotechnic unit and a simulated booster; the fifth simulated pyrotechnic unit is arranged at the connection position between the second-stage engine and the second interstage section, and the simulated booster is arranged at the second interstage section.
[0015] In an optional embodiment, the pyrotechnic system further includes a self-destruction simulation pyrotechnic unit, and at least three of the self-destruction simulation pyrotechnic units are respectively arranged inside the first-stage engine, the second-stage engine, and the third-stage engine.
[0016] In an optional embodiment, the second simulated pyrotechnic unit, the third simulated pyrotechnic unit, the fourth simulated pyrotechnic unit, the fifth simulated pyrotechnic unit and the self-destruction simulated pyrotechnic unit are electrically connected to the control system respectively; the second simulated pyrotechnic unit, the third simulated pyrotechnic unit, the fourth simulated pyrotechnic unit, the fifth simulated pyrotechnic unit and the self-destruction simulated pyrotechnic unit are electrically connected to the measurement system respectively.
[0017] In an optional embodiment, the posture control simulation component further includes a shell, and at least two of the simulation tanks are disposed in the shell.
[0018] In an optional embodiment, the attitude control simulation component further includes a simulated gas cylinder, a simulated attitude control engine and a simulated orbit control engine, and the simulated gas cylinder, the simulated attitude control engine and the simulated orbit control engine are respectively arranged on the outside of the shell. BRIEF DESCRIPTION OF THE DRAWINGS
[0019] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the specific embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.
[0020] Figure 1 This is a schematic diagram of the structure of the simulation training rocket of the present invention;
[0021] Figure 2 Schematic diagram of the structure of the posture control simulation component of the present invention.
[0022] Description of reference numerals:
[0023] 1. Arrow; 11. First simulated pyrotechnic unit; 12. Fairing front cover; 13. Adapter cabin; 14. Propulsion control cabin; 15. Fairing rear cover;
[0024] 2. Rocket body; 21. First stage engine; 211. First interstage section; 212. Fourth simulated pyrotechnics section; 22. Second stage engine; 221. Second interstage section; 23. Third stage engine; 231. Third simulated pyrotechnics section; 24. Transition section; 25. Self-destruction simulated pyrotechnics section;
[0025] 3. Tail section;
[0026] 4. Attitude control simulation component; 41. Shell; 42. Simulated tank; 43. Simulated gas cylinder; 44. Simulated attitude control engine; 45. Simulated orbit control engine;
[0027] 5. Control system;
[0028] 6. Measurement system;
[0029] 7. First simulated separation component; 71. Simulated cylinder; 72. Second simulated ignition unit;
[0030] 8. Second simulated separation assembly; 81. Fifth simulated pyrotechnic unit; 82. Simulated booster. DETAILED DESCRIPTION
[0031] To make the purpose, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without making creative efforts shall fall within the scope of protection of the present invention.
[0032] In the description of the present invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely to facilitate and simplify the description of the present invention. They are not intended to indicate or imply that the devices or components referred to must have, be constructed, or operate in a specific orientation, and therefore should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.
[0033] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood in a broad sense. For example, they may refer to fixed, detachable, or integral connections; mechanical or electrical connections; direct or indirect connections through an intermediate medium; and internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.
[0034] In addition, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.
[0035] The following combination Figures 1 to 2 , describing embodiments of the present invention.
[0036] According to an embodiment of the present invention, a simulated training rocket is provided, comprising: a rocket body, comprising an arrow 1, a body 2 and a tail section 3, wherein the arrow 1 and the tail section 3 are detachably connected to the body 2, respectively, and the body 2 has a simulated engine; a pyrotechnic system, comprising a first simulated pyrotechnic unit 11, wherein the first simulated pyrotechnic unit 11 is arranged at the connection position between the body 2 and the arrow 1; a posture control simulation component 4, arranged inside the arrow 1, wherein the posture control simulation component 4 has a simulated tank 42; a control system 5, arranged inside the arrow 1, and electrically connected to the first simulated igniter and the first simulated pyrotechnic unit 11; a measuring system 6, arranged inside the arrow 1, and electrically connected to the first simulated igniter and the first simulated pyrotechnic unit 11.
