Ducted rocket with adjustable parameters

Abstract

The invention discloses a parameter-adjustable ducted rocket, and relates to the field of ducted rockets, and the parameter-adjustable ducted rocket comprises a rocket body, a rudder sheet control assembly, a ducted power assembly, a flight control system, a debugging assembly and a plurality of carbon fiber main beams; the rudder sheet control assembly is used for providing control torque for stabilizing the flight attitude of the rocket; the rudder sheet control assembly is arranged below the rocket body; the duct power assembly is used for providing thrust required by the flight of the rocket; the duct power assembly is arranged in a power cabin of the rocket body and located above the rudder piece control assembly. The flight control system is arranged in an avionics cabin of the rocket body, and the duct power assembly and the rudder sheet control assembly are controlled through the flight control system; and the debugging assembly is used for verifying response states of the ducted rocket under different control parameters. According to the method, the parameter adjusting assembly is additionally arranged on the rocket body, so that the parameter adjusting convenience of the ducted rocket is improved, the parameter adjusting process is safe, the parameter adjusting result is high in accuracy, and the method can be directly applied to actual flight.

Description

Technical Field

[0001] The present application relates to the technical field of ducted rockets, and in particular to a ducted rocket with adjustable parameters. Background Art

[0002] A ducted rocket is a rocket powered by an electric duct, and is generally used for aerospace science education or rocket recovery algorithm testing. Ducted rocket parameter adjustment refers to debugging the control parameters in the ducted rocket flight control algorithm to stabilize the flight attitude of the ducted rocket.

[0003] At present, the mainstream parameter adjustment method for ducted rockets is to use matlab (Matrix Laboratory) to perform dynamic modeling of ducted rockets, and then continuously debug the parameters in the control module to enable the ducted rockets to achieve stable flight in mathematical simulation. This parameter adjustment method requires accurate mathematical modeling of ducted rockets, especially accurate modeling of the sensor sampling accuracy of ducted rockets, the aerodynamic force of the electric drive duct, the control response characteristics of the rudder blades, and the control torque of the rudder blades. However, since ducted rockets are a kind of low-cost model rockets, the materials used for various parts are relatively cheap, resulting in relatively large errors in the characteristic parameters of the parts, and since the aerodynamic force of the duct is relatively complex, it is difficult to perform accurate dynamic modeling of ducted rockets. The existing parameter adjustment methods for ducted rockets have the following problems:

[0004] (1) One way to adjust the parameters of a ducted rocket is: when there is no accurate ducted rocket dynamics model, people can only load the simulated control parameters into the actual ducted rocket for testing, and then continuously adjust the dynamics model according to the actual response to obtain a relatively accurate dynamics model. This parameter adjustment process is very long, with many dynamic model adjustments, long dynamics modeling time, and it is easy to cause test accidents due to unreasonable control parameters during the test.

[0005] (2) Another parameter adjustment method for ducted rockets is to fix the ducted rocket to a 2-DOF turntable, and then continuously adjust the parameters to make the rocket tend to be stable on the turntable. This parameter adjustment method requires the construction of an additional large turntable, which is costly and inconvenient to send to customers together with the rocket. At the same time, since the ducted rocket is installed on the turntable, the friction and inertia of the turntable itself will be superimposed on the rocket, thereby affecting the response characteristics of the flight control, resulting in the control parameters tested stable on the turntable causing attitude instability problems in actual flight. Summary of the invention

[0006] The purpose of the present 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] In order to achieve the above-mentioned purpose, the present application provides a ducted rocket with adjustable parameters, including: a rocket body, a rudder control assembly, a ducted power assembly, a flight control system, a debugging assembly and a plurality of carbon fiber main beams; wherein, the rudder control assembly: is used to provide a control torque for stabilizing the rocket's flight attitude; the rudder control assembly is arranged below the rocket body; the ducted power assembly: is used to provide the thrust required for the rocket's flight; the ducted power assembly is arranged in the power compartment of the rocket body and is located above the rudder control assembly; the flight control system is arranged in the avionics compartment of the rocket body, the flight control system is connected to the ducted power assembly and the rudder control assembly, and the ducted power assembly and the rudder control assembly are controlled by the flight control system; the debugging assembly Test assembly: used to verify the response state of the ducted rocket under different control parameters; the debugging assembly at least includes: a universal swing assembly for realizing universal swing motion and a center of mass single-axis swing assembly for realizing single-axis swing motion; the universal swing assembly is arranged at the top of the rocket body and is connected to the upper end of each carbon fiber main beam; the center of mass single-axis swing assembly is arranged below the flight control system, the center of mass single-axis swing assembly is rotationally connected to the rocket body, and the rotational connection position is located on the plane where the center of mass of the rocket body is located; the center of mass single-axis swing assembly is also rotationally connected to the carbon fiber main beam, and the rotational connection position 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.

