Rebullistic missile command and control model based on space-based information support

Abstract

The invention discloses a bulletproof missile command and control model based on space-based information support, and relates to the technical field of missile simulation control, the bulletproof missile command and control model comprises a power assembly, the power assembly comprises a power cylinder, the power cylinder is fixedly provided with a movable frame, and the movable frame is in spherical pair connection with a nozzle; a second driving motor and a first driving motor are fixedly installed in the power cylinder through a second driving motor support and a first driving motor support respectively, and a second power fan is fixedly installed on an output shaft of the second driving motor. By arranging the power assembly, the flight attitude of the model can be adjusted in real time, and the launched model can be recycled, so that the model can be repeatedly used; by arranging the control assembly, the warhead model of the model can be separated from the device, so that a ballistic missile command model which is more practical is simulated; the electromagnetic ejection mode is adopted, the initial speed of ejection is increased, and the power assembly can suck more air when started.

Description

Technical Field

[0001] The invention relates to the technical field of missile simulation control, in particular to an anti-ballistic missile command and control model based on space-based information support. Background Art

[0002] A ballistic missile is a missile that flies according to a predetermined program under the thrust of a rocket engine and flies along a free parabola trajectory after being shut down. Its flight trajectory is generally divided into an active segment and a passive segment: the active segment (also called the powered flight segment or booster segment) is the flight path of the missile from the launch point to the shutdown of the rocket engine under the thrust of the rocket engine and the guidance system; the passive segment includes the free flight segment and the reentry segment, which is the path of the missile flying at a given speed and ballistic angle obtained at the end of the active segment until the warhead detonates. In the field of science and education, missile models are needed for real action simulation, but the current ballistic missile command and control models only have similar appearances and do not have flight capabilities.

[0003] Prior art: A utility model patent with announcement number CN205759682U discloses a missile vehicle model control system, including a power module, a single-chip microcomputer, a wireless receiving module, a left motor, and a right motor. The characteristics of the utility model patent are that the 12V port of the power module is connected to the positive power pole of the left motor and the right motor, the GND2 port of the power module is connected to the negative power pole of the left motor and the right motor, the single-chip microcomputer is connected to the control port of the left and right motors, the single-chip microcomputer is connected to the laser through a triode, the single-chip microcomputer is also connected to the electric push rod through a relay module, and the single-chip microcomputer is also connected to the first grayscale sensor and the second grayscale sensor. The utility model patent has a simple structure and is easy to use, and is particularly suitable for use in a missile vehicle model control system. However, the prior art does not solve the above technical problems. Summary of the invention

[0004] In order to overcome the defects of the above-mentioned prior art, the present invention provides the following technical solutions: an anti-ballistic missile command and control model based on space-based information support, comprising a power assembly, the power assembly comprising a power cylinder, a movable frame is fixedly installed on the power cylinder, a nozzle is connected to the ball joint on the movable frame, a second drive motor and a first drive motor are respectively fixedly installed in the power cylinder through a second drive motor bracket and a first drive motor bracket, a second power fan is fixedly installed on the output shaft of the second drive motor, and a first power fan is fixedly installed on the output shaft of the first drive motor; a control assembly, the control assembly comprises an air inlet fixedly installed on the power cylinder, a battery is fixedly installed on one side of the air inlet close to the power cylinder through a battery bracket, a flight control is fixedly arranged on the battery, an electric adjustment protective shell is fixedly installed on the other side of the air inlet, an electromagnet is fixedly installed on the electric adjustment protective shell, and a warhead model is magnetically matched on the electromagnet.

[0005] Preferably, two connecting blocks spaced 90° apart are provided on the nozzle, two 90° servos are fixedly mounted on the movable frame, and the swing arms of the servos are movably connected to the connecting blocks via carbon fiber push-pull rods.

[0006] Preferably, the swing arm of the steering gear is connected to the carbon fiber push-pull rod ball pair, and the connecting block is connected to the carbon fiber push-pull rod ball pair.

[0007] Preferably, a fairing is also fixedly mounted on the power cylinder, and a gap is provided between the fairing and the first power fan.

