Adjustable parameter ducted rocket

Abstract

The application discloses a ducted rocket with adjustable parameters, and relates to the field of ducted rockets, which comprises a rocket body, a vane control assembly, a duct power assembly, a flight control system, an adjustment assembly and a plurality of carbon fiber main beams; the vane control assembly is used for providing a control moment for stabilizing the flight attitude of the rocket; the vane control assembly is arranged below the rocket body; the duct power assembly is used for providing the required thrust for the flight of the rocket; the duct power assembly is arranged in a power cabin of the rocket body and is located above the vane control assembly; the flight control system is arranged in an avionics cabin of the rocket body, and the duct power assembly and the vane control assembly are controlled through the flight control system; and the adjustment assembly is used for verifying the response state of the ducted rocket under different control parameters. The application increases the adjustment assembly on the rocket body, thereby improving the convenience of adjusting the parameters of the ducted rocket, the safety of the adjustment process, the high accuracy of the adjustment result, and the direct application to the actual flight.

Description

Technical Field

[0001] This application relates to the field of ducted rocket technology, and more particularly to a ducted rocket with adjustable parameters. Background Technology

[0002] A ducted rocket is a type of rocket powered by an electrically driven duct, typically used for aerospace science education or rocket recovery algorithm testing. Ducted rocket parameter tuning refers to adjusting the control parameters in the ducted rocket's flight control algorithm to stabilize its flight attitude.

[0003] Currently, the mainstream parameter tuning method for ducted rockets involves using MATLAB (Matrix Laboratory) to perform dynamic modeling of the ducted rocket, and then continuously adjusting the parameters in the control module to achieve stable flight in mathematical simulations. This method requires precise mathematical modeling of the ducted rocket, especially for the sensor sampling accuracy, aerodynamic forces of the electric drive duct, rudder control response characteristics, and rudder control torque. However, because ducted rockets are low-cost model rockets, the materials used for various components are relatively inexpensive, leading to significant errors in the characteristic parameters of the components. Furthermore, the aerodynamic forces of the duct are quite complex, making it difficult to perform precise dynamic modeling of ducted rockets. Existing parameter tuning methods for ducted rockets have the following problems:

[0004] (1) One method for adjusting the parameters of a ducted rocket is as follows: When there is no accurate dynamic model of the ducted rocket, people can only load the simulated control parameters into the actual ducted rocket for testing, and then continuously adjust the dynamic model based on the actual response to obtain a relatively accurate dynamic model. This parameter adjustment process is very lengthy, with many adjustments to the dynamic model, long dynamic modeling time, and the risk of experimental accidents due to unreasonable control parameters during the test.

[0005] (2) Another method for adjusting the parameters of a ducted rocket is to fix the ducted rocket to a 2-DOF turntable and then continuously adjust the parameters to make the rocket tend to be attitude-stable on the turntable. This method requires the construction of a large turntable, which is costly and inconvenient to send to the customer along with the rocket. At the same time, because the ducted rocket is installed on the turntable, the friction and inertial forces of the turntable itself will be superimposed on the rocket, thus affecting the response characteristics of the flight control system. This can lead to attitude instability problems in actual flight due to control parameters that are stable during testing on the turntable. Summary of the Invention

[0006] The purpose of this application is to provide a ducted rocket with adjustable parameters. By adding a parameter adjustment component to the rocket body, the convenience of adjusting the parameters of the ducted rocket is improved. The parameter adjustment process is safe and the parameter adjustment results are highly accurate and can be directly applied to actual flight.