[0008] As above, there are four carbon fiber main beams, and the four carbon fiber main beams are arranged evenly spaced in a circle with the vertical bearing of the rocket body as the center; the four carbon fiber main beams are respectively 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 respectively adjacent to the second carbon fiber main beam and the fourth carbon fiber main beam; the third carbon fiber main beam is respectively adjacent to the second carbon fiber main beam and the fourth carbon fiber main beam.

[0009] As above, the universal swing assembly includes: a joint bearing, a straight code and a debugging head cone for realizing universal swing motion; wherein, the upper end of the joint bearing is detachably connected to the middle part of the straight code; the lower end of the joint bearing is detachably connected to the upper end of the debugging head cone; the lower end of the debugging head cone is detachably connected to the upper end of each carbon fiber main beam; when performing universal swing debugging, one end of the straight code is fixed on the first placing device, and the other end of the straight code is fixed on the second placing device, and the rocket body is located between the first placing device and the second placing device, then the rocket body can perform universal swing motion around the fixed straight code.

[0010] As above, one end of the straight code is placed on the first placing device, and the first fixing object is used to press the one end of the straight code, so that the one end of the straight code is fixed on the first placing device; the other end of the straight code is placed on the second placing device, and the second fixing object is used to press the other end of the straight code, so that the other end of the straight code is fixed on the second placing device.

[0011] As above, the upper end of the joint bearing is connected to the middle part of the straight code through a screw; the lower end of the joint bearing is connected to the upper end of the debugging head cone through a screw.

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

[0013] As above, the center of mass single-axis swing assembly includes: a first debugging bracket, a second debugging bracket and a carbon fiber round rod; a first center of mass hole is set in the middle of the first debugging bracket; a second center of mass hole is set in the middle of the second debugging bracket; wherein, 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 round rod passes through the first center of mass hole, the center of mass of the rocket body and the second center of mass hole in sequence; when performing single-axis swing debugging, one end of the carbon fiber round rod is fixed on the third placing device, and the other end of the carbon fiber round rod is fixed on the fourth placing device, and the rocket body is located between the third placing device and the fourth placing device, then the rocket body can perform single-axis swing motion around the fixed carbon fiber round rod.

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

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

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

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

[0018] (1) The adjustable parameter ducted rocket of the present 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 there will be no test accidents caused by unreasonable parameters during the parameter adjustment process (such as there is no need to worry about the rocket flying out of control). The parameter response characteristics of the parameter adjustment results obtained using the debugging component are consistent with the actual flight. Therefore, the parameter adjustment results can be directly applied to actual flights.

[0019] (2) The adjustable parameter ducted rocket of the present application is designed with a universal debugging assembly on the top of the ducted rocket. Therefore, quick parameter adjustment can be achieved by only debugging the three parts of the nose cone, the spherical bearing and the straight code, and the safety of the parameter adjustment test is improved.

[0020] (3) The adjustable parameter ducted rocket of the present application is designed with a single-axis swing assembly at the center of mass of the ducted rocket. The assembly consists of only two debugging brackets (i.e., the first debugging bracket and the second debugging bracket) and a carbon fiber rod (i.e., carbon fiber round rod). Not only is the structure simple, but the parameter response obtained by debugging is consistent with the actual flight.

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

[0022] (5) The adjustable ducted rocket of the present 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 parameter errors caused by inaccurate modeling lead to the loss of control of the rocket flight test.