[0008] Preferably, an auxiliary air hole is provided on the air inlet between the electric adjustment protection shell and the flight control.

[0009] Preferably, it also includes a sliding cylinder, one end of the inner wall of the sliding cylinder is provided with a step, and a sliding iron block is overlapped on the step surface, and a ventilation through hole is opened on the sliding iron block.

[0010] Preferably, an electromagnetic winding is fixedly mounted around the sliding cylinder, and the sliding iron block is fixedly connected to one end of the towing rope.

[0011] Preferably, one end of the electromagnetic winding is electrically connected to one end of the auxiliary normally open contact of the contactor, the other end of the auxiliary normally open contact of the contactor is electrically connected to one end of the capacitor, the other end of the capacitor is electrically connected to the other end of the electromagnetic winding, the two ends of the capacitor are electrically connected to the output end of the inverter, the input end of the inverter is electrically connected to the two ends of the power supply, and a first normally open button is connected in series, and the magnetic attraction coil in the contactor is electrically connected to the two ends of the power supply, and a second normally open button is connected in series.

[0012] Compared with the prior art, the present invention has the following beneficial effects: (1) By setting a power component, the present invention can adjust the flight attitude of the model in real time, and can recover the launched model, so that the model can be reused many times; (2) By setting a control component, the present invention can separate the warhead model of the model from the device, thereby simulating a ballistic missile command model that is more in line with reality; (3) The present invention adopts an electromagnetic catapult method to increase the initial velocity of the launch, so that the power component can inhale more air when starting. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 It is a cross-sectional view of the overall structure of the present invention.

[0014] Figure 2 It is a schematic diagram of the overall structure of the present invention.

[0015] Figure 3 It is a structural schematic diagram of the sliding iron block of the present invention.

[0016] Figure 4 It is a cross-sectional view of the movable frame structure of the present invention.

[0017] Figure 5 This is a structural cross-sectional view of the second power fan of the present invention.

[0018] Figure 6 It is a structural schematic diagram of the battery of the present invention.

[0019] Figure 7 This is the electromagnetic winding control circuit diagram of the present invention.

[0020] In the figure: 101-movable frame; 102-servo; 103-carbon fiber push-pull rod; 104-connecting block; 105-nozzle; 106-power cylinder; 107-fairing; 108-first power fan; 109-first drive motor; 110-second power fan; 111-second drive motor; 112-second drive motor bracket; 113-first drive motor bracket; 201-air inlet; 202-flight control; 203-battery; 204-battery bracket; 205-auxiliary air hole; 206-electric adjustment protective shell; 207-electromagnet; 208-warhead model; 301-sliding cylinder; 302-electromagnetic winding; 303-drag rope; 304-sliding iron block; 3041-ventilation through hole; C-capacitor; KM-contactor; SB1-first normally open button; SB2-second normally open button. DETAILED DESCRIPTION

[0021] The technical solution of the present invention is further described below with reference to the accompanying drawings and through specific implementation methods.

[0022] Among them, the drawings are only used for illustrative explanations, and they only represent schematic diagrams rather than actual pictures, and should not be understood as limitations on this patent; in order to better illustrate the embodiments of the present invention, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product; for those skilled in the art, it is understandable that some well-known structures and their descriptions in the drawings may be omitted.

[0023] like Figure 3-Figure 5As shown, the present invention provides a technical solution: an anti-ballistic missile command and control model based on space-based information support, including a power assembly, the power assembly including a power cylinder 106, a movable frame 101 is fixedly installed on the power cylinder 106, a nozzle 105 is connected to the movable frame 101 by a ball joint, a second drive motor 111 and a first drive motor 109 are respectively fixedly installed in the power cylinder 106 through a second drive motor bracket 112 and a first drive motor bracket 113, a second power fan 110 is fixedly installed on the output shaft of the second drive motor 111, and a first drive motor 109 is fixedly installed in the power cylinder 106 through a second drive motor bracket 112 and a first drive motor bracket 113. A first power fan 108 is fixedly mounted on the output shaft of the engine 109, two connecting blocks 104 spaced 90° apart are arranged on the nozzle 105, two 90° servos 102 are fixedly mounted on the movable frame 101, the swing arm of the servo 102 is movably connected to the connecting block 104 through a carbon fiber push-pull rod 103, the swing arm of the servo 102 is connected to the carbon fiber push-pull rod 103 by a ball joint, the connecting block 104 is connected to the carbon fiber push-pull rod 103 by a ball joint, a fairing 107 is also fixedly mounted on the power cylinder 106, and a gap is arranged between the fairing 107 and the first power fan 108.