[0007] To achieve the above objectives, this application provides an adjustable ducted rocket, comprising: a rocket body, a rudder control assembly, a ducted propulsion assembly, a flight control system, a tuning assembly, and multiple carbon fiber main beams; wherein, the rudder control assembly: provides control torque for stabilizing the rocket's flight attitude; the rudder control assembly is located below the rocket body; the ducted propulsion assembly: provides the thrust required for rocket flight; the ducted propulsion assembly is located within the propulsion compartment of the rocket body and above the rudder control assembly; the flight control system is located within the avionics compartment of the rocket body, and the flight control system is connected to the ducted propulsion assembly and the rudder control assembly, controlling the ducted propulsion assembly and the rudder control assembly through the flight control system; tuning... Test Components: Used to verify the response status of the ducted rocket under different control parameters; the test components include at least: a universal oscillating assembly for realizing universal oscillating motion and a single-axis oscillating assembly for realizing single-axis oscillating motion; the universal oscillating assembly is located on the top of the rocket body and connected to the upper end of each carbon fiber main beam; the single-axis oscillating assembly is located below the flight control system, and is rotatably connected to the rocket body, with the rotatable connection located on the plane of the rocket body's center of mass; the single-axis oscillating assembly is also rotatably connected to the carbon fiber main beams, with the rotatable connection located on the plane of the rocket body's center of mass; multiple carbon fiber main beams are detachably connected to the rocket body.

[0008] As shown above, there are four carbon fiber main beams, which are evenly spaced in a circle around the vertical bearing of the rocket body. The four carbon fiber main beams are designated as the first carbon fiber main beam, the second carbon fiber main beam, the third carbon fiber main beam, and the fourth carbon fiber main beam. The first carbon fiber main beam is adjacent to the second carbon fiber main beam and the fourth carbon fiber main beam. The third carbon fiber main beam is adjacent to the second carbon fiber main beam and the fourth carbon fiber main beam.

[0009] As described above, the omnidirectional oscillation assembly includes: a joint bearing, a straight block, and an adjustment head cone for realizing omnidirectional oscillation motion; wherein, the upper end of the joint bearing is detachably connected to the middle part of the straight block; the lower end of the joint bearing is detachably connected to the upper end of the adjustment head cone; the lower end of the adjustment head cone is detachably connected to the upper end of each carbon fiber main beam; when performing omnidirectional oscillation adjustment, one end of the straight block is fixed to the first placement device, the other end of the straight block is fixed to the second placement device, and the rocket body is positioned between the first placement device and the second placement device, then the rocket body can perform omnidirectional oscillation motion around the fixed straight block.

[0010] As described above, one end of the single-character code is placed on the first placement device, and the first fixing object is used to press down on the one end of the single-character code, so that the one end of the single-character code is fixed on the first placement device; the other end of the single-character code is placed on the second placement device, and the second fixing object is used to press down on the other end of the single-character code, so that the other end of the single-character code is fixed on the second placement device.

[0011] As shown above, the upper end of the spherical bearing is connected to the middle of the flathead screw via a screw; the lower end of the spherical bearing is connected to the upper end of the adjustment head cone via a screw.

[0012] As shown above, the lower end of the adjustment head cone is connected to the upper end of each carbon fiber main beam by screws.

[0013] As described above, the single-axis oscillation assembly includes: a first adjustment bracket, a second adjustment bracket, and a carbon fiber rod; the first adjustment bracket has a first centroid hole in its middle; the second adjustment bracket has a second centroid hole in its middle; one end of the first adjustment bracket is detachably connected to the first carbon fiber main beam, and the other end of the first adjustment bracket is detachably connected to the fourth carbon fiber main beam; one end of the second adjustment bracket is detachably connected to the second carbon fiber main beam, and the other end of the second adjustment bracket is detachably connected to the third carbon fiber main beam; the carbon fiber rod passes through the first centroid hole, the centroid of the rocket body, and the second centroid hole in sequence; during single-axis oscillation adjustment, one end of the carbon fiber rod is fixed to the third placement device, and the other end of the carbon fiber rod is fixed to the fourth placement device, with the rocket body positioned between the third and fourth placement devices, so that the rocket body can perform single-axis oscillation motion around the fixed carbon fiber rod.

