JP2000186900A - Guided projectile - Google Patents

Abstract

PROBLEM TO BE SOLVED: To ensure aerodynamically static stable state over the entire speed region by providing a stable wing moving back and forth in the axial direction of body and altering the aerodynamic characteristics when the speed of a projectile changes from rearward to forward. SOLUTION: A rail 9 is secured to the outer surface of a body 5 in the axial direction thereof, a stable wing 10 movable on the rail 9 is supported on the rail 9. Stoppers 11 are arranged at the opposite ends of the rail 9 and a tubular cover 8 is coupled with the stable wing 10 through a pulley 12 by means of a wire 13. Immediately after a guided projectile 1 is launched from a mother plane, the stable wing 10 moves to the front of the body and acts to cancel an angle of elevation α upon occurrence thereof thus ensuring aerodynamic static stability for air flow under a state flying rearward of the body. When the projectile 1 is flying forward, the stable wing 10 moves rearward thus ensuring aerodynamic static stability for air flow.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

TECHNICAL FIELD The present invention relates to a helicopter,
It relates to a guided flying vehicle mounted on an aircraft such as a fixed wing aircraft and capable of flying toward a target body located behind the aircraft, and more specifically, guidance that the guided flying vehicle receives airflow from behind. The purpose of the present invention is to propose a guided flying object that keeps the attitude of the airframe stable in the initial stage and in the middle and late stages of guiding the airflow from the front.

[0002]

2. Description of the Related Art Mounted on an aircraft (hereinafter referred to as "base machine"),
A conventional technique relating to a guided flying object capable of flying toward the rear of the base unit will be described with reference to the drawings. FIG. 4 is a diagram showing the behavior of a conventional guided flying vehicle that is fired from a base unit toward a target unit located behind the base unit. In the figure, 1 is a guided flying object, 2 is a base unit that flies at the speed Vo and fires the guided flying unit 1, 3 is a target body located behind the base unit 2, and 4 is a propulsion force of the guided flying unit 1. 22 is a stage in which the guided flying object 1 is mounted on the base unit 2, 23 is a launching unit that is launched from the base unit 2 during flight of the guided flying unit 1 toward the rear of the base unit, and the propulsion unit 4 is After the ignition, the aircraft is flying at the speed Vb toward the rear of the aircraft, 24 is the stage at which the speed toward the rear of the aircraft is reduced so that the guided vehicle 1 has a speed of 0, and 25 is the guided flight. This shows a stage in which the vehicle 1 is accelerated and is flying at a speed Va heading forward of the guided flying vehicle.

In step 22, the guided flying object 1 is mounted toward the rear of the base unit 2. After the presence of the target body 3 such as an aircraft and a guided missile that poses a threat behind the base unit 2, the guided flying object 1 fired from the base unit 2 returns to step 23 immediately after the propulsion device 4 is ignited. As described above, the aircraft flies at the flying speed Vb in the same direction as that of the base unit 2, that is, toward the rear of the guided flying body 1. Thereafter, the flight speed toward the rear of the aircraft is reduced and the flight speed is reduced to 0, and the state of the stage 24 is passed.
Is guided until. That is, when the direction of the flying speed of the guidance flying vehicle 1 is the rear of the aircraft, the relative speed with respect to the airflow is negative, and when the direction of the flying speed is forward of the aircraft, the relative speed with respect to the airflow is positive. . Accordingly, the relative speed with respect to the airflow of the guided flying object 1 changes from negative to positive in such a flying process.

FIG. 5 is a block diagram showing a conventional guided flying vehicle. FIG. 5 (a) shows a stage in which the guided flying vehicle 1 flies forward in the fuselage, and FIG. Each of the flying stages is shown. In the figure, 5 is the fuselage of the guidance vehicle 1, 6 is the steering wing of the guidance vehicle 1, 7
Is the stable wing of the guided flying vehicle 1, G is the center of gravity of the guided flying vehicle 1, N1 is the lift of the steering wing 6, X1 is the distance from the center of gravity G to the aerodynamic center of the steering wing 6, and N2 is the lift of the stable wing 7. , X2
Is the distance from the center of gravity G to the aerodynamic center of the stable wing 7, α is the angle of attack with respect to the airflow around the aircraft, Vair is the velocity vector of the airflow, and Va is the speed of the guided flying vehicle 1 in step 25 of flying forward of the aircraft. Vector, Ma is the rotational moment around the center of gravity G in the stage 25 of flying forward the aircraft, Vb is the velocity vector of the guided flying vehicle 1 in the stage 23 flying in the backward direction of the aircraft, and Mb is the flight backward of the aircraft. The rotational moment around the center of gravity G in step 23.