[0024] like Figure 6 As shown, the control component includes an air inlet 201 fixedly mounted on the power cylinder 106, a battery 203 is fixedly mounted on one side of the air inlet 201 close to the power cylinder 106 through a battery bracket 204, a flight control 202 is fixedly arranged on the battery 203, an electric adjustment protective shell 206 is fixedly mounted on the other side of the air inlet 201, an electromagnet 207 is fixedly mounted on the electric adjustment protective shell 206, a warhead model 208 is magnetically attached to the electromagnet 207, and an auxiliary air hole 205 is opened on the air inlet 201 between the electric adjustment protective shell 206 and the flight control 202.

[0025] like Figure 1 , Figure 2 and Figure 7 As shown, it also includes a sliding cylinder 301, one end of the inner wall of the sliding cylinder 301 is provided with a step, and a sliding iron block 304 is overlapped on the step surface, and a ventilation through hole 3041 is opened on the sliding iron block 304, and an electromagnetic winding 302 is fixedly installed around the sliding cylinder 301, the sliding iron block 304 is fixedly connected to one end of the drag rope 303, one end of the electromagnetic winding 302 is electrically connected to one end of the auxiliary normally open contact of the contactor KM, the other end of the auxiliary normally open contact of the contactor KM is electrically connected to one end of the capacitor C, the other end of the capacitor C is electrically connected to the other end of the electromagnetic winding 302, the two ends of the capacitor C are electrically connected to the output end of the inverter, the input end of the inverter is electrically connected to the two ends of the power supply, and a first normally open button SB1 is connected in series, the magnetic attraction coil in the contactor KM is electrically connected to the two ends of the power supply, and a second normally open button SB2 is connected in series.

[0026] The working principle of an anti-ballistic missile command and control model based on space-based information support disclosed in the present invention is as follows: one end of a towing rope 303 is fixed to the ground, and then a sliding cylinder 301 is vertically fixed to the ground. Before use, the first normally open button SB1 is first pressed, and the power supply supplies power to the inverter, and the inverter charges the capacitor C. Then the first normally open button SB1 is released, and the second normally open button SB2 is pressed, and the magnetic attraction coil in the contactor KM is energized, and the auxiliary normally open contact of the contactor KM is closed. At this time, the electromagnetic winding 302 is connected in parallel to the two ends of the capacitor C, and the capacitor C will release the electric energy to the electromagnetic winding 302 instantly. At this time, the electromagnetic winding 302 generates magnetic force, thereby attracting the sliding iron block 304, and the sliding iron block 304 will move toward the electromagnetic winding 302. Because the sliding iron block 304 is overlapped with the nozzle 105, all the components on the nozzle 105 will move together. Since the towing rope 303 is connected to the sliding iron block 304, when the sliding iron block 304 moves to a certain When the height reaches 90°, it will be unable to move upwards under the action of the towing rope 303. At this time, the components on the nozzle 105 continue to move upwards. During this period, the second drive motor 111 and the first drive motor 109 are started by the flight control 202 and the electric regulator set in the electric regulator protective shell 206 (the second drive motor 111 and the first drive motor 109 have opposite rotation directions, thereby offsetting the torque on the output shaft). The start of the first drive motor 109 and the second drive motor 111 will drive the rotation of the first power fan 108 and the second power fan 110. The rotation of the first power fan 108 and the second power fan 110 will drive the air in the air inlet 201 to flow downward, and then spray downward through the nozzle 105, thereby generating lift. By controlling the swing of the two servos 102, the swing arm of the servo 102 will drive the nozzle 105 to swing freely through the carbon fiber push-pull rod 103 and the connecting block 104. The swing of the nozzle 105 will change the direction of the jet airflow, thereby changing the lift direction, and then controlling the flight attitude of the model. When the model rises to the required height, the rotation speed of the second drive motor 111 and the first drive motor 109 is reduced, thereby reducing the flight speed of the model. Before this process, the electromagnet 207 is powered off to separate the electromagnet 207 from the warhead model 208. At this time, the warhead model 208 will perform parabolic motion under the action of inertia until the warhead model 208 falls to the ground. The model is recovered by controlling the swing direction of the nozzle 105 and the rotation speed of the second drive motor 111 and the first drive motor 109.