[0023] (6) The adjustable ducted rocket of the present application does not need to be equipped with a parameter adjustment turntable during the parameter adjustment process. Not only is the cost much lower than that of the parameter adjustment turntable, but it also does not introduce interference from the friction and inertia of the parameter adjustment turntable, thus avoiding the distortion of the rocket's response to the control parameters due to interference from the friction and inertia of the parameter adjustment turntable.

[0024] (7) The debugging assembly of the adjustable ducted rocket of the present application has the advantages of simple structure, low cost, simple construction and easy use. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present application. For ordinary technicians in this field, other drawings can also be obtained based on these drawings.

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

[0027] Figure 2 This is a schematic diagram of the assembly of the commissioning components and four carbon fiber main beams;

[0028] Figure 3 Schematic diagram of universal swing adjustment for a ducted rocket with adjustable parameters;

[0029] Figure 4 Schematic diagram of single-axis swing debugging of a ducted rocket with adjustable parameters. DETAILED DESCRIPTION

[0030] The following is a clear and complete description of the technical solutions in the embodiments of the present invention in conjunction with the 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 creative work are within the scope of protection of the present invention.

[0031] like Figure 1-4 As shown, the present application provides a ducted rocket with adjustable parameters, including: a rocket body 1, a rudder control assembly 2, a ducted power assembly, a flight control system, a debugging assembly 3 and a plurality of carbon fiber main beams 4. Among them, the rudder control assembly 2: is used to provide a control torque for stabilizing the rocket's flight attitude; the rudder control assembly 2 is arranged below the rocket body 1. The ducted power assembly: is used to provide the thrust required for the rocket's flight; the ducted power assembly is arranged in the power compartment 11 of the rocket body 1, and is located above the rudder control assembly 2. The flight control system is arranged in the avionics compartment 12 of the rocket body 1, and the flight control system is connected to the ducted power assembly and the rudder control assembly 2, and the ducted power assembly and the rudder control assembly 2 are controlled by the flight control system. The debugging assembly 3: is used to verify the response state of the ducted rocket under different control parameters; the debugging assembly 3 at least includes: a universal swing assembly 31 for realizing universal swing motion and a center of mass single-axis swing assembly 32 for realizing single-axis swing motion. The universal swing assembly 31 is arranged at the top of the rocket body 1 and connected to the upper end of each carbon fiber main beam 4. The center of mass single-axis swing assembly 32 is arranged below the flight control system. The center of mass single-axis swing assembly 32 is rotationally connected to the rocket body 1, and the rotationally connected position is located on the plane where the center of mass of the rocket body 1 is located. The center of mass single-axis swing assembly 32 is also rotationally connected to the carbon fiber main beam 4, and the rotationally connected position is located on the plane where the center of mass of the rocket body 1 is located; 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 power assembly, thereby achieving normal flight of the ducted rocket. The specific setting position of the flight control system is set according to actual conditions. The present application preferably has the flight control system located in the avionics cabin 12 in the upper middle of the rocket body 1 of the ducted rocket.

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

[0034] The ducted power assembly is wrapped in the power compartment 11 by the power compartment shell of the rocket body 1.

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

[0036] Furthermore, the specific number of carbon fiber main beams 4 is set according to actual conditions. The present application preferably has four carbon fiber main beams 4, and the four carbon fiber main beams 4 are arranged evenly spaced around the vertical bearing of the rocket body 1. Among them, the four carbon fiber main beams 4 are respectively the first carbon fiber main beam 41, the second carbon fiber main beam 42, the third carbon fiber main beam 43 and the fourth carbon fiber main beam 44. The first carbon fiber main beam 41 is adjacent to the second carbon fiber main beam 42 and the fourth carbon fiber main beam 44 respectively. The third carbon fiber main beam 43 is adjacent to the second carbon fiber main beam 42 and the fourth carbon fiber main beam 44 respectively.

[0037] Furthermore, a plurality of main beam mounting holes are provided on each carbon fiber main beam 4. The carbon fiber main beam 4 is connected to the rocket body 1, the universal swing assembly 31 and / or the center of mass single-axis swing assembly 32 through the main beam mounting holes.

[0038] Specifically, the specific number of the main beam mounting holes is set according to the actual situation. The specific setting positions of the main beam mounting holes are set according to the actual situation.