[0014] As described above, one end of the carbon fiber rod is placed on the third placement device, and the third fixing object is used to press down on one end of the carbon fiber rod, so that one end of the carbon fiber rod is fixed on the third placement device; the other end of the carbon fiber rod is placed on the fourth placement device, and the fourth fixing object is used to press down on the other end of the carbon fiber rod, so that the other end of the carbon fiber rod is fixed on the fourth placement device.

[0015] As shown above, one end of the first debugging bracket is connected to the first carbon fiber main beam by screws, and the other end of the first debugging bracket is connected to the fourth carbon fiber main beam by screws.

[0016] As shown above, one end of the second debugging bracket is connected to the second carbon fiber main beam by screws, and the other end of the second debugging bracket is connected to the third carbon fiber main beam by screws.

[0017] The beneficial effects achieved by this application are as follows:

[0018] (1) The adjustable ducted rocket of this application improves the convenience of adjusting the parameters of the ducted rocket by adding a parameter adjustment component to the rocket body. The parameter adjustment process is safe and will not cause test accidents due to unreasonable parameters (such as no need to worry about the rocket flying out of control). The parameter response characteristics of the parameter adjustment results obtained by using the adjustment component are consistent with the actual flight. Therefore, the parameter adjustment results can be directly applied to actual flight.

[0019] (2) The adjustable ducted rocket of this application has a universal adjustment component designed on the top of the ducted rocket. Therefore, the parameter adjustment can be quickly achieved by adjusting only three parts: the head cone, the joint bearing and the straight code, and the safety of the parameter adjustment test is improved.

[0020] (3) The adjustable parameter ducted rocket of this application has a single-axis oscillating component designed at the center of mass of the ducted rocket. The component consists of only two adjustment brackets (i.e., the first adjustment bracket and the second adjustment bracket) and a carbon fiber rod (i.e., the carbon fiber round rod). It is not only simple in structure, but also the parameter response after adjustment is consistent with the actual flight.

[0021] (4) The adjustment component of the adjustable ducted rocket of this application is detachably connected to the rocket body, which is convenient for installation and disassembly. When the adjustment component is not in use, it can be removed and the universal swing component on the top of the rocket body can be replaced with a fairing to restore the normal appearance of the ducted rocket.

[0022] (5) The adjustable ducted rocket of this application does not require mathematical modeling of the ducted rocket during the parameter adjustment process, which saves a lot of research and development time and avoids the situation where the rocket control parameters are wrong due to inaccurate modeling, which may cause the rocket flight test to go out of control.

[0023] (6) The adjustable ducted rocket of this application does not require an adjustment turntable during the adjustment process. Not only is the cost much lower than that of the adjustment turntable, but it also does not introduce the interference of friction and inertial force of the adjustment turntable, thus avoiding the situation where the rocket's response to control parameters is distorted due to the interference of friction and inertial force of the adjustment turntable.

[0024] (7) The adjustable parameter ducted rocket debugging component of this application has the advantages of simple structure, low cost, simple construction and convenient use. Attached Figure Description

[0025] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in this application. For those skilled in the art, other drawings can be obtained based on these drawings.

[0026] Figure 1 A schematic diagram of one embodiment of a ducted rocket with adjustable parameters;

[0027] Figure 2 An assembly diagram of the debugging components and four carbon fiber main beams;

[0028] Figure 3 A schematic diagram of gimbaling adjustment for a ducted rocket with adjustable parameters;

[0029] Figure 4 A schematic diagram of single-axis oscillation testing for a ducted rocket with adjustable parameters. Detailed Implementation