[0027] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. An anti-ballistic missile command and control model based on space-based information support, characterized by: The invention comprises a power assembly, wherein the power assembly comprises a power cylinder (106), a movable frame (101) is fixedly mounted on the power cylinder (106), a nozzle (105) is connected to the movable frame (101) by a ball joint, a second drive motor (111) and a first drive motor (109) are respectively fixedly mounted in the power cylinder (106) through a second drive motor bracket (112) and a first drive motor bracket (113), a second power fan (110) is fixedly mounted on the output shaft of the second drive motor (111), and a first power fan (108) is fixedly mounted on the output shaft of the first drive motor (109); A control component, the control component comprising an air intake duct (201) fixedly mounted on a power cylinder (106), a battery (203) fixedly mounted on one side of the air intake duct (201) close to the power cylinder (106) via a battery bracket (204), a flight control (202) fixedly arranged on the battery (203), an electric control protection shell (206) fixedly mounted on the other side of the air intake duct (201), an electromagnet (207) fixedly mounted on the electric control protection shell (206), and a warhead model (208) magnetically matched on the electromagnet (207).

2. The anti-ballistic missile command and control model based on space-based information support according to claim 1 is characterized by: The nozzle (105) is provided with two connection blocks (104) spaced 90 degrees apart, and the movable frame (101) is fixedly mounted with two 90-degree steering gears (102), and the swing arms of the steering gears (102) are movably connected to the connection blocks (104) via carbon fiber push-pull rods (103).

3. The anti-ballistic missile command and control model based on space-based information support according to claim 2 is characterized in that: The swing arm of the steering gear (102) is connected to the carbon fiber push-pull rod (103) by a ball joint, and the connecting block (104) is connected to the carbon fiber push-pull rod (103) by a ball joint.

4. The anti-ballistic missile command and control model based on space-based information support according to claim 3 is characterized by: A fairing (107) is also fixedly mounted on the power cylinder (106), and a gap is provided between the fairing (107) and the first power fan (108).

5. The anti-ballistic missile command and control model based on space-based information support according to claim 4 is characterized in that: An auxiliary air hole (205) is provided on the air inlet (201) at a position between the electric control protection shell (206) and the flight control (202).

6. The anti-ballistic missile command and control model based on space-based information support according to claim 5 is characterized by: The invention also comprises a sliding cylinder (301), one end of the inner wall of the sliding cylinder (301) is provided with a step, a sliding iron block (304) is overlapped on the step surface, and a ventilation through hole (3041) is opened on the sliding iron block (304).

7. The anti-ballistic missile command and control model based on space-based information support according to claim 6 is characterized by: An electromagnetic winding (302) is fixedly mounted around the sliding cylinder (301), and the sliding iron block (304) is fixedly connected to one end of the towing rope (303).

8. The anti-ballistic missile command and control model based on space-based information support according to claim 7 is characterized by: One end of the electromagnetic winding (302) is electrically connected to one end of the auxiliary normally open contact of the contactor (KM), the other end of the auxiliary normally open contact of the contactor (KM) is electrically connected to one end of the capacitor (C), the other end of the capacitor (C) is electrically connected to the other end of the electromagnetic winding (302), the two ends of the capacitor (C) are electrically connected to the output end of the inverter, the input end of the inverter is electrically connected to the two ends of the power supply, and a first normally open button (SB1) is connected in series, the magnetic attraction coil in the contactor (KM) is electrically connected to the two ends of the power supply, and a second normally open button (SB2) is connected in series.

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