[0005] In a stage 25 in which the guided flying vehicle 1 flies forward, the rotational moment Ma around the center of gravity G of the guided flying vehicle 1 can be expressed by the following equation (1).

[0006]

(Equation 1)

The rotational moment Ma around the center of gravity G of the guided flying object 1 can be expressed by the following equation (1).
Is changed, or the angle of attack α increases due to disturbance such as turbulence of the flow around the body, the rotational moment Ma becomes positive and acts in a direction to cancel the increase in the angle of attack α. Therefore, the guided flying object 1 is aerodynamically stable.

On the other hand, in the stage 23 in which the guided flying vehicle 1 flies backward, the rotational moment Mb around the center of gravity G of the guided flying vehicle 1 can be expressed by the following equation (2).

[0009]

(Equation 2)

The rotational moment Mb around the center of gravity G of the guided flying object 1 can be expressed as shown in Equation 2.
When the angle of attack α increases due to a change in the course of the vehicle or due to disturbance such as turbulence in the flow around the body, the rotational moment Mb becomes negative and acts in a direction to further increase the angle of attack α. Therefore, the guided flying object 1 is not statically stable aerodynamically, so that it is difficult to fly stably. Therefore, it is necessary to constantly generate a rotational moment using the steering wings 6 to cancel the increase in the angle of attack α.

[0011]

When the guided flying object 1 capable of flying toward the rear of the base unit 2 is fired toward the rear of the base unit 2, the flying speed during the flying process is increased by the guided flight. The body of the vehicle 1 changes from a rearward direction to a forward direction. At this time, in the conventional guided flying vehicle 1, the direction of the moment around the center of gravity of the aircraft determined by the magnitude of the lift acting on the steering wings 6 and the stable wings 7 makes the flying aircraft stable while flying forward. Flight angle, but the angle of attack α while flying backward
This causes a problem in that it is difficult to ensure the stability of the attitude of the aircraft because an aerodynamically unstable state occurs due to the occurrence of a head-lifting moment that causes an increase. In addition, guidance flying object 1
In order to secure the posture stability of the vehicle, even if posture control was performed using the steering wing 6 to generate lift and generate a moment in a direction to cancel the head-lifting moment, a disturbance exceeding the control force was applied. In such a case, there is a problem that control becomes impossible.

SUMMARY OF THE INVENTION The present invention has been made to solve the above-mentioned problem, and in a guided flying object which is separated from a parent aircraft in flight and can fly toward the rear of the parent aircraft, the flying speed of the guided flying object is reduced. By changing the aerodynamic characteristics while the flying body changes from the rearward direction to the forward direction, and by making it aerodynamically stable in all speed regions, guided flying that can always achieve stable flying The purpose is to get the body.

[0013]

According to a first aspect of the present invention, there is provided a guided flying object which is separated from an aircraft in flight and is capable of flying toward the rear of the aircraft. A propulsion device disposed behind the fuselage, a steering wing provided in front of the fuselage of the guidance vehicle, and a blast attached to the rear end of the propulsion device and ignited by the propulsion device after being ignited A closed cylindrical cover on the rear end side that detaches rearward, a rail fixed to the outer surface of the fuselage of the guidance flying vehicle in the longitudinal direction of the axle, and suspended on the rail and supported on the rail in the longitudinal direction of the axle. A moving stabilizer, a stopper disposed at both ends of the rail to limit a movable range of the stabilizer, and connecting the cylindrical cover and the stabilizer in a U-shape via a pulley to guide the flying; Immediately after the body is fired A wire that transmits the tension generated by the tubular cover that has received the blast of the fired propulsion device moving backward to the stable wing, and that after a certain period of time has been blown by the heat of the blast and releases the tension transmitted to the stable wing, It is provided with.

