An attitude control and trajectory change system for rocket models

Abstract

The invention discloses an attitude control and orbit change system for a rocket model, comprising: a ground launch control device, a timing control module, an attitude control and orbit change module, a power supply module and more than two attitude control engines; the ground launch control device is used for setting a delay sequence for the timing control module and sending a start instruction to the timing control module; the timing control module is connected with all trigger relays of the attitude control and orbit change module according to the set delay sequence, thereby realizing the power-on of the trigger relays; the single-chip microcomputer of the attitude control and orbit change module is used for detecting the current angle attitude of the rocket model, and controlling more than one trigger relay corresponding to the attitude control engine to close according to the angle attitude; when the trigger relay is in a powered-on and closed state, the corresponding attitude control engine is ignited. The invention realizes the ballistic orbit change of the rocket model by combining the single-chip microcomputer technology with the model rocket engine technology, and solves the defects of the mercury switch type attitude and orbit change control system and the aerodynamic control system.

Description

Technical Field

[0001] The invention belongs to the technical field of aerospace models, and in particular relates to an attitude control and trajectory change system for a rocket model. Background Art

[0002] Domestic aerospace models are mainly Dongfeng-1, Xiaolishi, Feitianmeng, Tianying Spin Wing, Hercules and Changzheng-2C. These rocket models are all launched vertically. After launch, they are constrained by the launch rod, and the flight attitude and trajectory generally do not change. The simple aerospace model trajectory change system is mainly used on rocket models with a diameter of more than 120mm. After the rocket model equipped with this system is launched, it can complete the trajectory change flight according to the set timing and launch angle.

[0003] The trajectory change system is mainly used to achieve missile trajectory change flight, and is mainly used in some ballistic missiles. There is no such mature technology in the field of aerospace models. There are two main methods close to the attitude control of aircraft in the model field: mercury switch attitude trajectory change control system and aerodynamic control.

[0004] 1. Mercury switch type attitude change control system

[0005] Mercury switch, also known as tilt switch, stores a small drop of mercury in a small container connected to an electrode. Most of the containers are vacuum or injected with inert gas. The mercury switch type attitude control system is based on the mercury switch. With the help of the characteristics of the mercury switch and combined with the attitude change of the rocket model in the air, the attitude change of the rocket model is realized, and it is used in conjunction with the timing control circuit. When in use, according to the predetermined attitude change direction, a certain launch angle is preset for the launch rocket. After the igniter takes off, due to the tilt of the rocket model, the mercury in the corresponding mercury switch flows, and the switch is closed. When the set timing is reached, the mercury attitude control system is energized and the corresponding attitude control engine is controlled to work, thereby realizing the attitude control change of the rocket model.

[0006] 2. Aerodynamic control

[0007] Aerodynamic control is based on the principle of relativity of motion and the basic laws of gas flow. When an aircraft flies at a certain speed in the atmosphere, it will be affected by aerodynamic forces. Aerodynamic forces can be decomposed into lift, side force and drag, and the corresponding aerodynamic moments can be decomposed into rolling moment, yaw moment and pitch moment that affect the attitude of the aircraft. Aerodynamic forces and moments are related to the flight speed, flight altitude, shape of the aircraft and the attitude of the aircraft relative to the incoming flow. The greater the incoming flow speed, that is, the greater the speed of the aircraft, the greater the kinetic energy. After the incoming flow hits the aircraft, most of the kinetic energy is converted into pressure energy due to obstruction, and the total aerodynamic force also increases. Basically, lift, side force and drag are proportional to the square of the aircraft speed. The greater the air density, the greater the inertia of the air, and the greater the thrust required for the aircraft to fly forward. According to the principle of action and reaction, the air will act on the aircraft with greater force. Therefore, aerodynamic force is proportional to air density. Since air density decreases with increasing altitude, the higher the altitude, the different airflow velocity distribution acting on the aircraft, which will inevitably affect the size and direction of aerodynamics. Using aerodynamics to control the attitude of an aircraft is a mature technology. This technology detects the attitude, flight speed, air pressure and other parameters of the aircraft and feeds them back to the internal computer system. The computer system analyzes and calculates based on the detected data, and then sends control instructions to the steering gear system, which adjusts the wings on the aircraft to achieve attitude control.