[0037] Combine Figure 1 As shown, the dimensions of the rocket body components are consistent with those of the official rocket product. The lengths, diameters and assembly relationships of the arrowhead 1, the rocket body 2 and the tail section 3 are consistent with those of the real rocket, ensuring that the overall aspect ratio and structural layout of the simulated rocket are consistent with those of the real rocket. The mechanical interfaces at the connection positions between the rocket body components are consistent with those of the official rocket product, and the load-bearing capacity and torque requirements of the connecting components (such as bolts, flanges, and clips) used at the connection positions are the same as those of the real components, ensuring that the force and operating procedures required for disassembly and assembly by the operator are consistent with those of the real rocket.
[0038] It should be noted that the simulated engine is a simulated component, and the simulated component is an existing structure, which is consistent with the structure of the real engine. The difference is that there is no real propellant inside the simulated engine, and a first simulated igniter is set at the nozzle mouth. The structure of the first simulated igniter is consistent with the real igniter. The difference is that the first simulated igniter has a built-in resistor instead of the simulated real igniter bridge wire; when the first simulated igniter receives the ignition signal from the control system 5, the resistance power is increased, so that the surface temperature of the resistor quickly rises to 300°C to simulate the ignition point of the ignition charge column, and the resistance value and temperature signal are fed back to the measurement system 6 in real time.
[0039] It should be noted that the first simulated pyrotechnic part 11 is a simulated pyrotechnic device. The simulated pyrotechnic device is an existing structure. Its external mechanical structure and internal circuit design (such as resistance, capacitance and other parameters) are exactly the same as those of real pyrotechnic devices, but it does not contain explosives, propellants or other hazardous materials of real pyrotechnic devices, and meets the needs of mechanical disassembly and resistance testing.
[0040] It should be noted that the attitude control simulation assembly 4 is a simulated component with an existing structure. Its simulated tank 42 does not contain propellant, and the dimensions of the shell 41 and the simulated tank 42 are consistent with those of the real components. In addition, a hollow counterweight structure is set inside the simulated tank 42. By filling the counterweight with low-density foam, the total mass is consistent with the mass of a real tank containing propellant. At the same time, the same mechanical interfaces as the real tank, such as flanges, are used to ensure that the disassembly and assembly feel is consistent with that of the real tank.
[0041] It should be noted that the control system 5 uses the same control components as a real rocket, including but not limited to existing components such as a central computer, an integrated controller, a tail section 3 controller, a fiber optic inertial measurement combination, a servo and a pyrotechnic control mechanism, as well as a final-stage battery and a tail section 3 battery. The control system 5 is electrically connected to other components such as the first simulated pyrotechnic unit 11 and the simulated ignition unit through a cable network; among them, the final-stage battery and the tail section 3 battery are replaced by safe process batteries to provide a stable test voltage to meet the resistance test requirements of pyrotechnics (first simulated igniter, first simulated pyrotechnic unit 11) and eliminate the high energy risk of real batteries.
[0042] It should be noted that the measurement system 6 uses the same test components as the real rocket, including but not limited to the existing components such as the measurement and control center unit, phased array antenna, FM transmitter and antenna, editor, GPS / BD2 antenna, pulse coherent transponder, antenna and sensor. The measurement system 6 is electrically connected to the components to be tested (such as the first simulated pyrotechnics unit 11 and the simulated ignition unit) through the cable network, and collects data through the cable network.
[0043] In this embodiment, a simulation training rocket is provided, and the simulation training rocket includes a rocket body composed of an arrow 1, a rocket body 2 and a tail section 3 that are detachably connected, and a simulated engine arranged at the rocket body 2, a first simulated pyrotechnic part 11 arranged between the rocket body 2 and the arrow 1, and an attitude control simulation component 4, a control system 5 and a measurement system 6 arranged in the arrow 1, so as to meet the contact and disassembly and assembly needs of the job operators, ensure that the disassembly and assembly feel and the contact experience are consistent with those of the real rocket, and provide a practical operation experience; at the same time, the pyrotechnic component (the first simulated igniter and the first simulated pyrotechnic part 11) is electrically connected to the control system 5 and the measurement system 6 respectively, to meet the requirements of the pyrotechnic component resistance test and provide a practical operation experience; in addition, the overall simulation training rocket can also meet the field operation requirements such as rocket lifting, transporting onto a vehicle, erecting and launching (simulated operation, not actually launching) with the help of ground support equipment in daily simulation training, that is, to meet the practical operation needs of the job operators; the structural characteristics and electrical characteristics of each simulated component in the training simulation rocket are consistent with those of the real rocket, so as to train the operation details, achieve good training effects, and be safe and reliable.