[0030] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0031] like Figure 1-4 As shown, this application provides an adjustable ducted rocket, including: a rocket body 1, a rudder control assembly 2, a ducted propulsion assembly, a flight control system, a debugging assembly 3, and multiple carbon fiber main beams 4. The rudder control assembly 2 is used to provide control torque for stabilizing the rocket's flight attitude; it is located below the rocket body 1. The ducted propulsion assembly is used to provide the thrust required for rocket flight; it is located within the propulsion compartment 11 of the rocket body 1 and above the rudder control assembly 2. The flight control system is located within the avionics compartment 12 of the rocket body 1, and is connected to the ducted propulsion assembly and the rudder control assembly 2, controlling them. The debugging assembly 3 is used to verify the response state of the ducted rocket under different control parameters; it includes at least: a gimbaled oscillating assembly 31 for achieving omnidirectional oscillation motion and a centroid-based single-axis oscillation assembly 32 for achieving single-axis oscillation motion. The omnidirectional oscillating assembly 31 is located at the top of the rocket body 1 and is connected to the upper end of each carbon fiber main beam 4. The center-of-gravity single-axis oscillating assembly 32 is located below the flight control system. The center-of-gravity single-axis oscillating assembly 32 is rotatably connected to the rocket body 1, and the rotatable connection point is located on the plane of the center of gravity of the rocket body 1. The center-of-gravity single-axis oscillating assembly 32 is also rotatably connected to the carbon fiber main beam 4, and the rotatable connection point is located on the plane of the center of gravity of the rocket body 1; multiple carbon fiber main beams 4 are detachably connected to the rocket body 1.

[0032] Specifically, the flight control system uniformly controls the rudder control assembly 2 and the ducted propulsion assembly, thereby enabling the ducted rocket to fly normally. The specific location of the flight control system is set according to the actual situation. In this application, it is preferred that the flight control system is located in the avionics compartment 12, which is located slightly above the rocket body 1 of the ducted rocket.

[0033] Specifically, the flight control system is encased in the avionics compartment 12 within the outer shell of the rocket body 1.

[0034] The ducted propulsion assembly is enclosed within the propulsion compartment 11 by the outer shell of the rocket body 1.

[0035] The avionics compartment shell and the power compartment shell are both part of the rocket body 1.

[0036] Furthermore, the specific number of carbon fiber main beams 4 is set according to the actual situation. In this application, it is preferred that there are four carbon fiber main beams 4, arranged in a circular pattern with the vertical bearing of the rocket body 1 as the center. Specifically, the four carbon fiber main beams 4 are designated as a first carbon fiber main beam 41, a second carbon fiber main beam 42, a third carbon fiber main beam 43, and a fourth carbon fiber main beam 44. The first carbon fiber main beam 41 is adjacent to both the second carbon fiber main beam 42 and the fourth carbon fiber main beam 44. The third carbon fiber main beam 43 is adjacent to both the second carbon fiber main beam 42 and the fourth carbon fiber main beam 44.

[0037] Furthermore, each carbon fiber main beam 4 is provided with multiple main beam mounting holes. The carbon fiber main beam 4 is connected to the rocket body 1, the universal oscillating assembly 31 and / or the center-of-gravity single-axis oscillating assembly 32 through the main beam mounting holes.

[0038] Specifically, the number of main beam mounting holes is determined based on the actual situation. The specific locations of the main beam mounting holes are also determined based on the actual situation.

[0039] Furthermore, such as Figure 2 and Figure 3 As shown, the omnidirectional oscillating assembly 31 includes: a joint bearing 311, a straight block 312, and an adjustment head cone 313 for realizing omnidirectional oscillation. The upper end of the joint bearing 311 is detachably connected to the middle of the straight block 312. The lower end of the joint bearing 311 is detachably connected to the upper end of the adjustment head cone 313. The lower end of the adjustment head cone 313 is detachably connected to the upper end of each carbon fiber main beam 4. During omnidirectional oscillation adjustment, one end of the straight block 312 is fixed to the first placement device 5, and the other end of the straight block 312 is fixed to the second placement device 6. With the rocket body 1 positioned between the first placement device 5 and the second placement device 6, the rocket body 1 can then perform omnidirectional oscillation around the fixed straight block 312.

