JP2001124500A - Guided flier - Google Patents

Abstract

PROBLEM TO BE SOLVED: To reduce the aerodynamic resistance of a mother plane in condition that a guided flier is loaded on the mother plane, and also, to protect the constituent parts positioned at the rear of a guided flier from an obstacle in air or aerodynamic heating, and further, to secure the aerodynamic stability of the guided flier immediately after firing, in a guided flier which is fired rearward of the airplane whereon it is loaded. SOLUTION: A guided flier 3, which is fired rearward of an airplane whereon it is loaded, is equipped with a nozzle 4 for a propeller provided at the rear end face of itself 3, an unfolding wing 5 being folded and stored in the rear of itself 3, and a cover 7 being attached, such that it covers the nozzle 4 of the propeller and the unfolding wing 5, to the rear of itself 3.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a technology relating to a guided flying vehicle mounted on an aircraft (hereinafter referred to as "base unit") and fired toward a predetermined target located behind the base unit.

[0002]

2. Description of the Related Art FIG. 7 shows a conventional technique relating to a guided flying object. FIG. 7 (a) is a diagram showing the launch situation of the guided flying vehicle 3 launched toward the rear of the base unit 1, in which the changes in the state of the guided flying vehicle 3 after launch are shown in chronological order. Is shown. FIG. 7B is a view showing a guided flying object 3 attached to the base unit 1 via the launcher 2, wherein 1 is the base unit, 2 is a launcher, 3 is a guided flying unit, and 4 is a propulsion device. The nozzle 11 is a wing of the guided flying object.

FIG. 7A shows a guided flying object 3 mounted on the base unit 1. The guided flying object 3 is fired or dropped backward from the base unit 1, but immediately after the launch, the flight speed of the base unit 1 is reduced to the guided flying object 3.
Flying in the opposite direction to the flight direction (state) because of the direction opposite to the flight direction (state). After igniting the propulsion device, start flight control and accelerate in the flight direction over time (state) Continue flying (state).

In FIG. 7 (b), a guided flying object 3 is attached to a launcher 2, and thereafter is launched or dropped backward to fly.

The guided flying vehicle constructed as described above has a large aerodynamic resistance due to the wings 11 and a large aerodynamic resistance when the aircraft is mounted on the base unit 1 and flies. The nozzle 4 faces directly in the flight direction of the base unit 1, which adversely affects the flight performance of the base unit 1. Further, during flight, the nozzle 4 and the wings 11 of the propulsion device located at the rear of the guidance vehicle 3 may be damaged by collision with obstacles in the atmosphere or aerodynamic heating. In addition, immediately after being fired from the mother machine, when airflow is received from the rear of the aircraft, the wing 1 generates a large lift behind the aircraft.
1. Because there are protrusions such as the nozzle 4 of the propulsion device,
There was a possibility that the vehicle would become aerodynamically unstable, lose its posture and collide with the base unit 1.

SUMMARY OF THE INVENTION The present invention has been made to solve such a problem, and reduces the aerodynamic resistance of a base unit when the guided vehicle is mounted on the base unit, and is located at the rear of the guided vehicle. Its purpose is to protect the components from atmospheric obstacles and aerodynamic heating, and to ensure the aerodynamic stability of the guided flying vehicle immediately after launch.

[0006]

According to the first aspect of the present invention, there is provided a guided flying object which is provided at a rear end face of the flying object to be launched toward the rear of an aircraft to be mounted. A propulsion device comprising: a nozzle of a propulsion device, a deployable wing provided at a rear portion of the guide vehicle, and a cover attached to cover the nozzle of the propulsion device and the deployed wing in a folded state. It is.

According to a second aspect of the present invention, there is provided a guided flying object provided with a sealing material for sealing the inside of the cover.

[0008] A guided flying object according to a third aspect of the present invention has the cover having a pointed shape.

In a fourth aspect of the present invention, the cover is formed with a heat-resistant material inside.

According to a fifth aspect of the present invention, there is provided a guided flying object, wherein the cover has a weight therein.

[0011]

DESCRIPTION OF THE PREFERRED EMBODIMENTS Embodiment 1 FIG. 1 and FIG. 2 are views showing a guided flying object according to Embodiment 1 of the present invention. FIG. 1 is a diagram showing a launch situation of a guided flying vehicle launched toward the rear of the base unit.
Shows time-series changes in the state of the guided flying object after launch. FIG. 2A is a view showing a state in which the guided flying object is mounted on the base unit and flying, and FIG. 2B is a view showing a state immediately after the guided flying body is fired. Reference numeral 2 denotes a launcher, 3 denotes a guided flying object, 4 denotes a nozzle of a propulsion device, 5 denotes a deployment wing, 6 denotes a cover, and A denotes blast ejected from the nozzle 4 of the propulsion device.