[0044] The simulation training rocket provided in this embodiment can also meet the needs of carrying out teaching and training on basic principles and technical methods related to solid rockets, such as solid rocket structure composition, working principle of on-board equipment, flight control principle (attitude control simulation component 4), on-board fault analysis, etc., and reduce costs; the simulation training rocket can complete the field operation needs such as rocket lifting, transporting onto the vehicle, erecting and launching (simulated operation, not actual launch) through ground support equipment combined with a mobile launch platform; the power system (simulated engine), liquid propulsion attitude control power system (attitude control simulation component 4), and pyrotechnic system (including but not limited to the first simulated pyrotechnic part 11) of this simulation training rocket all use simulation parts, which ensures the safety and reliability of the simulation training rocket when used while meeting the actual operation training.
[0045] Preferably, the mechanical interface, external dimensions and dimensional parameters of the simulated engine are consistent with those of the official rocket product; specifically, on the first aspect, the mechanical interface of the simulated engine is consistent with that of the real engine, and the connection structural features (such as the bolt hole position, flange size, buckle shape, sealing interface) of the simulated engine (such as the first-stage engine 21, the second-stage engine 22, and the third-stage engine 23) and the adjacent components (such as the tail section 3, the first interstage section 211, the second interstage section 221, and the transition section 24) are consistent with those of the real engine, ensuring that operators can use real tools for disassembly and assembly training.
[0046] In some embodiments, the arrow 1 includes a fairing front cover 12, a transfer cabin 13, a propulsion control cabin 14 and a fairing rear cover 15; the attitude control simulation component 4, the control system 5 and the measurement system 6 are all arranged in the propulsion control cabin 14; the transfer cabin 13 connects the fairing front cover 12 and the propulsion control cabin 14, the fairing rear cover 15 is arranged on the periphery of the propulsion control cabin 14, and the end of the fairing rear cover 15 is connected to the transfer cabin 13; a first simulation separation component 7 is also provided in the arrow 1, the first simulation separation component 7 includes a simulation cylinder 71 and a second simulation pyrotechnic part 72, the second simulation pyrotechnic part 72 is arranged at the connection position between the fairing front cover 12 and the transfer cabin 13, the simulation cylinder 71 is arranged in the fairing front cover 12, and is arranged close to the transfer cabin 13.
[0047] It should be noted that the first simulated separation component 7 is a simulation part, which is used to simulate the action signals generated by the simulated cylinder 71 and the second simulated pyrotechnics during separation. There is no actual separation, and it only serves as training and teaching. The simulated cylinder 71 and the second simulated pyrotechnics part 72 are both simulation parts. The size of the simulated cylinder 71 is consistent with that of the real cylinder. The difference from the real cylinder may be, but is not limited to, the use of a servo motor instead of high-pressure gas drive to simulate the action signals generated when the real cylinder is separated. The simulated cylinder 71 is an existing component and will not be described in detail here. The second simulated pyrotechnics part 72 is a simulated pyrotechnic, and its external mechanical structure and internal circuit design (such as resistance, capacitance and other parameters) are exactly the same as those of a real pyrotechnic, but does not contain explosives, propellants or other hazardous materials of a real pyrotechnic, and meets the requirements of mechanical disassembly and resistance testing. The simulated pyrotechnics are existing components and will not be described in detail here.
[0048] Specifically, the fairing front cover 12 is the front-end component of the arrow 1, and its structural dimensions are the same as those of the fairing front cover 12 of a real rocket; a plurality of second simulated pyrotechnic parts 72 are axially evenly distributed at the docking surface between the fairing front cover 12 and the adapter cabin 13, and a plurality of simulated cylinders 71 are connected to the fairing front cover 12; the adapter cabin 13 is connected between the fairing front cover 12 and the propulsion control cabin 14, and the structural dimensions of the adapter cabin 13 are the same as those of the adapter cabin 13 of a real rocket, and the mechanical interface at the connection position between the adapter cabin 13 and the fairing is the same as that of a real rocket, such as the same connecting components used (such as bolts, flanges or snaps), and the same connection structural features (such as bolt hole position, flange size, snap shape or sealing interface); the fairing rear cover 15 is sleeved on the peripheral side of the propulsion control cabin 14, and the opposite sides of the fairing rear cover 15 are respectively connected to the adapter cabin 13 and the transition section 24.