[0040] Specifically, the ball joint bearing 311 internally uses a ball joint to connect the upper and lower joints, thus enabling the two joints to achieve omnidirectional oscillation. During omnidirectional oscillation adjustment, the adjustable ducted rocket only includes the omnidirectional oscillation assembly 31, omitting the center-of-gravity single-axis oscillation assembly 32, to avoid any impact from the center-of-gravity single-axis oscillation assembly 32 on the omnidirectional oscillation adjustment. The adjustable ducted rocket of this application features an omnidirectional adjustment assembly 31 at the top of the ducted rocket; therefore, parameter adjustment can be quickly achieved by adjusting only three parts: the nose cone 313, the ball joint bearing 311, and the straight-line code 312, thus improving the safety of the parameter adjustment test.

[0041] Furthermore, one end of the single-character code 312 is placed on the first placement device 5, and the first fixing object 51 is used to press down on one end of the single-character code 312, so that one end of the single-character code 312 is fixed on the first placement device 5; the other end of the single-character code 312 is placed on the second placement device 6, and the second fixing object 61 is used to press down on the other end of the single-character code 312, so that the other end of the single-character code 312 is fixed on the second placement device 6.

[0042] Specifically, the first placement device 5 and the second placement device 6 are tables, but not limited to tables; in this application, a table is preferred. The first fixing object 51 and the second fixing object 61 are both weights with a preset weight. The preset weight presses the straight code 312 onto the first placement device 5 and the second placement device 6. However, the pressing of the straight code 312 onto the first placement device 5 and the second placement device 6 is not limited to the first fixing object 51 and the second fixing object 61; the straight code 312 can also be fixed to the first placement device 5 and the second placement device 6 by a detachable connection method such as bolts. In this application, the straight code 312 is preferably pressed onto the first placement device 5 and the second placement device 6 by the first fixing object 51 and the second fixing object 61.

[0043] This installation method allows the ducted rocket to swing freely between two tables, thus verifying the response to different control parameters. If the control parameters are reasonable, the rocket body 1 will maintain a stable attitude, and the three-axis angles will not oscillate or diverge. If the parameters are unstable, the rocket body 1 will exhibit attitude oscillations and shaking. In this mode, the rocket can be debugged, and control parameters can be tested freely. Since the code 312 is fixed, there is no need to worry about the rocket body 1 going out of control and flying off, causing a test accident or rocket damage.

[0044] Furthermore, the upper end of the spherical bearing 311 is connected to the middle of the flathead screw 312 by a screw; the lower end of the spherical bearing 311 is connected to the upper end of the adjustment head cone 313 by a screw, but not limited to screws, but preferably screws in this application.

[0045] Furthermore, the lower end of the adjustment head cone 313 is connected to the upper end of each carbon fiber main beam 4 by screws, but not limited to screws; screws are preferred in this application.

[0046] Furthermore, such as Figure 2 and Figure 4 As shown, the single-axis oscillating assembly 32 includes: a first adjustment bracket 321, a second adjustment bracket 322, and a carbon fiber rod 323. The first adjustment bracket 321 has a first centroid hole in its center; the second adjustment bracket 322 has a second centroid hole in its center. One end of the first adjustment bracket 321 is detachably connected to the first carbon fiber main beam 41, and the other end is detachably connected to the fourth carbon fiber main beam 44. One end of the second adjustment bracket 322 is detachably connected to the second carbon fiber main beam 42, and the other end is detachably connected to the third carbon fiber main beam 43. The carbon fiber rod 323 passes sequentially through the first centroid hole, the centroid of the rocket body 1, and the second centroid hole. When performing single-axis swing adjustment, one end of the carbon fiber rod 323 is fixed to the third placement device 7, and the other end of the carbon fiber rod 323 is fixed to the fourth placement device 8. The rocket body 1 is positioned between the third placement device 7 and the fourth placement device 8. Then the rocket body 1 can swing around the fixed carbon fiber rod 323 in a single axis.