FIG. 1 shows a guided flying object 3 mounted on the base unit 1. Guided flying object 3
Is fired or dropped backward from the main unit 1,
Immediately after the launch, the flight speed of the base unit 1 is opposite to the flight direction of the guidance vehicle 3, so that the airflow is received from the rear of the aircraft (state), the propulsion device is ignited, and the nozzle 4 of the propulsion device is ignited. The cover 6 is separated by the blast A, which is the combustion gas ejected from the air (state), and after a lapse of a predetermined time, or when the flying speed of the guided flying object 3 falls below a predetermined value by a speed detector (not shown). Is detected, a deployment command is generated from a control unit (not shown), the deployment wing 5 is deployed, flight control of the airframe is started (state), and the vehicle is directed toward a rearward target in a direction opposite to the traveling direction of the base unit 1. Let's fly (state). From the state, the deployment wing 5 is locked so as not to be deployed in a state of being folded in the direction toward the machine axis and fixed to the machine body. Further, in this state, the deployment wing 5 is unlocked in response to the deployment command, and the deployment wing 5 is directed outward from the machine axis by a deployment mechanism including a spring or a motor that applies a rotational torque to the deployment wing 5. Expand to

In the state of FIG. 1 in which the guided flying object 3 is mounted on the base unit 1 and is flying, that is, in FIG. 2A, the deployment is folded and stored with the nozzle 4 of the propulsion device having a large aerodynamic resistance. Since the wing 5 is covered by the cover 6 having a small aerodynamic resistance, the nozzle 4 and the deployable wing 5 of the propulsion device are protected from the external environment without increasing the aerodynamic resistance of the base unit 1.

FIG. 1 immediately after the launch vehicle 3 is fired
In the state shown in FIG. 2, that is, in FIG. 2B, the guided flying vehicle 3 receives an airflow from the rear of the aircraft due to the flight speed of the base unit 1, but the deploying wings 5 that easily generate lift behind the aircraft, and the nozzles 4 of the propulsion device Since the protrusions such as are covered by the cover 6, the protrusions are aerodynamically stable and can be smoothly separated from the base unit 1.

Embodiment 2 FIG. 3 is a view showing a guided flying object according to Embodiment 2 of the present invention.
3A shows a state in which the guided flying object is mounted on the base unit and is flying, and FIG. 3B shows a state immediately after the guided flying object is fired. In the figure, 1 is a mother machine, 2 is a launcher, 3 is a guided flying object, 4 is a nozzle of a propulsion device, 5 is a deployment wing,
Reference numeral 6 denotes a cover, and 7 denotes a sealing material. Other configurations and the flying state after the launch are the same as in the first embodiment.

In the state shown in FIG. 3A in which the guided flying vehicle 3 is mounted on the base unit 1 and flying, the deployed wing 5 folded and housed with the nozzle 4 of the propulsion device having a large aerodynamic resistance is used. , The nozzle 4 and the deploying wings 5 of the propulsion device are protected from the external environment without increasing the aerodynamic resistance of the base unit 1. Further, since the inside of the cover 6 is hermetically sealed by the seal member 7, the nozzle 4 and the deploying wing 5 of the propulsion device are not affected by moisture, dust and the like in the outside air.

FIG. 3 immediately after the launch vehicle 3 is fired
In (b), the guided flying object 3 receives an airflow from the rear of the aircraft according to the flight speed of the base unit 1, but the protrusions such as the deployment wing 5 and the nozzle 4 of the propulsion device, which are likely to generate lift at the rear of the aircraft, are covered by the cover 6. , And is aerodynamically stable, and can be smoothly separated from the base unit 1.

Embodiment 3 FIG. 4 is a view showing a guided flying object according to Embodiment 3 of the present invention.
4A shows a state in which the guided flying object is mounted on the base unit and flying, and FIG. 4B shows a state immediately after the guided flying object is fired. In the figure, 1 is a mother machine, 2 is a launcher, 3 is a guided flying object, 4 is a nozzle of a propulsion device, 5 is a deployment wing,
Reference numeral 8 denotes a cover with a sharp tip. Other configurations and the flying state after the launch are the same as in the first embodiment.