The guided flying object according to the second invention is separated from an aircraft in flight, and is capable of flying toward the rear of the aircraft. A propulsion device, a steering wing provided at the front of the fuselage of the guidance flying vehicle, a rail fixed to the outer surface of the fuselage of the guidance flying vehicle in the longitudinal direction of the aircraft, and suspension on the rail. A stabilizer that is supported and moves on the rail in the longitudinal direction of the machine axis, a stopper that is provided at both ends of the rail to limit the movable range of the stabilizer, and a plane orthogonal to the machine axis on the wing surface of the stabilizer. An auxiliary wing is provided with the wing surface oriented in a parallel direction and transmitting an air resistance force received by the wing surface during flight to a stable wing.

[0015] The guided flying object according to the third invention is separated from an aircraft in flight and is capable of flying toward the rear of the aircraft. A propulsion device, a steering wing provided at the front of the fuselage of the guidance flying vehicle, a rail fixed to the outer surface of the fuselage of the guidance flying vehicle in the longitudinal direction of the aircraft, and suspension on the rail. The stable wing is moved in the longitudinal direction of the machine via a stable wing that is supported and moves on the rail in the longitudinal direction of the machine and a power transmission unit that converts a driving torque into a translational force in the longitudinal direction of the machine and transmits the translational force to the stable wing. A drive motor to be driven, a drive controller for giving a drive command to the drive motor, and detecting that the guided flying object has fallen below a certain speed after firing the guided flying object, and outputting a signal to the drive controller. Speed detection It is that a stage.

[0016]

DESCRIPTION OF THE PREFERRED EMBODIMENTS Embodiment 1 FIG. 1 is a configuration diagram showing a first embodiment of the present invention, and FIG. 1 (a) shows a state in which a guided flying object 1 flies forward of an aircraft.
(B) shows a state in which the aircraft flies backward. In the figure, reference numeral 8 denotes a cylindrical cover attached to the rear end of the propulsion device 4 and receives a blast A after being ignited by the propulsion device and detaches rearward.
Rails fixed on the outer surface of the
Is a stable wing suspended on the rail 9 and movable on the rail 9; 11 is stoppers provided at both ends of the rail 9;
Reference numeral 13 denotes a wire connecting the tubular cover 8 and the stabilizing wing 10 via a pulley 12, and the rest is the same as a conventional guided flying object.

FIG. 1 (b) shows a state in which the guided flying vehicle 1 constructed as described above is in a state immediately after the guided flying vehicle 1 is fired from the base unit 2, that is, a state in which the flying vehicle 1 flies backward at a speed Vb. ), The propulsion device 4 is ignited and receives the pressure of the blast A that blows out, so that the cylindrical cover 8 separates to the rear of the fuselage, and the cylindrical cover 8 receives the rear of the fuselage via the tension Tb generated on the wire 13. The force is transmitted to the stabilizer 10. Since the wire 13 connects the tubular cover 8 and the stabilizer 10 in a U-shape via the pulley 12, the stabilizer 10 slides on the rail 9 and moves forward of the fuselage. It reaches the position where it hits the stopper 11 attached to the front end of the rail 9. At this time, the stable wing 10
Is located closer to the front of the fuselage, and satisfies the relationship shown in Expression 3 with respect to the distance X2b between the center of gravity G of the guided flying vehicle 1 and the aerodynamic center of the stabilizer 10 so that the center of gravity G of the guided flying vehicle 1 is satisfied. The surrounding rotational moment Mb1 is expressed as shown in Equation 4, and acts in a direction to cancel the increase when the angle of attack α is generated, so that aerodynamic static stability against airflow can be secured in a state of flying backward of the aircraft. .