[0047] Specifically, when performing single-axis oscillation debugging, the adjustable ducted rocket is equipped with only the center-of-mass single-axis oscillation component 32, and not the universal oscillation component 31, so as to avoid the universal oscillation component 31 affecting the single-axis oscillation debugging.

[0048] Since rocket flight attitude control is essentially an angular motion control around the center of mass, the carbon fiber rod 323 must pass through the center of mass of the rocket body 1 in order to make the response characteristics of the control parameters consistent with the actual rocket flight.

[0049] Furthermore, one end of the carbon fiber rod 323 is placed on the third placement device 7, and the third fixing object 71 is used to press down on one end of the carbon fiber rod 323, so that one end of the carbon fiber rod 323 is fixed on the third placement device 7; the other end of the carbon fiber rod 323 is placed on the fourth placement device 8, and the fourth fixing object 81 is used to press down on the other end of the carbon fiber rod 323, so that the other end of the carbon fiber rod 323 is fixed on the fourth placement device 8.

[0050] Specifically, the third placement device 7 and the fourth placement device 8 are tables, but not limited to tables; in this application, tables are preferred. The third fixing object 71 and the fourth fixing object 81 are both weights with a preset weight. The carbon fiber rod 323 is pressed onto the third placement device 7 and the fourth placement device 8 by the preset weight. However, the carbon fiber rod 323 is not limited to being pressed onto the third placement device 7 and the fourth placement device 8 by the third fixing object 71 and the fourth fixing object 81; it can also be fixed onto the third placement device 7 and the fourth placement device 8 by a detachable connection method such as bolts. In this application, the carbon fiber rod 323 is preferably pressed onto the third placement device 7 and the fourth placement device 8 by the third placement device 7 and the fourth placement device 8.

[0051] The specific structures of the first placement device 5, the second placement device 6, the third placement device 7, and the fourth placement device 8 may be the same or different; in this application, they are preferably the same.

[0052] The specific structures of the first fixing member 51, the second fixing member 61, the third fixing member 71, and the fourth fixing member 81 may be the same or different; in this application, they are preferably the same.

[0053] Furthermore, one end of the first debugging bracket 321 is connected to the first carbon fiber main beam 41 by screws, and the other end of the first debugging bracket 321 is connected to the fourth carbon fiber main beam 44 by screws, but not limited to screws, screws are preferred in this application.

[0054] Furthermore, one end of the second debugging bracket 322 is connected to the second carbon fiber main beam 42 by screws, and the other end of the second debugging bracket 322 is connected to the third carbon fiber main beam 43 by screws, but not limited to screws, screws are preferred in this application.

[0055] Specifically, the parameter adjustment principle of an adjustable ducted rocket is as follows: Due to the good structural symmetry of the ducted rocket, once a set of parameters that can stabilize the ducted rocket's attitude without wobbling is calibrated using the center-of-mass single-axis gyroscope assembly 32, these parameters can be copied to the other side, which is horizontally perpendicular to the carbon fiber rod 323. This allows the ducted rocket to maintain stable pitch and yaw angles in the horizontal plane. Then, the universal gyroscope assembly 31 is used to adjust the rocket to stabilize the roll angle of the longitudinal axis, ultimately achieving stable three-axis attitude of the rocket.

[0056] When not in use, the debugging component 3 can be removed, and the universal gyratory assembly 31 on top of the rocket body 1 can be replaced with a fairing, thereby restoring the normal appearance of the ducted rocket.