[0039] Further, such as Figure 2 and Figure 3 As shown, the universal swing assembly 31 includes: a joint bearing 311, a straight code 312 and a debugging head cone 313 for realizing universal swing motion. Among them, the upper end of the joint bearing 311 is detachably connected to the middle part of the straight code 312. The lower end of the joint bearing 311 is detachably connected to the upper end of the debugging head cone 313. The lower end of the debugging head cone 313 is detachably connected to the upper end of each carbon fiber main beam 4. When performing universal swing debugging, one end of the straight code 312 is fixed to the first placement device 5, and the other end of the straight code 312 is fixed to the second placement device 6, and the rocket body 1 is located between the first placement device 5 and the second placement device 6, then the rocket body 1 can perform universal swing motion around the fixed straight code 312.

[0040] Specifically, a ball head is used inside the joint bearing 311 to connect the upper and lower joints, so the two joints can achieve universal swing motion. When performing universal swing debugging, the adjustable ducted rocket only has a universal swing assembly 31, and does not have a center of mass single-axis swing assembly 32, so as to avoid the influence of the center of mass single-axis swing assembly 32 on the universal swing debugging. The adjustable ducted rocket of the present application is designed with a universal debugging assembly 31 at the top of the ducted rocket. Therefore, quick parameter adjustment can be achieved by only debugging the three parts of the head cone 313, the joint bearing 311 and the straight code 312, and the safety of the parameter adjustment test is improved.

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

[0042] Specifically, the first placement device 5 and the second placement device 6 are tables, but are not limited to tables. The present application preferably uses tables. The first fixture 51 and the second fixture 61 are both weights with preset weights. The preset weights are used to press the straight code 312 onto the first placement device 5 and the second placement device 6. However, the first fixture 51 and the second fixture 61 are not limited to pressing the straight code 312 onto the first placement device 5 and the second placement device 6. The straight code 312 can also be fixed to the first placement device 5 and the second placement device 6 by a detachable connection such as a bolt connection. The present application preferably uses the first fixture 51 and the second fixture 61 to press the straight code 312 onto the first placement device 5 and the second placement device 6.

[0043] With this installation method, the ducted rocket can swing freely between the two tables to verify the response status of different control parameters. If the control parameters are reasonable, the attitude of the rocket body 1 will remain stable, and the three-axis angles will not oscillate or diverge. If the parameters are unstable, the attitude of the rocket body 1 will oscillate and shake. When debugging the rocket in this mode, the control parameters can be tested at will. Since the straight code 312 is in a fixed state, there is no need to worry that the rocket body 1 will be thrown out of control or fly up, causing a test accident or rocket damage.

[0044] Furthermore, the upper end of the joint bearing 311 is connected to the middle of the straight code 312 through a screw; the lower end of the joint bearing 311 is connected to the upper end of the debugging head cone 313 through a screw, but is not limited to screws, and screws are preferred in this application.

[0045] Furthermore, the lower end of the debugging head cone 313 is connected to the upper end of each carbon fiber main beam 4 through screws, but is not limited to screws. Screws are preferred in the present application.

[0046] Further, such as Figure 2 and Figure 4 As shown, the mass center single-axis swing assembly 32 includes: a first debugging bracket 321, a second debugging bracket 322 and a carbon fiber round rod 323; a first mass center hole is set in the middle of the first debugging bracket 321; a second mass center hole is set in the middle of the second debugging bracket 322. Among them, one end of the first debugging bracket 321 is detachably connected to the first carbon fiber main beam 41, and the other end of the first debugging bracket 321 is detachably connected to the fourth carbon fiber main beam 44. One end of the second debugging bracket 322 is detachably connected to the second carbon fiber main beam 42, and the other end of the second debugging bracket 322 is detachably connected to the third carbon fiber main beam 43. The carbon fiber round rod 323 passes through the first mass center hole, the mass center of the rocket body 1 and the second mass center hole in sequence. When performing single-axis swing debugging, one end of the carbon fiber round rod 323 is fixed on the third placing device 7, and the other end of the carbon fiber round rod 323 is fixed on the fourth placing device 8, and the rocket body 1 is located between the third placing device 7 and the fourth placing device 8, then the rocket body 1 can perform single-axis swing motion around the fixed carbon fiber round rod 323.