[0008] However, the mercury switch type attitude control system and aerodynamic control have the following defects:

[0009] (1) The core of the mercury switch-type attitude control system is the mercury switch, which is harmful to the human body and the environment. There are various accidents in the launch and flight of rocket models. If there is a malfunction during the flight, the rocket model will fall from a high altitude, causing damage to the system and the risk of mercury leakage.

[0010] (2) Aerodynamic control requires a high level of professional knowledge from the user. It is necessary to establish a mathematical model and conduct fluid dynamics analysis and complex mathematical calculations based on the power parameters, rocket model flight speed and other parameters and air fluid parameters.

[0011] (3) The aerodynamic control method has a complex structure, is difficult to manufacture, and has a relatively high cost. Summary of the invention

[0012] In view of this, the present invention provides an attitude control and trajectory change system for a rocket model. By combining single-chip microcomputer technology with model rocket engine technology, the ballistic trajectory change of the rocket model is realized, and the defects of the mercury switch type attitude trajectory change control system and the aerodynamic control system are solved.

[0013] The present invention is achieved through the following technical solutions:

[0014] An attitude control and orbit change system for a rocket model, comprising: a ground launch control device, a timing control module, an attitude control and orbit change module, a power module and two or more attitude control engines; the attitude control and orbit change system is integrated on the rocket model, and the two or more attitude control engines are located at the upper end of the center of mass of the rocket model;

[0015] The attitude control and trajectory change module includes a single chip microcomputer and two or more trigger relays; the two or more trigger relays are connected to the two or more attitude control engines in a one-to-one correspondence;

[0016] The power supply module is used to supply power to the timing control module;

[0017] The ground control device is used to set a delay sequence for the timing control module and send a start instruction to the timing control module, and at the same time control whether the power supply module supplies power to the timing control module;

[0018] After receiving the start command from the ground control device, the timing control module is connected to all the trigger relays of the attitude control and trajectory change module according to the set delay timing, thereby energizing the trigger relays;

[0019] The single-chip microcomputer of the attitude control trajectory change module is used to detect the current angular attitude of the rocket model, and control one or more trigger relays corresponding to the attitude control engine to close according to the angular attitude; when the trigger relay is in a powered and closed state, the corresponding attitude control engine is ignited, and the attitude control engine generates radial thrust after ignition. Under the action of the radial thrust, the attitude of the rocket model changes, thereby realizing the trajectory change flight of the rocket model.

[0020] Furthermore, the two or more attitude control engines are distributed in a circle, and the centers of the two or more attitude control engines arranged in a circle and the center of mass of the rocket model are both located on the axis of the rocket model.

[0021] Beneficial effects:

[0022] (1) Since the present invention uses a single-chip microcomputer and a model rocket engine (the attitude control engine is a type of model rocket engine) to achieve the attitude control trajectory change of the rocket model, there is no risk of leakage, and it is harmless to the human body and the environment.

[0023] (2) Since the single-chip microcomputer technology and model rocket engine technology are very mature, the present invention only needs to clarify the logical relationship according to the flight process of the rocket model, and then program the single-chip microcomputer according to the logical relationship, thus avoiding the need for professional knowledge and software.

[0024] (3) Since the single-chip microcomputer has a high degree of integration, the structure of the present invention is relatively simple. As long as the relevant structural design is carried out according to the size of each module, the entire system can be installed in the rocket model. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 It is a composition diagram of the present invention;

[0026] Figure 2 It is a schematic diagram of the layout of the present invention;

[0027] Figure 3 This is the outline drawing of the rocket model;

[0028] Among them, 2-attitude control engine, 3-attitude control trajectory change module, 4-timing control module. DETAILED DESCRIPTION

[0029] The present invention is described in detail below with reference to the accompanying drawings and embodiments.