[0057] The beneficial effects achieved by this application are as follows:

[0058] (1) The adjustable ducted rocket of this application improves the convenience of adjusting the parameters of the ducted rocket by adding a parameter adjustment component to the rocket body. The parameter adjustment process is safe and will not cause test accidents due to unreasonable parameters (such as no need to worry about the rocket flying out of control). The parameter response characteristics of the parameter adjustment results obtained by using the adjustment component are consistent with the actual flight. Therefore, the parameter adjustment results can be directly applied to actual flight.

[0059] (2) The adjustable ducted rocket of this application has a universal adjustment component designed on the top of the ducted rocket. Therefore, the parameter adjustment can be quickly achieved by adjusting only three parts: the head cone, the joint bearing and the straight code, and the safety of the parameter adjustment test is improved.

[0060] (3) The adjustable parameter ducted rocket of this application has a single-axis oscillating component designed at the center of mass of the ducted rocket. The component consists of only two adjustment brackets (i.e., the first adjustment bracket and the second adjustment bracket) and a carbon fiber rod (i.e., the carbon fiber round rod). It is not only simple in structure, but also the parameter response after adjustment is consistent with the actual flight.

[0061] (4) The adjustment component of the adjustable ducted rocket of this application is detachably connected to the rocket body, which is convenient for installation and disassembly. When the adjustment component is not in use, it can be removed and the universal swing component on the top of the rocket body can be replaced with a fairing to restore the normal appearance of the ducted rocket.

[0062] (5) The adjustable ducted rocket of this application does not require mathematical modeling of the ducted rocket during the parameter adjustment process, which saves a lot of research and development time and avoids the situation where the rocket control parameters are wrong due to inaccurate modeling, which may cause the rocket flight test to go out of control.

[0063] (6) The adjustable ducted rocket of this application does not require an adjustment turntable during the adjustment process. Not only is the cost much lower than that of the adjustment turntable, but it also does not introduce the interference of friction and inertial force of the adjustment turntable, thus avoiding the situation where the rocket's response to control parameters is distorted due to the interference of friction and inertial force of the adjustment turntable.

[0064] (7) The adjustable parameter ducted rocket debugging component of this application has the advantages of simple structure, low cost, simple construction and easy use.

[0065] Although preferred embodiments of this application have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the scope of protection of this application is intended to be interpreted as including the preferred embodiments as well as all changes and modifications falling within the scope of this application. Obviously, those skilled in the art can make various alterations and variations to this application without departing from the spirit and scope of this application. Thus, if these modifications and variations of this application fall within the scope of protection of this application and its equivalents, this application also intends to include these modifications and variations.

Claims

1. A ducted rocket with adjustable parameters, characterized in that, include: Rocket body, rudder control assembly, ducted propulsion assembly, flight control system, debugging assembly, and multiple carbon fiber main beams; Among them, the rudder control assembly is used to provide control torque for stabilizing the rocket's flight attitude; the rudder control assembly is located below the rocket body. Ducted propulsion assembly: Used to provide the thrust required for rocket flight; the ducted propulsion assembly is located in the power compartment of the rocket body and is situated above the rudder control assembly; The flight control system is located in the avionics compartment of the rocket body. The flight control system is connected to the ducted propulsion assembly and the control plate assembly, and controls the ducted propulsion assembly and the control plate assembly through the flight control system. Debugging components: used to verify the response status of the ducted rocket under different control parameters; the debugging components include at least: a universal oscillating component for realizing universal oscillating motion and a center-of-mass single-axis oscillating component for realizing single-axis oscillating motion; The omnidirectional oscillating assembly is located at the top of the rocket body and is connected to the upper end of each carbon fiber main beam; The center-of-gravity single-axis oscillation assembly is located below the flight control system. The center-of-gravity single-axis oscillation assembly is rotatably connected to the rocket body, and the rotatable connection position is located on the plane where the center of gravity of the rocket body is located. The center-of-mass single-axis oscillating assembly is also rotatably connected to the carbon fiber main beam, and the rotatable connection is located on the plane where the center of mass of the rocket body is located; Multiple carbon fiber main beams are detachably connected to the rocket body.

