JPH07127999A - Actuator for spin missile - Google Patents

Abstract

PURPOSE:To provide a small, low-cost actuator to be used in a spin missile in which its operating range is high. CONSTITUTION:This actuator is comprised of a cylinder, a piston 2, a shaft 3 integrally assembled with the piston 2, an operating wing 8 of which angle is changed by the shaft 3, valves 4a, 4b for adjusting a pressure within the cylinder, a pressurizing source 9 for supplying pressure to the valves 4a, 4b, and a solenoid 5 for driving the valves 4a, 4b. The solenoid 5 and the valves 4a, 4b are driven at a predetermined position of a spin position of a missile, a pressurizing side and a pressure reducing side of a cylinder which is divided into two segments by the piston 2 are reversed from each other and then the operating vane 8 performs a repeating operation. With such an arrangement as above, a complex control can be eliminated, a range of the actuator is increased, a simplified structure reduces the size and cost of the actuator.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention is used in a spin missile that flies while rotating around the longitudinal axis of a machine body, and is applied to both an aerodynamic steering actuator or an aerodynamic and reaction force combined actuator. The present invention relates to a missile actuator.

[0002]

2. Description of the Related Art FIG. 6 is a block diagram of a conventional spin missile actuator. 1 is a cylinder which will be described later, 2 is a piston which divides the inside of the cylinder 1 into two and moves in the direction of arrow a, and 3 is the piston. A shaft which is integral with the piston 2 and moves a steering wing to be described later, 4 is a valve for supplying pressure to the cylinder 1, 5 is a solenoid for driving the valve 4, 6
Is a discharge port provided so as to discharge the pressure inside the cylinder 1 through the valve 4, 7 is a pressurizing pipe for supplying a reaction force to the valve 4 and the cylinder 1, and 8 is according to the operation of the shaft. A moving steering blade, 9 is a pressure source for supplying pressure to the pressure pipe 7, 10 is a pressure seal provided so that the pressure of the cylinder 1 does not leak to the outside according to the movement of the shaft, 11 is the shaft 3 A displacement detector that detects the amount of displacement, 12 is a displacement comparator that compares the output of the displacement detector 11 with an angle command, arrow a is the shaft moving direction, and arrow b is the steering blade angle changing direction.

The pressure of the pressure source 9 is guided to the valve 4 via the pressure pipe 7, the valve 4 is opened and closed by the solenoid 5, and the pressure of the pressure source 9 is guided to the cylinder 1 when the valve 4 is open. The pressure in the cylinder 1 rises, and when the valve 4 is closed, the medium in the cylinder is discharged to the outside from the discharge port 6 and the pressure in the cylinder 1 decreases.
A pressure difference occurs between the piston 2 and the shaft 3 due to the pressure difference, the movement of the shaft 3 causes the steering blade 8 to change its angle in the direction of the arrow, and the displacement of the shaft 3 is displaced. The detector 11 measures the angle output of the steering wing 8, the displacement comparator 12 compares the angle output with the angle command, and the solenoid 5 operates according to the difference between the two.

[0004]

Comparing a spin missile flying while rotating about the longitudinal axis of the airframe with a missile flying without rotating, the spin missile has a frequency of 3 to 10 times or more the rotation frequency of the airframe. A moving actuator is required, and a high bandwidth actuator needs to be adopted. On the other hand, even if there is an error in the setting angle of the steering blade, the turning force due to the steering angle setting error of the steering blade is smoothed by the rotation of the airframe and does not significantly affect the missile trajectory. Therefore, in the spin missile actuator, it is necessary to attach importance to the responsiveness rather than the angle setting accuracy. Further, since the spin missile system is adopted to share the pitch control and yaw control actuators, the spin missile is usually a small missile, and the actuator is also required to be downsized. Also, in the spin missile, the spin frequency of the airframe and the angle change of the steering blade are synchronized, and when the aircraft reaches the predetermined roll direction, the steering blade changes its angle to the maximum steering angle. It is characterized by turning in a predetermined direction.

In conventional spin missile actuators, the accuracy of the rudder angle setting is emphasized rather than synchronization with a predetermined frequency. Therefore, the pressure source 9, valve 4, cylinder 1, piston 2, shaft 3, etc. In addition to the basic constituent elements of (1), the displacement detector 11, the displacement comparator 12, etc. are required, and there is a problem that the structure is complicated and it is difficult to downsize the actuator.

Further, in the conventional actuator for spin missile, since the steering blade is set to a steering angle other than the maximum steering angle, the piston 2 is moved to an arbitrary position depending on the balance between the valve 4a and the valve 4b. Therefore, there is a problem that the control becomes complicated and it is difficult to improve the response of the actuator.