In the state shown in FIG. 4A in which the guidance flying object 3 is mounted on the base unit 1 and is flying, the deployment wing 5 folded and housed with the nozzle 4 of the propulsion device having a large aerodynamic resistance is further increased. Since the tip having a small aerodynamic resistance is covered by the pointed cover 8, the aerodynamic resistance of the base unit 1 is smaller than that of the first embodiment, and the nozzle 4 and the deployment wing 5 of the propulsion device are protected from the external environment. It is in a state.

FIG. 4 immediately after the launch vehicle 3 is fired
In (b), the guided flying object 3 receives an air current from the rear of the aircraft according to the flight speed of the base unit 1, but the protruding parts such as the deployment wing 5 and the nozzle 4 of the propulsion device, which are likely to generate lift at the rear of the aircraft, have tips. Since it is covered by the sharp cover 8, it is aerodynamically stable and can be smoothly separated from the base unit 1.

Embodiment 4 FIG. FIG. 5 is a view showing a guided flying object according to Embodiment 4 of the present invention.
(A) shows a state in which the guided flying vehicle is mounted on the base unit and is flying. FIG. 5 (b) shows a state immediately after the guided flying vehicle is fired, and a state in which the propulsion device is ignited and the cover is detached. Show. In the figure, 1 is a base machine, 2 is a launcher, 3 is a guided flying object, 4 is a nozzle of a propulsion device, 5 is a deployment wing, 9 is a cover made of heat-resistant material, and A is a blast jetted from a nozzle 4 of the propulsion device. Show. Other configurations and the flying state after the launch are the same as in the first embodiment.

In the state shown in FIG. 5A in which the guided flying object 3 is mounted on the base unit 1 and flying, the deployed wing 5 folded and stored with the nozzle 4 of the propulsion device having a large aerodynamic resistance is more aerodynamic. Since the cover 9 is made of a heat-resistant material having a small resistance, the aerodynamic resistance of the base unit 1 is smaller, and the nozzle 4 and the deploying wing 5 of the propulsion device are protected from the external environment.

FIG. 5 immediately after the launch vehicle 3 is fired
In (b), the guided flying object 3 receives an air current from the rear of the aircraft according to the flight speed of the base unit 1, but protrusions such as the deployable wing 5 and the nozzle 4 of the propulsion device, which are likely to generate lift at the rear of the aircraft, are made of heat-resistant material. The cover 9 is made of a material, so that it is aerodynamically stable and smoothly detaches from the base unit 1. After that, the propulsion device is ignited and the blast A ejected from the nozzle 4 of the propulsion device separates the cover 9 made of a heat-resistant material. The blasting force is applied to the cover 9 made of a heat-resistant material so that the heat
And securely separated from the mounting part.

Embodiment 5 FIG. 6 is a view showing a guided flying object according to Embodiment 5 of the present invention.
6A shows a state in which the guided flying object is mounted on the base unit and flying, and FIG. 6B shows a state immediately after the guided flying object is fired. In the figure, 1 is a mother machine, 2 is a launcher, 3 is a guided flying object, 4 is a nozzle of a propulsion device, 5 is a deployment wing,
Reference numeral 6 denotes a cover, and 10 denotes a counterweight mounted inside the cover 6. Other configurations and the flying state after the launch are the same as in the first embodiment.

In the state shown in FIG. 6A in which the guided flying object 3 is mounted on the base unit 1 and flying, the nozzle 4 of the propulsion device having a large aerodynamic resistance and the deployed wing 5 folded and stored are more aerodynamic. Since it is covered by the cover 6 having a small resistance, the nozzle 4 and the deployment wing 5 of the propulsion device are protected from the external environment without increasing the aerodynamic resistance of the mother machine 1.

FIG. 6 immediately after the launch vehicle 3 is fired
In (b), the guided flying object 3 receives an airflow from the rear of the aircraft according to the flight speed of the base unit 1, but the protrusions such as the deployment wing 5 and the nozzle 4 of the propulsion device, which are likely to generate lift at the rear of the aircraft, are covered by the cover 6. And become aerodynamically stable. Further, by providing the counterweight 10, the center of gravity of the airframe immediately after the launch is located upstream of the airflow as compared with the other embodiments, so that the aerodynamic center is located further downstream with respect to the center of gravity. As a result, a moment in the direction of canceling the lift behind the aircraft is generated, the state immediately after the launch becomes more aerodynamically stable, and the vehicle can be smoothly separated from the mother machine 1. In addition, after the cover 6 is separated, the weight of the aircraft is reduced by the weight of the counterweight 10, so that more efficient flight is possible. By using a heat-resistant material as the counterweight 10, the cover 6 that is hardly damaged by heat can be obtained.

[0027]

As described above, the present invention has the following effects.