[0018]

(Equation 3)

[0019]

(Equation 4)

Next, FIG. 1 (a) shows a state in which the guided flying object 1 is fired from the base unit 2 and the propulsion unit 4 has been ignited for a while, that is, a state in which the aircraft flies forward at a speed Va. The cylindrical cover 8 and the stable wing 1
The wire 13 which has been connected between the fuselage 0 and the blast A ejected from the propulsion device 4 continues to be blown by the high-temperature heat flow of the blast A, and the stabilizer 13 is released from the pulling force of the wire 13 in the forward direction of the fuselage. , The guided flying object 1 is shown in Fig. 1 (b)
The stable wing 10 slides on the rail 9 due to the inertia force acting in the acceleration process of reducing the rearward-facing speed Vb shown in FIG. 1 and flying at the forward-aircraft speed Va shown in FIG. It moves toward the rear of the fuselage and reaches a position where it hits a stopper 11 attached to the rear end of the rail 9. At this time, the stable wing 10 is located near the rear of the fuselage, and the distance X2a between the center of gravity G of the guided flying vehicle 1 and the aerodynamic center of the stable wing 10 satisfies the relationship shown in Expression 5, thereby leading to the guided flying. The rotational moment Ma1 around the center of gravity G of the vehicle 1 is expressed as shown in Formula 6, and acts in a direction to cancel the increase when the angle of attack α is generated. Therefore, even when flying forward, the aerodynamic force against the airflow is obtained. Static stability can be secured.

[0021]

(Equation 5)

[0022]

(Equation 6)

Embodiment 2 FIG. FIG. 2 is a block diagram showing a second embodiment of the present invention. FIG. 2 (a) shows a state in which the guided flying object 1 flies forward of the fuselage, and FIG. 2 (b) shows a state where it flies backward. Respectively. In the figure, 9 is a rail fixed to the outer surface of the fuselage 5 of the guidance flying vehicle 1 in the longitudinal direction of the machine axis, 10 is a stable wing suspended on the rail 9 and movable on the rail 9, and 11 is a rail 9 Stoppers 14 are provided at both ends of the stable wing 10
Auxiliary wings are provided on the wing surface in a direction orthogonal to the machine axis, and the other components are the same as those of the conventional guided flying object.

FIG. 2 (b) shows a state in which the guided flying vehicle 1 configured as described above has just been launched from the base unit 2, ie, is flying backward at a speed Vb. ), The airflow V in which the auxiliary wings 14 whose wing faces in the direction orthogonal to the heading flows from the rear of the fuselage.
Due to the action of the air resistance force directed to the front of the fuselage generated in response to the air, the stabilizer wing 10 having the auxiliary wings 14 on the wing surface slides on the rails 9 and moves toward the front of the fuselage. To the position where the stopper 11 is attached to the stopper 11. At this time, the stabilizer 10 is located near the front of the fuselage, and the center of gravity G of the guidance vehicle 1 and the stabilizer 10 are
Satisfies the relationship shown in Expression 7 with respect to the distance X2b to the center of aerodynamics, the rotational moment Mb2 about the center of gravity G of the guided flying object 1 is expressed as shown in Expression 8, and the angle of attack α
When the airplane is generated, it acts in a direction to cancel the increase, so that aerodynamic static stability against airflow can be ensured in a state where the aircraft flies backward.

[0025]

(Equation 7)

[0026]

(Equation 8)

Next, in FIG. 2 (a), which shows a state in which the guided flying object 1 is fired from the base unit 2 and has passed for a while, that is, a state in which it flies forward at a speed Va, the traveling direction of the aircraft is changed. It is upside down. When the guided flying vehicle 1 flies at the forward-facing speed Va shown in FIG. 2A by reducing the rearward-facing speed Vb shown in FIG. 2B, the wing surface becomes orthogonal to the aircraft axis. The stabilizing wings 10 having the auxiliary wings 14 on the wing surface are mounted on the rails 9 by the action of the rearward-facing air resistance generated by the facing auxiliary wings 14 receiving the airflow Vair flowing from the front of the aircraft. To the rear of the fuselage, and reaches a position where it hits a stopper 11 attached to the rear end of the rail 9. At this time, the stabilizer 10 is located near the rear of the fuselage,
By satisfying the relationship shown in Expression 9 with respect to the distance X2a between the center of gravity G of the guided flying vehicle 1 and the aerodynamic center of the stable wing 10, the rotational moment Ma2 around the center of gravity G of the guided flying vehicle 1 is expressed as shown in Expression 10. In addition, when the angle of attack α is generated, it acts in a direction to cancel the increase, so that aerodynamic stability against airflow can be secured even in a state of flying forward of the aircraft.