[0049] In some embodiments, the simulated engine includes a first-stage engine 21, a second-stage engine 22 and a third-stage engine 23; the arrow body 2 also includes a transition section 24, a first interstage section 211 and a second interstage section 221; the first end of the first-stage engine 21 is detachably connected to the tail section 3, and the second end is detachably connected to the first interstage section 211; the first end of the second-stage engine 22 is connected to the first interstage section 211, and the second end is detachably connected to the second interstage section 221; the first end of the third-stage engine 23 is connected to the second interstage section 221, and the second end is detachably connected to the transition section 24; the side of the transition section 24 facing away from the third-stage engine 23 is connected to the fairing rear cover 15.
[0050] Specifically, the simulated engines are provided with at least three, namely, a first-stage engine 21, a second-stage engine 22, and a third-stage engine 23, and the first-stage engine 21, the second-stage engine 22, and the third-stage engine 23 are all simulated parts; the mechanical interface at the connection between the first-stage engine 21 and the tail section 3 is consistent with the mechanical interface at the corresponding position of the real rocket, such as the same connecting parts used (such as bolts, flanges or snaps), and the same connection structure features (such as bolt hole position, flange size, snap shape or sealing interface).
[0051] In some embodiments, the pyrotechnic system further includes a third simulated pyrotechnic unit 231 and a fourth simulated pyrotechnic unit 212. The third simulated pyrotechnic unit 231 is arranged at the connection position between the transition section 24 and the third-stage engine 23, and the fourth simulated pyrotechnic unit 212 is arranged at the connection position between the first-stage engine 21 and the first inter-stage section 211.
[0052] Specifically, multiple third simulated pyrotechnic parts 231 are arranged at the interface between the transition section 24 and the third-stage engine 23, and multiple fourth simulated pyrotechnic parts 212 are arranged at the interface between the first-stage engine 21 and the first-stage intersection 211. The third simulated pyrotechnic parts 231 and the fourth simulated pyrotechnic parts 212 are both simulated pyrotechnic products. The external mechanical structure and internal circuit design (such as resistance, capacitance and other parameters) are exactly the same as real pyrotechnic products, but do not contain explosives, propellants or other hazardous materials of real pyrotechnic products, which meet the needs of mechanical disassembly and resistance testing. The simulated pyrotechnic products are existing components and will not be repeated here.
[0053] In some embodiments, it also includes a second simulated separation component 8, which includes a fifth simulated pyrotechnic unit 81 and a simulated booster 82; the fifth simulated pyrotechnic unit 81 is arranged at the connection position between the second-stage engine 22 and the second interstage section 221, and the simulated booster 82 is arranged at the second interstage section 221.
[0054] Specifically, the second simulated separation component 8 is a simulation component, which is used to simulate the action signals generated by the simulated booster 82 and the fifth simulated pyrotechnic during separation. There is no actual separation, and it only serves the purpose of training and teaching. The simulated booster 82 and the second simulated pyrotechnic part 72 are both simulation components. The simulated booster 82 is a separation engine, and its structure and size are consistent with the real separation engine, but the difference is that it does not contain propellant, and a second simulated igniter is set at the nozzle mouth. The second simulated igniter has the same structure as the real igniter, but the difference is that the first simulated igniter has a built-in resistor instead of the simulated real igniter bridge wire. The simulated igniter is an existing component and will not be repeated here. When receiving the ignition signal from the control system 5, the resistance power is increased to make the surface temperature of the resistor rise rapidly to simulate the ignition point of the ignition charge column, and the resistance value and temperature signal are fed back to the measurement system 6 in real time.
[0055] In some embodiments, the pyrotechnic system further includes a self-destruction simulation pyrotechnic unit 25 , and at least three of the self-destruction simulation pyrotechnic units 25 are respectively disposed inside the first-stage engine 21 , the second-stage engine 22 , and the third-stage engine 23 .
[0056] Specifically, the self-destruction simulation pyrotechnic unit 25 is a simulated pyrotechnic device. Its external mechanical structure and internal circuit design (such as resistance, capacitance and other parameters) are exactly the same as those of a real pyrotechnic device, but it does not contain the explosives, propellants or other hazardous materials of a real pyrotechnic device, and meets the requirements of mechanical disassembly and assembly and resistance testing. The simulated pyrotechnic device is an existing component and will not be described in detail here. When the self-destruction simulation pyrotechnic unit 25 receives the self-destruction command issued by the control system 5, the resistance of the internal resistor of the self-destruction simulation pyrotechnic unit 25 drops sharply, and simultaneously sends a self-destruction activation signal and a resistance value change signal to the test system to simulate the action of the safe self-destruction pyrotechnic device in a real rocket.