2. The adjustable-parameter ducted rocket according to claim 1, characterized in that, There are four carbon fiber main beams, which are evenly spaced in a circle around the vertical bearing of the rocket body. Among them, the four carbon fiber main beams are the first carbon fiber main beam, the second carbon fiber main beam, the third carbon fiber main beam, and the fourth carbon fiber main beam; The first carbon fiber main beam is adjacent to the second carbon fiber main beam and the fourth carbon fiber main beam, respectively; The third carbon fiber main beam is adjacent to the second and fourth carbon fiber main beams, respectively.

3. The adjustable-parameter ducted rocket according to claim 2, characterized in that, The omnidirectional oscillating assembly includes: a joint bearing for realizing omnidirectional oscillating motion, a straight block, and an adjustment head cone; The upper end of the spherical bearing is detachably connected to the middle part of the straight code. The lower end of the spherical bearing is detachably connected to the upper end of the adjustment head cone; The lower end of the adjustment head cone is detachably connected to the upper end of each carbon fiber main beam; When performing omnidirectional swing adjustment, fix one end of the straight code to the first placement device and the other end of the straight code to the second placement device, and place the rocket body between the first placement device and the second placement device. Then the rocket body can swing around the fixed straight code.

4. The adjustable-parameter ducted rocket according to claim 3, characterized in that, Place one end of the single-character code on the first placement device and press it down with the first fixing object, so that one end of the single-character code is fixed on the first placement device; place the other end of the single-character code on the second placement device and press it down with the second fixing object, so that the other end of the single-character code is fixed on the second placement device.

5. The adjustable-parameter ducted rocket according to claim 3, characterized in that, The upper end of the spherical bearing is connected to the middle of the flathead screw via a screw; the lower end of the spherical bearing is connected to the upper end of the adjustment head cone via a screw.

6. The adjustable-parameter ducted rocket according to claim 3, characterized in that, The lower end of the adjustment head cone is connected to the upper end of each carbon fiber main beam by screws.

7. The adjustable-parameter ducted rocket according to claim 2, characterized in that, The single-axis oscillating assembly includes: a first adjustment bracket, a second adjustment bracket, and a carbon fiber round rod; the first adjustment bracket has a first center of mass hole in its middle; the second adjustment bracket has a second center of mass hole in its middle. One end of the first debugging bracket is detachably connected to the first carbon fiber main beam, and the other end of the first debugging bracket is detachably connected to the fourth carbon fiber main beam. One end of the second debugging bracket is detachably connected to the second carbon fiber main beam, and the other end of the second debugging bracket is detachably connected to the third carbon fiber main beam; The carbon fiber rod passes sequentially through the first centroid hole, the center of mass of the rocket body, and the second centroid hole. When performing single-axis swing adjustment, fix one end of the carbon fiber rod to the third placement device and the other end of the carbon fiber rod to the fourth placement device, and place the rocket body between the third and fourth placement devices. Then the rocket body can swing around the fixed carbon fiber rod in a single-axis motion.

8. The adjustable-parameter ducted rocket according to claim 7, characterized in that, Place one end of the carbon fiber rod on the third placement device and press it down with the third fixing object to fix one end of the carbon fiber rod on the third placement device; place the other end of the carbon fiber rod on the fourth placement device and press it down with the fourth fixing object to fix the other end of the carbon fiber rod on the fourth placement device.

9. The adjustable-parameter ducted rocket according to claim 7, characterized in that, One end of the first debugging bracket is connected to the first carbon fiber main beam by screws, and the other end of the first debugging bracket is connected to the fourth carbon fiber main beam by screws.

10. The adjustable-parameter ducted rocket according to claim 7, characterized in that, One end of the second debugging bracket is connected to the second carbon fiber main beam by screws, and the other end of the second debugging bracket is connected to the third carbon fiber main beam by screws.

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