[0028]

(Equation 9)

[0029]

(Equation 10)

Embodiment 3 FIG. 3 is a configuration diagram showing a third embodiment of the present invention. FIG. 3 (a) shows a state in which the guided flying object 1 flies forward of the fuselage, and FIG. 3 (b) shows a state where it flies backward. Respectively. In the drawing, 9 is a rail fixed to the outer surface of the fuselage 5 of the guidance flying vehicle 1 in the longitudinal direction of the machine axis, 10 is a stable wing suspended on the rail 9 and movable on the rail 9, and 15 is a stable wing. A drive motor 16 for generating power to move 10 in the longitudinal direction of the machine axis. 16 applies a pulling force to the stable wing 10 in the forward and backward directions of the machine axis to move or stop the stable wing 10 to an arbitrary position on the rail 9. A belt transmission 17 arranged so as to be able to transmit the rotation torque of the drive output shaft of the drive motor 15 to the belt transmission 16;
18 is a drive controller for giving a drive command to the drive motor 15;
Reference numeral 19 denotes a differential pressure sensor which is supported outside the fuselage 5 of the guidance flying vehicle 1 in parallel with the machine axis and detects a pressure difference between the front and rear sides. This is a differential pressure detector that outputs a signal for instructing the controller 18 to issue a drive command for the drive motor 15, and the other components are the same as those of the conventional guided flying object.

FIG. 3 (b) shows a state in which the guided flying vehicle 1 has just been launched from the base unit 2 in the guided flying vehicle configured as described above, that is, a state in which the flying vehicle 1 flies backward at the speed Vb. In the step (1), a drive command is issued from the drive controller 18 to the drive motor 15 as an initial setting of the guidance flying vehicle 1 so as to position the stabilizing wing 10 at the forefront of the rail 9, and the rotation of the drive output shaft of the drive motor 15 The torque is transmitted to the stabilizer 10 as a control force via a power transmission mechanism constituted by the gear 17 and the belt transmission device 16,
The stabilizer 10 is at the forefront of the rail 9 and is stationary. At this time, the stable wing 10 is located near the front of the fuselage, and satisfies the relationship shown in Expression 11 with respect to the distance X2b between the center of gravity G of the guided flying vehicle 1 and the aerodynamic center of the stable wing 10, thereby guiding the guided flight. The rotational moment Mb3 around the center of gravity G of the vehicle 1 is expressed as shown in Equation 12, and acts in a direction to cancel the increase when the angle of attack α is generated. Stable static stability.

[0032]

[Equation 11]

[0033]

(Equation 12)

Next, in FIG. 3A, which shows a state in which the guided flying object 1 has been fired from the base unit 2 and has been flying for a while, that is, a state in which it flies forward at a speed Va, the traveling direction of the aircraft is reversed. are doing. The guided flying vehicle 1 reduces the velocity Vb in the rearward direction of the aircraft shown in FIG.
In the process of flying at the forward-facing speed Va shown in (a), if the forward-rearward speed decreases and the pressure difference between the front and rear of the differential pressure sensor 19 becomes smaller than a certain level, the guiding flying vehicle 1 will soon come out. Since the vehicle travels forward, the differential pressure detector 20 outputs a signal to the drive controller 18 to issue a drive command for the drive motor 15, and the drive controller 18 sends the drive motor 15 the stable wing 10 at the end of the rail 9. A drive command to position the drive unit 15 is provided, and the rotational torque of the drive output shaft of the drive motor 15 is transmitted to the stable wing 10 as a control force via a power transmission mechanism including a gear 17 and a belt transmission device 16. , The stable wing 10 slides on the rail 9 and moves toward the rear of the fuselage.
Rest at the end of the. At this time, the stable wing 10 is located near the rear of the fuselage, and the distance X2a between the center of gravity G of the guided flying object 1 and the aerodynamic center of the stable wing 10 satisfies the relationship shown in Expression 13 so that the guided flight is performed. The rotational moment Ma3 around the center of gravity G of the vehicle 1 is expressed as shown in Expression 14, and acts in a direction to cancel the increase when the angle of attack α is generated. Therefore, even when flying forward, the aerodynamic force against the airflow Static stability can be secured.