[0047] Specifically, when performing single-axis swing debugging, the ducted rocket with adjustable parameters only has a center of mass single-axis swing component 32, but no universal swing component 31, so as to avoid the influence of the universal swing component 31 on the single-axis swing debugging.

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

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

[0050] Specifically, the third placement device 7 and the fourth placement device 8 are tables, but are not limited to tables. The present application preferably uses tables. The third fixture 71 and the fourth fixture 81 are both weights with preset weights, and the carbon fiber round rod 323 is pressed onto the third placement device 7 and the fourth placement device 8 by the preset weights, but are not limited to pressing the carbon fiber round rod 323 onto the third placement device 7 and the fourth placement device 8 by the third fixture 71 and the fourth fixture 81. The carbon fiber round rod 323 can also be fixed to the third placement device 7 and the fourth placement device 8 by a detachable connection such as a bolt connection. The present application preferably uses the third placement device 7 and the fourth placement device 8 to press the carbon fiber round rod 323 onto the third placement device 7 and the fourth placement device 8.

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

[0052] The specific structure of the first fixture 51 , the specific structure of the second fixture 61 , the specific structure of the third fixture 71 and the specific structure of the fourth fixture 81 may be the same or different, and in the present 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 is 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 is not limited to screws. Screws are preferred in this application.

[0055] Specifically, the working principle of the adjustable parameter of the ducted rocket is as follows: due to the good structural symmetry of the ducted rocket, when the ducted rocket uses the center of mass single-axis swing component 32 to debug a set of parameters that can make the ducted rocket attitude stable and not shaken, this set of parameters can be copied to the other side that is horizontally perpendicular to the carbon fiber round rod 323, so that the pitch and yaw angles of the ducted rocket in the horizontal plane can be kept stable. Then, the universal swing component 31 is used to debug the rocket to achieve the stability of the rolling angle of the longitudinal axis, and finally the three-axis attitude of the rocket can be kept stable.

[0056] When the debugging assembly 3 is not in use, it can be removed and then the universal swing assembly 31 on the top of the rocket body 1 can be replaced with a fairing to restore the normal appearance of the ducted rocket.

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

[0058] (1) The adjustable parameter ducted rocket of the present 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 there will be no test accidents caused by unreasonable parameters during the parameter adjustment process (such as there is no need to worry about the rocket flying out of control). The parameter response characteristics of the parameter adjustment results obtained using the debugging component are consistent with the actual flight. Therefore, the parameter adjustment results can be directly applied to actual flights.

[0059] (2) The adjustable parameter ducted rocket of the present application is designed with a universal debugging assembly on the top of the ducted rocket. Therefore, quick parameter adjustment can be achieved by only debugging the three parts of the nose cone, the spherical bearing and the straight code, and the safety of the parameter adjustment test is improved.

[0060] (3) The adjustable parameter ducted rocket of the present application is designed with a single-axis swing assembly at the center of mass of the ducted rocket. The assembly consists of only two debugging brackets (i.e., the first debugging bracket and the second debugging bracket) and a carbon fiber rod (i.e., carbon fiber round rod). Not only is the structure simple, but the parameter response obtained by debugging is consistent with the actual flight.

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

[0062] (5) The adjustable ducted rocket of the present 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 parameter errors caused by inaccurate modeling lead to the loss of control of the rocket flight test.

[0063] (6) The adjustable ducted rocket of the present application does not need to be equipped with a parameter adjustment turntable during the parameter adjustment process. Not only is the cost much lower than that of the parameter adjustment turntable, but it also does not introduce interference from the friction and inertia of the parameter adjustment turntable, thus avoiding the distortion of the rocket's response to the control parameters due to interference from the friction and inertia of the parameter adjustment turntable.

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

[0065] Although the preferred embodiments of the present application have been described, those skilled in the art may make additional changes and modifications to these embodiments once they are aware of the basic creative concepts. Therefore, the scope of protection of the present application is intended to be interpreted as including the preferred embodiments and all changes and modifications that fall within the scope of the present application. Obviously, those skilled in the art may make various changes and modifications to the present application without departing from the spirit and scope of the present application. Thus, if these modifications and variations of the present application fall within the scope of the protection scope of the present application and its equivalent technology, the present application is also intended to include these modifications and variations.