Further, the conventional actuator for spin missile requires the displacement detector 11 and the displacement comparator 12 and has a problem that the price is high.

[0008]

An actuator for spin missiles according to the present invention comprises a pressure source for generating a driving force for steering blade deflection, a valve for distributing the pressure of the pressure source to a cylinder and a discharge port, and A solenoid that drives the valve, a piston that is inside the cylinder and reciprocates inside the cylinder,
A shaft that is integral with the piston and a steering wing that is driven by the shaft are provided.

Further, the spin missile actuator according to the present invention is such that a pressure source for generating a driving force for changing the steering blade angle, a pressure regulating valve for adjusting the pressure of the pressure source, and a predetermined pressure by the pressure regulating valve. A valve that distributes the pressure maintained at a cylinder and a discharge port, a connecting rod that switches the opening and closing direction of the valve, a piston that is inside the cylinder and reciprocates inside the cylinder, a shaft that is integral with the piston, The steering wing driven by the shaft and the switching rod that is integral with the shaft and that interferes with the connecting rod at a predetermined position are provided.

Further, the spin missile actuator according to the present invention is provided with a pressure source for generating a driving force for changing the steering blade angle, a pressure regulating valve for adjusting the pressure of the pressure source, and a predetermined pressure by the pressure regulating valve. A valve that distributes the pressure maintained at the cylinder and the discharge port, a solenoid that drives the valve, and a piston that is in the cylinder and reciprocates inside the cylinder;
A shaft that is integral with the piston, a steering wing that is driven by the shaft, and a switch switching plate that is integral with the shaft and that interferes with the switch at a predetermined position.

Further, the actuator for spin missile according to the present invention comprises a pressure source for generating a driving force for changing the steering blade angle, a valve for discharging the pressure inside the cylinder, a solenoid for driving the valve, and a cylinder A piston that reciprocates inside the cylinder, a shaft that is integral with the piston, a steering blade that is driven by the cylinder, and a switch selector plate that is integral with the shaft and that interferes with the switch at a predetermined position. It is the one provided with.

Further, the spin missile actuator according to the present invention includes a pressurizing source for generating a driving force for changing the steering blade angle, a valve for discharging the pressure inside the cylinder, a solenoid for driving the valve, and the cylinder. A nozzle provided at the outlet of the high-pressure gas to be discharged further and provided in a predetermined direction and position so as to promote the effect of the steering blade, a piston in the cylinder that reciprocates inside the cylinder, and the piston And a steering wing driven by the shaft, and a switch switching plate that is integral with the shaft and interferes with the switch at a predetermined position.

[0013]

In the present invention, the solenoid is driven by a predetermined input signal corresponding to the rotation frequency of the spin missile, and one of the cylinders is pressurized and the other is depressurized by using two valves connected to the solenoid. By doing
Drives pistons, shafts, and steering wings.

In the present invention, the two valves are used to pressurize one of the cylinders and depressurize the other, thereby driving the piston, the shaft and the steering blade. Further, the supply pressure is adjusted by a predetermined pressure command corresponding to the rotation frequency of the spin missile to set the steering wing deflection frequency to a predetermined value. Further, the switching rod, which is integral with the shaft, switches the direction of the valve through the connecting rod when the piston reaches a predetermined position, reverses the pressurizing side and the depressurizing side, and the steering vanes make repetitive motions.

In the present invention, the two valves are used to pressurize one of the cylinders and depressurize the other, thereby driving the piston, the shaft, the steering blade, and the switch switching plate. Further, the supply pressure is adjusted by a predetermined pressure command corresponding to the rotation frequency of the spin missile to set the steering wing deflection frequency to a predetermined value. Further, the switch switching plate, which is integral with the shaft, switches the direction of the valve via the solenoid when the piston reaches a predetermined position, and reverses the pressurizing side and the depressurizing side, and the steering vanes make repetitive motions.

Further, according to the present invention, by opening one of the two valves and closing the other, one of the cylinders is pressurized and the other is depressurized to drive the piston, the shaft, the steering blade, and the switch switching plate. To do. Further, the supply pressure is adjusted by a predetermined pressure command corresponding to the rotation frequency of the spin missile to set the steering wing deflection frequency to a predetermined value. Further, the switch switching plate, which is integral with the shaft, switches the direction of the valve via the solenoid when the piston reaches a predetermined position, and reverses the pressurizing side and the depressurizing side, and the steering vanes make repetitive motions.