[0057] In some embodiments, the second simulated pyrotechnic unit 72, the third simulated pyrotechnic unit 231, the fourth simulated pyrotechnic unit 212, the fifth simulated pyrotechnic unit 81 and the self-destruction simulated pyrotechnic unit 25 are electrically connected to the control system 5 respectively; the second simulated pyrotechnic unit 72, the third simulated pyrotechnic unit 231, the fourth simulated pyrotechnic unit 212, the fifth simulated pyrotechnic unit 81 and the self-destruction simulated pyrotechnic unit 25 are electrically connected to the measurement system 6 respectively.
[0058] Specifically, the second simulated pyrotechnic unit 72, the third simulated pyrotechnic unit 231, the fourth simulated pyrotechnic unit 212, the fifth simulated pyrotechnic unit 81 and the self-destruction simulated pyrotechnic unit 25 are respectively electrically connected to the control system 5 and the measurement system 6 by means of a cable network. The cable network is an existing component and will not be described in detail here; the control system 5 sends a signal to the simulated pyrotechnic product to simulate the action of the pyrotechnic product, and sends the corresponding resistance change signal to the measurement system 6.
[0059] In some embodiments, the attitude control simulation component 4 also includes a shell 41, and at least two of the simulated tanks 42 are arranged in the shell 41; the attitude control simulation component 4 also includes a simulated gas cylinder 43, a simulated attitude control engine 44 and a simulated orbit control engine 45, and the simulated gas cylinder 43, the simulated attitude control engine 44 and the simulated orbit control engine 45 are respectively arranged on the outside of the shell 41.
[0060] Specifically, a hollow counterweight structure is respectively provided inside at least two simulated tanks 42, and by filling the counterweight blocks with low-density foam, the total mass is made consistent with the mass of a real tank containing propellant; at least two simulated gas cylinders 43 are provided on the top side of the shell 41, and the structure of the simulated gas cylinders 43 is consistent with that of the real gas cylinders, except that they are filled with inert gas; the simulated attitude control engine 44 and the simulated orbit control engine 45 are both simulated parts, and the structure and size are consistent with the real engine, but the difference is that they do not contain propellant and have no propulsion capability, and only simulate the signal when the real propulsion control engine is in action. The simulated parts are existing structures and will not be described in detail here.
[0061] The specific usage is that job personnel can use the simulated training rocket to carry out individual training tasks, including self-inspection of component structures, disassembly and inspection testing of the overall structure of the rocket body, and simulated pyrotechnic circuit resistance testing, etc., to verify the mechanical interface matching of the various components of the rocket body (arrow 1, rocket body 2, tail section 3, interstage section, etc.), and improve the operational proficiency of job personnel; job personnel can also use the simulated training rocket to carry out full-process training tasks. The full-process training tasks include technical area training and launch area training. The technical area training includes the assembly and docking of the entire rocket, assembling the fairing (including the front cover, rear cover and other components) into a complete protection unit (star cover assembly), docking the star cover assembly with the rocket, and transferring the simulated training rocket onto the launch vehicle. The launch area training includes grounding the training simulation rocket, unfolding and leveling the launch vehicle carrying the training simulation rocket, distributing power to the training simulation rocket, reading parameters at the test system, erecting the training simulation rocket, installing grid rudders at the tail section 3, and dismantling the tail section 3.
[0062] In this embodiment, a simulated training rocket is set up to replace the real rocket during training. The job operators can use the simulated training rocket to complete a series of rocket-related tasks, thereby achieving training effects. At the same time, the simulated training rocket can meet the needs of high frequency and repeated use, replacing the virtual reality or software simulation calculation method used in related technologies for training, and realizing risk-free actual operation simulation of full-scene and full-process tasks, providing actual operation experience, and exercising operation details, which has a good training effect on job operators.
[0063] Obviously, the above embodiments are merely examples for clarity of explanation and are not intended to limit the implementation methods. Although the embodiments of the present invention have been described with reference to the accompanying drawings, those skilled in the art may make various modifications and variations without departing from the spirit and scope of the present invention, and such modifications and variations are all within the scope defined by the present invention.