Claims

1. A ducted rocket with adjustable parameters, characterized in that: include: Rocket body, rudder control assembly, ducted power assembly, flight control system, debugging assembly and multiple carbon fiber main beams; Among them, the rudder blade control component is used to provide a control torque for stabilizing the rocket's flight attitude; the rudder blade control component is arranged below the rocket body; Ducted power assembly: used to provide the thrust required for rocket flight; the ducted power assembly is set in the power cabin of the rocket body and is located above the rudder control assembly; The flight control system is arranged in the avionics cabin of the rocket body, and is connected to the ducted power assembly and the rudder blade control assembly, and the ducted power assembly and the rudder blade control assembly are controlled by the flight control system; Debugging component: used to verify the response state of the ducted rocket under different control parameters; the debugging component at least includes: a universal swing component for realizing universal swing motion and a center of mass single-axis swing component for realizing single-axis swing motion; The universal swing assembly is arranged on the top of the rocket body and connected to the upper end of each carbon fiber main beam; The center-of-mass single-axis swing assembly is arranged below the flight control system, and the center-of-mass single-axis swing assembly is rotationally connected to the rocket body, and the rotationally connected position is located on the plane where the center of mass of the rocket body is located; The center of mass single-axis swing assembly is also rotatably connected to the carbon fiber main beam, and the position of 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 ducted rocket with adjustable parameters according to claim 1, characterized in that: There are four carbon fiber main beams, which are evenly spaced 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 carbon fiber main beam and the fourth carbon fiber main beam respectively.

3. The ducted rocket with adjustable parameters according to claim 2, characterized in that: The universal swing assembly includes: a spherical bearing, a straight code and a debugging head cone for realizing universal swing motion; 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 debugging head cone; The lower end of the debugging nose cone is detachably connected to the upper end of each carbon fiber main beam; When performing universal swing debugging, fix one end of the straight code on the first placing device, and fix the other end of the straight code on the second placing device, and make the rocket body located between the first placing device and the second placing device, so that the rocket body can perform universal swing motion around the fixed straight code.

4. The ducted rocket with adjustable parameters according to claim 3, characterized in that: Place one end of the straight code on the first placement device, and press the one end of the straight code with a first fixing object to fix the one end of the straight code on the first placement device; place the other end of the straight code on the second placement device, and press the other end of the straight code with a second fixing object to fix the other end of the straight code on the second placement device.

5. The ducted rocket with adjustable parameters according to claim 3, characterized in that: The upper end of the joint bearing is connected to the middle part of the straight code through screws; the lower end of the joint bearing is connected to the upper end of the debugging head cone through screws.

6. The ducted rocket with adjustable parameters according to claim 3, characterized in that: The lower end of the debugging nose cone is connected to the upper end of each carbon fiber main beam by screws.

7. The ducted rocket with adjustable parameters according to claim 2, characterized in that: The centroid single-axis swing assembly includes: a first debugging bracket, a second debugging bracket and a carbon fiber round rod; a first centroid hole is arranged in the middle of the first debugging bracket; a second centroid hole is arranged in the middle of the second debugging bracket; Wherein, 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 round rod sequentially passes through the first mass center hole, the mass center of the rocket body, and the second mass center hole; When performing single-axis swing debugging, one end of the carbon fiber round rod is fixed on the third placing device, and the other end of the carbon fiber round rod is fixed on the fourth placing device, and the rocket body is located between the third placing device and the fourth placing device. Then, the rocket body can perform single-axis swing motion around the fixed carbon fiber round rod.

8. The ducted rocket with adjustable parameters according to claim 7, characterized in that: Place one end of the carbon fiber round rod on the third placing device, and press one end of the carbon fiber round rod with a third fixing object to fix one end of the carbon fiber round rod on the third placing device; place the other end of the carbon fiber round rod on the fourth placing device, and press the other end of the carbon fiber round rod with a fourth fixing object to fix the other end of the carbon fiber round rod on the fourth placing device.

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

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

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