[0035]

(Equation 13)

[0036]

[Equation 14]

[0037]

Since the guided flying object according to the present invention is constituted as described above, the following effects can be obtained.

According to the first to third aspects of the present invention, there is provided a guided flying object separated from an aircraft in flight and capable of flying toward the rear of the aircraft, comprising a stabilizing wing moving in the longitudinal direction of the aircraft, By changing the aerodynamic characteristics while the flying body speed changes from the rear of the aircraft to the front, it is aerodynamically stable in all speed ranges, so that guided flying can always secure a stable flight You can get the body.

[Brief description of the drawings]

FIG. 1 is a configuration diagram of a guided flying object according to a first embodiment of the present invention.

FIG. 2 is a configuration diagram of a guided flying object according to a second embodiment of the present invention.

FIG. 3 is a configuration diagram of a guided flying object according to a third embodiment of the present invention.

FIG. 4 is a view showing the behavior of a conventional guided flying object.

FIG. 5 is a configuration diagram of a conventional guided flying object.

[Explanation of symbols]

DESCRIPTION OF SYMBOLS 1 Guided flying object, 2 mother aircraft, 3 target bodies, 4 propulsion devices, 5 fuselage, 6 steering wings, 7 stable wings, 8 cylindrical cover, 9 rails, 10 stable wings, 11 stoppers, 12
Pulley, 13 wire, 14 aileron, 15 drive motor, 16 belt transmission, 17 gear, 18 drive controller, 19 differential pressure sensor, 20 differential pressure detector.

Claims (3)

[Claims] 1. A guided flying vehicle separated from an aircraft in flight and capable of flying toward the rear of the aircraft, comprising: a propulsion device disposed behind a fuselage of the guided flying vehicle; A steering wing provided at a front portion of a body of the body, and a closed cylindrical cover at a rear end side attached to a rear end of the propulsion device and receiving a blast after being ignited by the propulsion device and detaching rearward. A rail fixed to the outer surface of the fuselage of the guidance flying vehicle in the longitudinal direction of the aircraft, a stabilizer wing suspended on the rail and moving on the rail in the longitudinal direction of the aircraft, and disposed at both ends of the rail. A stopper that limits the range in which the stabilizer can move, a blast of the propulsion device that ignites immediately after the guidance flying object is fired by connecting the tubular cover and the stabilizer to a U-shape via a pulley. The cylindrical cover received is behind And a wire for transmitting the tension generated by the separation to the stable wing and releasing the tension transmitted to the stable wing after being blown by the heat of the blast after a lapse of a predetermined time. 2. A guidance vehicle separated from an aircraft in flight and capable of flying toward the rear of the aircraft, comprising: a propulsion device disposed behind a fuselage of the guidance vehicle; A steering wing provided at the front of the fuselage of the body, a rail fixed to the outer surface of the fuselage of the guided flying vehicle in the longitudinal direction of the aircraft, and suspended on the rail to move in the longitudinal direction of the aircraft on the rail. A stabilizer provided at both ends of the rail to limit a movable range of the stabilizer, and a stopper provided on the wing of the stabilizer in a direction parallel to the plane orthogonal to the machine axis and flying. A guided flying object comprising: an auxiliary wing that transmits air resistance received on a wing surface to a stable wing during a test. 3. A guided vehicle separated from an aircraft in flight and capable of flying toward the rear of the aircraft, comprising: a propulsion device disposed behind a fuselage of the guided vehicle; A steering wing provided at the front of the fuselage of the body, a rail fixed to the outer surface of the fuselage of the guided flying vehicle in the longitudinal direction of the aircraft, and suspended on the rail to move in the longitudinal direction of the aircraft on the rail. A stable wing, a drive motor for moving the stable wing in the longitudinal direction of the machine via power transmission means for converting a driving torque into a translational force in the longitudinal direction of the machine and transmitting the translational force to the stable wing; and a drive command to the drive motor. And a speed detecting means for outputting a signal to the drive controller by detecting that the guided vehicle has fallen below a certain speed after firing the guided vehicle. Guidance flying Body.