Claims
1. A simulated training rocket, characterized in that: include; An arrow body comprises an arrow head (1), an arrow body (2) and a tail section (3), wherein the arrow head (1) and the tail section (3) are detachably connected to the arrow body (2), and the arrow body (2) has a simulated engine, wherein a first simulated igniter is provided in the simulated engine; The pyrotechnic system comprises a first simulated pyrotechnic part (11), wherein the first simulated pyrotechnic part (11) is arranged at the connection position between the arrow body (2) and the arrow head (1); A posture control simulation component (4) is arranged inside the arrow (1), and the posture control simulation component (4) has a simulation tank (42); A control system (5) is arranged inside the arrow (1) and is electrically connected to the first simulated igniter and the first simulated ignition unit (11); The measuring system (6) is arranged inside the arrow (1) and is electrically connected to the first simulated igniter and the first simulated ignition unit (11).
2. The simulation training rocket according to claim 1, characterized in that: The arrow (1) includes a fairing front cover (12), a transfer cabin (13), a propulsion control cabin (14) and a fairing rear cover (15); The attitude control simulation component (4), the control system (5) and the measurement system (6) are all arranged in the propulsion control cabin (14); The transfer cabin (13) is connected to the fairing front cover (12) and the propulsion control cabin (14), the fairing rear cover (15) is arranged on the periphery of the propulsion control cabin (14), and the end of the fairing rear cover (15) is connected to the transfer cabin (13); A first simulated separation component (7) is also provided in the arrow (1). The first simulated separation component (7) includes a simulated cylinder (71) and a second simulated pyrotechnic part (72). The second simulated pyrotechnic part (72) is provided at a connection position between the fairing front cover (12) and the transfer cabin (13). The simulated cylinder (71) is provided in the fairing front cover (12) and is arranged close to the transfer cabin (13).
3. The simulation training rocket according to claim 2, characterized in that: The simulated engine includes a first-stage engine (21), a second-stage engine (22) and a third-stage engine (23); The arrow body (2) further comprises a transition section (24), a first interstage section (211), and a second interstage section (221); The first end of the first stage engine (21) is detachably connected to the tail section (3), and the second end is detachably connected to the first interstage section (211); the first end of the second stage engine (22) is connected to the first interstage section (211), and the second end is detachably connected to the second interstage section (221); the first end of the third stage engine (23) is connected to the second interstage section (221), and the second end is detachably connected to the transition section (24); The side of the transition section (24) facing away from the three-stage engine (23) is connected to the fairing rear cover (15).
4. The simulation training rocket according to claim 3, characterized in that: The pyrotechnic system further comprises a third simulated pyrotechnic unit (231) and a fourth simulated pyrotechnic unit (212), wherein the third simulated pyrotechnic unit (231) is arranged at a connection position between the transition section (24) and the third-stage engine (23), and the fourth simulated pyrotechnic unit (212) is arranged at a connection position between the first-stage engine (21) and the first inter-stage section (211).
5. The simulation training rocket according to claim 4, characterized in that: Also included is a second simulated separation assembly (8), wherein the second simulated separation assembly (8) includes a fifth simulated pyrotechnic unit (81) and a simulated booster (82); The fifth simulated pyrotechnic unit (81) is arranged at the connection position between the second stage engine (22) and the second interstage section (221), and the simulated booster (82) is arranged at the second interstage section (221).
6. The simulation training rocket according to claim 5, characterized in that: The pyrotechnic system further comprises a self-destruction simulation pyrotechnic unit (25), wherein at least three of the self-destruction simulation pyrotechnic units (25) are respectively arranged inside the first-stage engine (21), the second-stage engine (22) and the third-stage engine (23).
7. The simulation training rocket according to claim 6, characterized in that: The second simulated pyrotechnics unit (72), the third simulated pyrotechnics unit (231), the fourth simulated pyrotechnics unit (212), the fifth simulated pyrotechnics unit (81) and the self-destruction simulated pyrotechnics unit (25) are electrically connected to the control system (5) respectively; The second simulated pyrotechnics unit (72), the third simulated pyrotechnics unit (231), the fourth simulated pyrotechnics unit (212), the fifth simulated pyrotechnics unit (81) and the self-destruction simulated pyrotechnics unit (25) are electrically connected to the measurement system (6) respectively.
8. The simulation training rocket according to claim 7, characterized in that: The attitude control simulation component (4) further comprises a shell (41), and at least two simulation tanks (42) are arranged in the shell (41).
9. The simulation training rocket according to claim 8, characterized in that: The attitude control simulation component (4) further comprises a simulation gas cylinder (43), a simulation attitude control engine (44) and a simulation orbit control engine (45), wherein the simulation gas cylinder (43), the simulation attitude control engine (44) and the simulation orbit control engine (45) are respectively arranged outside the housing (41).