According to the present invention, one of the two valves is opened and the other is closed to pressurize one of the cylinders and depressurize the other, thereby driving the piston, the shaft, the steering blade, and the switch switching plate. To do. Further, the supply pressure is adjusted by a predetermined pressure command corresponding to the rotation frequency of the spin missile to set the steering wing deflection frequency to a predetermined value. Further, the switch switching plate, which is integral with the shaft, switches the direction of the valve via the solenoid when the piston reaches a predetermined position, and reverses the pressurizing side and the depressurizing side, and the steering vanes make repetitive motions. Further, a nozzle is provided at the gas discharge port of the valve, and the nozzle is arranged in a direction in which the effect of the steering blade is promoted, so that a missile with high responsiveness can be obtained by the high pressure gas discharged from the valve on the open side.

[0018]

EXAMPLES Example 1. 1 is a spin missile actuator according to a first embodiment of the present invention, in which 1 is a cylinder, 2 is a piston, 3 is a shaft, 4 is a valve, 5 is a solenoid, 6 is a discharge port, 7 is a pressure pipe, and 9 is a pressure pipe. Is a pressure source, 10 is a seal, arrow a is a shaft moving direction, arrow b is a steering blade angle changing direction, and arrow c is a valve opening / closing direction. In the present invention, a predetermined input signal synchronized with the spin frequency of the airframe is input to the solenoid 5 and the valve 4 is moved in the direction of arrow C.
Due to this, either one of the two pairs of cylinders 1 is pressurized, and the shaft 3 moves in the direction of arrow a due to the pressure difference between the two surfaces of the piston 2. The wing 8 interlocking with the shaft 3 reaches the maximum steering angle when the missile rotates and reaches a predetermined direction, so that the missile turns in a predetermined direction. The spin missile actuator according to the present invention is characterized by a simple structure and a small number of parts. Further, the two pairs of valves 4 are connected by an axis, and since synchronization of the two pairs of valves does not need to be a problem, control is easy and the actuator bandwidth is increased. Further, in the case of an actuator having the same volume as the conventional actuator for spin missile, the piston 2
If the pressure receiving area of is increased, the band of the actuator is further increased.

Example 2. 2 is a spin missile actuator according to a second embodiment of the present invention, in which 1 is a cylinder, 2 is a piston, 3 is a shaft, 4 is a valve, 6 is a discharge port, 7 is a pressurizing pipe, 8 is a steering blade, 9 is a pressure source, 10 is a seal, 13 is a pressure regulating valve, 14 is a connecting rod, 15 is a switching rod,
The arrow a indicates the shaft moving direction, and the arrow mouth indicates the steering blade angle changing direction. In FIG. 2, since the pressure of the pressure source 9 is applied to the cylinder 1b via the valve 4b, the piston 2, the shaft 3, and the switching rod 15 move in the direction of arrow a, and at the same time, the steering blade 8
Rotates in the direction of the arrow mouth. When the switching rod 15b reaches a predetermined position, the switching rod 15b pushes the connecting rod 14 in the direction of arrow a to reverse the opening / closing direction of the valve 4. When the opening / closing direction of the valve 4 is reversed, the cylinder 1a is pressed by the cylinder 1b, and the piston 2, the shaft 3, and the switching rod 15 move in the direction opposite to the arrow a. After that, the same operation is repeated, and the steering vane 8 repeatedly moves in a predetermined cycle. The pressure regulating valve 13 keeps the pressure inside the cylinder 1 at a predetermined value to obtain a predetermined blade repetition period.

Example 3. 3 is an actuator for a spin missile showing a third embodiment of the present invention, in which 1 is a cylinder, 2 is a piston, 3 is a shaft, 4 is a valve, 5 is a solenoid, 6 is a discharge port, 7 is a pressure pipe, and 8 is a pressure pipe. Is a steering blade, 9 is a pressure source, 10 is a seal, 13 is a pressure regulating valve, 16 is a switch switching plate, 17 is a switch, arrow a is a shaft moving direction, arrow mouth is a steering blade changing direction, and arrow c is a valve opening / closing. Direction. In FIG. 3, since the pressure of the pressure source 9 is applied to the cylinder 1b via the valve 4b, the piston 2, the shaft 3 and the switching plate 16 move in the direction of arrow a, and at the same time, the steering blade 8 rotates in the direction of arrow. To do. When the switching plate 16 reaches a predetermined position, the switching plate 16 comes into contact with the switch 17a and reverses the opening / closing direction of the valve 4 via the solenoid 5.
When the opening / closing direction of the valve 4 is reversed, the cylinder 1a is pressurized instead of the cylinder 1b, and the piston 2, the shaft 3, and the switching plate 16 move in the direction opposite to the arrow a. After that, the same operation is repeated, and the steering vane 8 repeatedly moves in a predetermined cycle. The pressure regulating valve 13 keeps the pressure inside the cylinder 1 at a predetermined value to obtain a predetermined blade repetition period.