[0030] This embodiment provides an attitude control and trajectory change system for a rocket model, see the attached Figure 1 , including: ground launch control device, timing control module, attitude control and trajectory change module, power module and more than two attitude control engines; see attached Figure 2 , the attitude control and trajectory change system is integrated on the rocket model, the two or more attitude control engines are distributed in a circle on the upper end of the center of mass of the rocket model, and the centers of the two or more attitude control engines arranged in a circle and the center of mass of the rocket model are both located on the axis of the rocket model;

[0031] The attitude control and trajectory change module includes a single chip microcomputer and two or more trigger relays;

[0032] The ground launch control device is connected to the timing control module and the power supply module through the ground launch cable respectively, and the timing control module is connected to the input end of the trigger relay of the attitude control and orbit change module and the power supply module through the signal cable respectively; the two or more attitude control engines are connected to the output end of the trigger relay of the attitude control and orbit change module in a one-to-one correspondence;

[0033] The power supply module is used to supply power to the timing control module;

[0034] The ground control device is used to set a delay sequence for the timing control module and send a start instruction to the timing control module, and at the same time control whether the power supply module supplies power to the timing control module;

[0035] The timing control module is used to perform timing control on the attitude control and orbit change of the rocket model. After receiving the start command from the ground launch control device, it is connected to all the trigger relays of the attitude control and orbit change module according to the set delay timing, thereby realizing the energization of the trigger relays;

[0036] The attitude control trajectory change module is a core component. The single-chip microcomputer is used to detect the current angular attitude of the rocket model, and control one or more trigger relays corresponding to the attitude control engine to close according to the angular attitude (initially, all trigger relays remain in the disconnected state); when the trigger relay is in the energized and closed state, the corresponding attitude control engine is ignited, and the attitude control engine generates radial thrust after ignition. Since the attitude control engine is located at the upper end of the center of mass of the rocket model, the attitude of the rocket model changes under the action of the radial thrust, thereby realizing the trajectory change flight of the rocket model.

[0037] During operation, the attitude control and trajectory change system is integrated into the rocket model, and all launch preparations are completed. The handheld ground launch control device is turned on, and the delay timing of the attitude control and trajectory change module is set on the panel of the ground launch control device. After the setting is completed, the timing control module is charged through the power module. After charging, the launch button on the panel of the ground launch control device is pressed, and the rocket model ignites and takes off. At the same time, the ground launch control device sends a start command to the timing control module; the attitude control and trajectory change module single chip microcomputer detects the current angle attitude of the rocket model (i.e., the tilt angle a), see attached Figure 3 , and according to the angle attitude, one or more trigger relays corresponding to the attitude control engine are controlled to close. When the first time point of the delay sequence of the timing control module is reached, all the trigger relays of the attitude control trajectory change module are energized; the attitude control engine corresponding to the trigger relay in the energized and closed state is ignited, and the attitude control engine generates radial thrust after ignition. Under the action of the radial thrust, the attitude of the rocket model changes, thereby realizing the trajectory change flight of the rocket model.

[0038] In summary, the above are only preferred embodiments of the present invention and are not intended to limit the protection scope of the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. An attitude control and trajectory change system for a rocket model, characterized in that: include: A ground launch control device, a timing control module, an attitude control and trajectory change module, a power module and two or more attitude control engines; the attitude control and trajectory change system is integrated on a rocket model, and the two or more attitude control engines are located at the upper end of the center of mass of the rocket model; The attitude control and trajectory change module includes a single chip microcomputer and two or more trigger relays; the two or more trigger relays are connected to the two or more attitude control engines in a one-to-one correspondence; The power supply module is used to supply power to the timing control module; The ground launch control device is provided with a panel, through which the delay timing is set for the timing control module, and a launch button is also provided on the panel. When the launch button is pressed, the corresponding rocket model ignites and takes off. At the same time, the ground launch control device sends a start instruction to the timing control module, and controls whether the power supply module supplies power to the timing control module; After receiving the start command from the ground control device, the timing control module is connected to all the trigger relays of the attitude control and trajectory change module according to the set delay timing, thereby energizing the trigger relays; The single-chip microcomputer of the attitude control trajectory change module is used to detect the current angular attitude of the rocket model, and control one or more trigger relays corresponding to the attitude control engine to close according to the angular attitude; when the trigger relay is in a powered and closed state, the corresponding attitude control engine is ignited, and the attitude control engine generates radial thrust after ignition. Under the action of the radial thrust, the attitude of the rocket model changes, thereby realizing the trajectory change flight of the rocket model.

2. The attitude control and trajectory change system for a rocket model as claimed in claim 1, characterized in that: The two or more attitude control engines are distributed in a circle, and the centers of the two or more attitude control engines arranged in a circle and the center of mass of the rocket model are both located on the axis of the rocket model.

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