According to the first aspect of the invention, the aerodynamic resistance of the base unit when the guided flying object is mounted on the base unit can be reduced. Further, it is possible to protect the nozzles and the deployment wings of the propulsion device from mechanical damage due to collision with an obstacle in the atmosphere and thermal damage due to aerodynamic heating during flight of the base unit. In addition, immediately after launch, the aircraft receives airflow from the rear of the aircraft, and before flying control starts, it stably aerodynamically separates from the mother aircraft without generating a large lift behind the aircraft and starts flying stably It becomes possible to do.

According to the second aspect of the invention, the aerodynamic resistance of the base unit when the guided flying object is mounted on the base unit can be reduced. Further, it is possible to protect the nozzles and the deployment wings of the propulsion device from mechanical damage due to collision with an obstacle in the atmosphere and thermal damage due to aerodynamic heating during flight of the base unit. In addition, it becomes possible to protect the nozzles and the deployment wings of the propulsion device from moisture and dust in the atmosphere. In addition, immediately after launch, the aircraft receives airflow from the rear of the aircraft, and before flying control starts, it stably aerodynamically separates from the mother aircraft without generating a large lift behind the aircraft and starts flying stably It becomes possible to do.

According to the third aspect of the present invention, the aerodynamic resistance of the base unit in a state where the guided flying object is mounted on the base unit can be further reduced. Further, it is possible to protect the nozzles and the deployment wings of the propulsion device from mechanical damage due to collision with an obstacle in the atmosphere and thermal damage due to aerodynamic heating during flight of the base unit. In addition, immediately after launch, the aircraft receives airflow from the rear of the aircraft, and before flying control starts, it stably aerodynamically separates from the mother aircraft without generating a large lift behind the aircraft and starts flying stably It becomes possible to do.

According to the fourth aspect of the invention, the aerodynamic resistance of the base unit in a state in which the guided flying object is mounted on the base unit can be reduced. Further, it is possible to protect the nozzles and the deployment wings of the propulsion device from mechanical damage due to collision with an obstacle in the atmosphere and thermal damage due to aerodynamic heating during flight of the base unit. In addition, immediately after launch, the aircraft receives airflow from the rear of the aircraft, and before flying control starts, detaches from the mother aircraft stably aerodynamically without generating large lift at the rear of the aircraft and starts flying stable It becomes possible to do. In addition, there is no danger of impairing the propulsion characteristics and aerodynamic characteristics of the guided flying vehicle due to incomplete separation of the cover.

According to the fifth aspect of the invention, the aerodynamic resistance of the base unit in a state where the guided flying object is mounted on the base unit can be reduced. Further, it is possible to protect the nozzles and the deployment wings of the propulsion device from mechanical damage due to collision with an obstacle in the atmosphere and thermal damage due to aerodynamic heating during flight of the base unit. In addition, in the state immediately before launch, receiving airflow from the rear of the aircraft and before starting flight control, a moment is generated in the direction to cancel the lift without generating a large lift behind the aircraft, and it is more aerodynamically stable. It is possible to separate from the mother machine and start flying stably.

[Brief description of the drawings]

FIG. 1 is a diagram showing an operation in Embodiment 1 of the present invention.

FIG. 2 is a configuration diagram showing the first embodiment of the present invention.

FIG. 3 is a configuration diagram showing a second embodiment of the present invention.

FIG. 4 is a configuration diagram showing a third embodiment of the present invention.

FIG. 5 is a configuration diagram showing a fourth embodiment of the present invention.

FIG. 6 is a configuration diagram showing a fifth embodiment of the present invention.

FIG. 7 is a diagram illustrating a conventional guided flying object.

[Explanation of symbols]

 REFERENCE SIGNS LIST 1 mother machine 2 launcher 3 guided flying object 4 propulsion device nozzle 5 deployment wing 6 cover 7 sealing material 8 sharp-pointed cover 9 heat-resistant material cover 10 counterweight 11 wing A blast

Claims (5)

[Claims] 1. A guided flying vehicle that is fired toward the rear of a mounted aircraft, wherein a nozzle of a propulsion device provided on a rear end surface of the flying vehicle and a rear portion of the guided flying vehicle are provided. A guided flying object comprising: a deployable deployable wing; and a cover attached so as to cover a nozzle of the propulsion device and the deployable wing in a folded state. 2. The guided flying object according to claim 1, further comprising a sealing material for sealing the inside of the cover. 3. The guidance flying object according to claim 1, wherein the cover has a pointed shape. 4. The guidance flying object according to claim 1, wherein the cover has a heat-resistant material inside. 5. The guided flying object according to claim 1, wherein the cover has a weight therein.