Example 4. 4 is a spin missile actuator according to a fourth embodiment of the present invention, in which 1 is a cylinder, 2 is a piston, 3 is a shaft, 4 is a valve, 6 is a discharge port, 7 is a pressurizing pipe, 8 is a steering blade, 9 is a pressure source, 10 is a seal, 16 is a switch switching plate, 17 is a switch, 18
Is a valve opening / closing indicator, arrow a is the shaft moving direction, and arrow mouth is the steering blade angle changing direction. In FIG. 4, the pressure of the pressure source 9 is applied to both the cylinders 1a and 1b, but the valve 4a is opened.
Since the valve 4b is closed, the pressure in the cylinder 1b is
The pressure becomes larger than the pressure a, and the piston 2, the shaft 3, and the switching plate 16 move in the direction of arrow a, and at the same time, the steering blade 8
Rotates in the direction of the arrow mouth. When the switching plate 16 reaches a predetermined position, the switching plate 16 contacts the switch 17a and reverses the opening / closing direction of the valve 4 through the valve opening / closing instruction. Valve 4
When the opening and closing direction of the cylinder is reversed, the internal pressure of the cylinder 1a becomes larger than the internal pressure of the cylinder 1b, and the piston 2 and the shaft 3
Then, the switching plate 16 moves in the direction opposite to the arrow a. After that, the same operation is repeated, and the steering vane 8 repeatedly moves at a predetermined cycle instructed by the valve opening / closing indicator 18.

Embodiment 5. FIG. 5 is a spin missile actuator according to a fifth embodiment of the present invention, in which 1 is a cylinder, 2 is a piston, 3 is a shaft, 4 is a valve, 7 is a pressure pipe, 8 is a steering blade, and 9 is a pressure source. Reference numeral 10 is a seal, 16 is a switch switching plate, 17 is a switch, 18 is a valve opening / closing indicator, 19 is a nozzle, arrow a is a shaft moving direction, and an arrow mouth is a steering blade angle changing direction. In FIG. 5, the pressure of the pressure source 9 is applied to both the cylinders 1a and 1b, but since the valve 4a is open and the valve 4b is closed, the pressure of the cylinder 1b becomes larger than the pressure of the cylinder 1a, and the piston 2 and the shaft 3
Then, the switching plate 16 moves in the direction of arrow A, and at the same time, the steering blade 8 rotates in the direction of arrow. When the switching plate 16 reaches a predetermined position, the switching plate 16 contacts the switch 17a and reverses the opening / closing direction of the valve 4 via the valve opening / closing indicator. When the opening / closing direction of the valve 4 is reversed, the internal pressure of the cylinder 1a becomes larger than the internal pressure of the cylinder 1b, and the piston 2, the shaft 3, and the switching plate 16 move in the direction opposite to arrow a. After that, the same operation is repeated, and the steering vane 8 repeatedly moves at a predetermined cycle instructed by the valve opening / closing indicator 18. Further, in the present invention, one of the valve 4a and the valve 4b is always open, and when a stored gas or a combustion gas is used as the pressure source 9, a high-speed gas is always supplied from either the nozzle 19a or 19b. Gush out. This nozzle is arranged at a position that promotes the effect of the steering blade 8 for controlling the attitude of the missile, and an actuator that combines aerodynamic steering and reaction force control by a side thruster is obtained.

[0023]

As described above, according to the present invention, by simplifying the structure, the components other than the cylinder can be downsized or omitted, and the cylinder can be enlarged to increase the band of the actuator.

Further, according to the present invention, there is an effect that complicated control is not required due to the simplification of the configuration and the band of the actuator is increased.

Further, according to the present invention, there is an effect that the size of the actuator is reduced by simplifying the structure and the structure.

Further, according to the present invention, there is an effect that the price of the actuator can be reduced by simplifying the structure and the structure.

[Brief description of drawings]

FIG. 1 is a diagram showing an example of the overall configuration of a first embodiment of the present invention.

FIG. 2 is a diagram showing an example of the overall configuration of a second embodiment of the present invention.

FIG. 3 is a diagram showing an example of the overall configuration of a third embodiment of the present invention.

FIG. 4 is a diagram showing an example of the overall configuration of a fourth embodiment of the present invention.

FIG. 5 is a diagram showing an example of the overall configuration of a fifth embodiment of the present invention.

FIG. 6 is a diagram showing an example of the overall configuration of a conventional actuator.

[Explanation of symbols]

 1 Cylinder 2 Piston 3 Shaft 4 Valve 5 Solenoid 6 Discharge Port 7 Pressurizing Pipe 8 Steering Blade 9 Pressurizing Source 10 Seal 11 Displacement Detector 12 Displacement Comparator 13 Pressure Regulator 14 Link Rod 15 Change Rod 16 Switch Change Plate 17 Switch 18 Valve Open / close indicator 19 Nozzle I Shaft moving direction B Steering blade angle changing direction C Valve opening / closing direction

Claims (5)

[Claims] 1. A spin missile which is controlled to fly while rotating about a longitudinal axis of a machine body, and in which a steering wheel has a maximum steering angle in a predetermined roll rotation position of the machine body and is controlled to turn in a predetermined direction. In the actuator, a solenoid from which a signal from a sensor that produces a signal synchronized with the spin rotation frequency of the missile is input,
Two valves whose opening and closing are controlled by the action of the solenoid, a cylinder whose internal pressure is changed by opening and closing the two valves, and a piston which moves inside the cylinder by the pressure inside the cylinder and moves the steering blade. An actuator for a spin missile, characterized in that the actuator reciprocates in a movable range by the action of the signal and the solenoid, thereby moving the steering blade. 2. A spin missile that is controlled to fly while rotating about the longitudinal axis of the machine body, and the steering blade has a maximum steering angle in a predetermined direction when the roll rotation position of the machine body is in a predetermined direction. In the actuator, the pressure of the pressure source is guided to two interlocking valves via a pressure regulating valve, and one of the two valves is opened to apply the pressure of the pressure source to the cylinder, A piston that moves by the pressure inside the cylinder and moves the steering blade, a switching rod that moves according to the operation of the piston, and a connecting rod that interferes with the switching rod when the piston reaches a predetermined position. And the connecting rod reverses the opening / closing direction of the valve, whereby the piston continues the reciprocating motion autonomously, and the frequency of the reciprocating motion depends on the action of the pressure of the pressure source. An actuator for a spin missile, characterized in that the steering blade is moved by being adjusted. 3. A spin missile which is controlled to fly while rotating about the longitudinal axis of the machine body, and in which the roll rotation position of the machine body has a maximum steering angle of the steering blades in a predetermined direction and is controlled to turn in a predetermined direction. In the actuator, the pressure of the pressure source is guided to two interlocking valves via a pressure regulating valve, one of the valves is opened, and the pressure of the pressure source is applied to the cylinder. A piston that moves inside the cylinder and moves the steering blade, a switch switching plate that moves according to the operation of the piston, and a switch that causes the piston to interfere with the switch switching plate at a predetermined position are provided. Movement of the switch causes the opening and closing of the valve to be electrically reversed so that the piston continues to reciprocate autonomously. An actuator for a spin missile, characterized in that the reciprocating frequency is adjusted by the action of the pressure of the pressure source to move the steering blade. 4. A spin missile which is controlled to fly while rotating about the longitudinal axis of the airframe, and in which the roll rotation position of the airframe has the maximum steering angle of the steering blades in a predetermined direction and turns in a predetermined direction. In the actuator, two valves for guiding the pressure of a pressure source into the cylinder to discharge the internal pressure to the cylinder, and the pressure of one of the two divided cylinder chambers for dividing the cylinder into two. A piston that moves in the cylinder by opening to the atmosphere by the valve, a switch switching plate that moves by the operation of the piston, and a switch that causes the piston to interfere with the switch switching plate at a predetermined position, The switch is switched by the movement of the piston, the opening and closing of the valve is electrically reversed, and the piston continues to reciprocate autonomously. An actuator for a spin missile, characterized in that the steering wing is moved thereby. 5. A spin missile which is controlled to fly while rotating about the longitudinal axis of the airframe, and in which the roll rotation position of the airframe has a maximum steering angle of the steering blades in a predetermined direction and turns in a predetermined direction. In the actuator, two valves for guiding the pressure of a pressure source into the cylinder to discharge the internal pressure to the cylinder, and the pressure of one of the two divided cylinder chambers for dividing the cylinder into two. A piston that moves in the cylinder by opening to the atmosphere by the valve, a nozzle that discharges high-pressure gas in the cylinder in a predetermined direction with the pressure exhaust port of the cylinder directed in a predetermined direction, and the piston A switch switching plate that moves in response to the movement of the piston, and a switch that causes the piston to interfere with the switch switching plate at a predetermined position. The spin missile actuator is characterized in that the switch is switched by the switch, the opening and closing of the valve is electrically reversed, and the piston autonomously continues the reciprocating motion to move the steering wing.